Final Report - Aerospace Engineering · Web viewTopic Area: Fluid Dynamics Department of Aerospace Engineering and Mechanics University of Minnesota 107 Akerman Hall 110 Union Street

Study of Droplet Coalescence Criteria of a Liquid/Liquid Interface in Micro-Gravity Conditions

Topic Area: Fluid Dynamics

DEPARTMENT OF AEROSPACEENGINEERING AND MECHANICS

UNIVERSITY OF MINNESOTA

107 Akerman Hall110 Union Street SE

Minneapolis, MN 55455

Team Contact:Nicolas G. Schellpfeffer

[email protected] / (612) 730-2723

Supervisor:Dr. Ellen K. Longmire


Team Members:

Nicolas G. Schellpfeffer, flight crewSenior, Aerospace Engineering


Richard A. Johnson, flight crewSenior, Aerospace Engineering


Matthew J. Stegmeir, alt. flight crewSenior, Aerospace Engineering


Maria L. Bigwood, flight crewSenior, Aerospace Engineering


Nathan T. Koelln, flight crewSenior, Aerospace Engineering


Kimberly A. Lay, ground crewSenior, Aerospace Engineering


Submitted on:July 12, 2003

mailto:[email protected]








Table of Contents

1.0 Abstract................................................................................................................ 3

2.0 Experiment Background..................................................................................... 4

3.0 Experiment Description...................................................................................... 6

4.0 Equipment Description....................................................................................... 7

5.0 Structural Analysis.............................................................................................. 10

5.1 Free Body Diagram............................................................................................ 10

5.2 Listing of Weights and Materials........................................................................ 11

5.3 Safety Factors..................................................................................................... 13

6.0 Electrical Analysis............................................................................................... 14

6.1 Load Tables........................................................................................................ 15

6.2 Stored Energy..................................................................................................... 16

6.3 Electrical Kill Switch.......................................................................................... 16

6.4 Loss of Electrical Power..................................................................................... 16

7.0 Experimental Procedures & Data Acquisition.................................................. 17

7.1 Equipment Shipping to Ellington Field..............................................................17

7.2 Ground Operations.............................................................................................17

7.3 Loading...............................................................................................................17

7.4 Pre-Flight...........................................................................................................18

7.5 Take-off/Landing.................................................................................................18

7.6 In-Flight..............................................................................................................18

7.7 Post-Flight..........................................................................................................18

7.8 Off-Loading.........................................................................................................18

7.8 Data Acquisition.................................................................................................18

8.0 Experimental Analysis......................................................................................... 20

8.1 Ground Test Analysis..........................................................................................20

8.2 Flight Test Analysis............................................................................................22

8.3 Comparative Analysis.........................................................................................24

9.0 Conclusions........................................................................................................... 27

10.0 Outreach Program............................................................................................. 28

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10.1 Science Museum of Minnesota..........................................................................28

10.2 Local Schools....................................................................................................28

10.3 Local Press.......................................................................................................29

10.4 Flyer’s Hometown Press...................................................................................29

11.0 Bibliography....................................................................................................... 30

Appendices.................................................................................................................. 31

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1.0 Abstract:

Using the zero gravity environment created aboard NASA’s KC-135A aircraft, results show the dependability of the gravitational force on the coalescence of fluids. The analysis and results indicate that the absence of gravity favors coalescence. With the dominant force no longer being gravity, the collisions have fewer disturbances causing an increased stability that promotes the coalescence of the two droplets. Therefore, in a zero gravity environment coalescence occurs over a larger region of collisions. Moreover, the data obtained and analysis of the fluid dynamic properties during the each stage of the collision validates the result of the experiment. The data shows obvious shifts in transitional boundaries of coalescence between the ‘normal’ and zero gravity environments. The shifts in transitional boundaries directly show the increased region of coalescence. The analysis of the fluid dynamic properties of each stage of a collision also supports the conclusions. The presence of a gravitational force creates a less stable collision, where gravity causes the impact parameter to continually vary changing the direction of the droplets, which causes instability during the film drainage stage of a collision. The tests performed indicate that an environment absent of a gravitational force promotes stable collisions, therefore favoring a wider region of coalescence.

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2.0 Experiment Background:

The criterion for coalescence of two droplets colliding in a liquid-liquid interface is studied in micro-gravity conditions. Previous experiments in this subject have used droplet sizes with diameters on the order of microns to justify the assumption that buoyancy forces were negligible. For this experiment the ability to perform the collisions in a zero gravity environment creates a unique opportunity to analyze the criteria for coalescence on a macroscopic scale. The zero gravity environment will establish if coalescence can be determined directly by two dimensionless parameters, the Weber number and impact parameter. With buoyancy forces not present, the properties of droplet collision and coalescence are defined only by their size, relative velocity and position at impact. Variations of these parameters will be studied to determine when coalescence occurs.

The collision of two droplets will result in one of three possible outcomes: shattering, bouncing, and coalescence (See Figure 2.1). Shattering occurs at high relative velocities and will not be the focus in this experiment. As is bouncing a trivial result and will also not the main focus when it occurs. Coalescence is a more intriguing phenomenon and will be the emphasis of our experiment.

Figure 2.1: Time Sequence of two-drop coalescence experiments (a) Coalescence does not occur. (b) Coalescence does occur. (Taken from Leal, L.G. – 2000)

Coalescence is the combination of two discrete fluid particles and occurs in a three-stage process beginning with the approach of the particles toward one another. The drag on the particles is well known due to the maintained spherical shapes. This allows the trajectories to be easily modeled. The second stage is the ambient liquid film drainage between the droplets as the separation distance becomes small compared to the droplet radii. It is believed that gravity affects the drainage rate; therefore previous experiments are done on a microscopic scale. The final stage is the rupture of the film between the fluid droplets, which causes a combination of the two volumes. Coalescence of the droplets will occur when a critical thickness of the film is reached; if this thickness is not reached the droplets will bounce off one another.

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After coalescence the droplets may remain together or separate. The outcome of coalescence is dependant on the ratio of the inertial energy of the droplet to its surface energy, which is quantified by the Weber number (see Figure 2.2). Separation of the droplets can occur by stretching or reflexive separation. Stretching involves the elongation of the new fluid particle after combination, while reflexive separation is passing of the droplets through one another with no significant change in the original droplet properties. If the droplets combine and remain together they will oscillate until slowed by viscous effects. Additional effects that will not be considered in the realm of this experiment are initial droplet oscillations from nozzle detachment and droplet wake interactions in the collision zone.

Figure 2.2: Analytically obtained regions of coalescence, reflexive separation, and stretching separation for two drops of same size,

together with experimental data (Taken from Ashgriz - 1990)

Previous research on droplet coalescence has been studied; however, the effects of micro-gravity on this phenomenon are not completely understood, and it is the intention of this experiment to determine the manner in which the droplets will behave.

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3.0 Experiment Description:Coalescence of liquid drops dispersed in an immiscible liquid has a vast importance in many industrial applications, including liquid-liquid extraction, emulsification, and polymer blending processes. Our aim is to conduct experimentation on the effects of droplet diameter and velocity on the probability of a droplet collision leading to coalescence or separation. More specifically our objectives include:

Eliminating the effects of buoyancy forces on the droplets through the use of the micro-gravity environment.

Studying how the critical film thickness is affected as droplet size is varied. Observing how the collision outcome is affected by the relative velocity between

the two droplets. Comparing macroscopic droplet interactions to previously obtained microscopic

droplet data.

The experiment is fully defined by seven dimensionless parameters: Weber number (We), impact parameter (x), Reynolds number, density ratio, viscosity ratio, diameter ratio, and a velocity ratio. However, the Weber number and impact parameter primarily influence the outcome of droplet collision. In our experiment we intend to vary the droplet diameter (d) and the droplet velocity (U), which are related to the Weber number through the following equation:

dUWe

2

(3.1)

where ρ is density of the droplet fluid, and σ is the interfacial surface tension between the droplet and ambient fluids. The density and surface tension will be experimentally determined constants. The other significant dimensionless quantity in this experiment is the impact parameter, defined by:

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2dd

Xx

(3.2)

where X is the distance from the center of one drop to the relative velocity vector placed at the center of the other drop (see Figure 4.1), multiplied by two, and divided by the sum of the two drops diameters. The impact parameter varies between 0 and 1, where zero corresponds to a head-on collision and tangential collisions have an impact parameter of one.

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Figure 3.1: Definition of the impact parameter (Taken from Johansen, S.T. – 2002)

Our hypothesis is that collected data will validate previously determined relationships between dimensionless parameters. It is our belief that the direction and magnitude of the droplets’ velocities and sizes can be directly related to coalescence when the buoyancy forces are not present. The main objective of the experiment is to find a relationship between the impact parameter and the Weber number for which coalescence or separation of the colliding droplets occurs.

4.0 Equipment Description:The following are the main elements of our experimental apparatus:

Plexiglas Tank:The tank is 18” tall x 9” wide x 9” deep, and is constructed of ½” thick Plexiglas with a total fluid capacity of 4.43 gallons. The tank is held together using Weld-On 3, manufactured by the IPS Corporation. A quarter turn valve will be used for filling the tank. The top of the tank will include an accumulator, which will adjust for pressure and volume changes during flight. It is secured to the sides with bolts and an o-ring is used to prevent possible leaks. The tank includes a deflection plate located slightly above the fluid interface to decrease fluid mixing during transitions. The plate is also used as a contrasting background for the top video camera.

Nozzles:The nozzles, fabricated from stainless steel pipe, are used to insert the water-glycerin mixture into the tank. The nozzle separation distance will be adjustable. Swage lock seals around the nozzle connections to the tank allow for movement

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X

U1

U2

Ur = U2 - U1

Ø = d1

Ø = d2

of the nozzles while preventing the fluids from leaking.

Solenoid Valves:Two identical solenoid valves manufactured by J. D. Gould Company, Inc., model number M-3V, will be used to control the flow from the nozzles. The solenoid valves are internal pilot piston operated valves. These will allow us to precisely vary the amount of fluid contained in each set of droplets. A simple electronic controller will be used to control the valves’ duty cycles.

Pump:A centrifugal pump manufactured by the Little Giant Pump Company, model number 1.5-MDI-SC, will be used to provide a constant pressure head at the nozzles. The pump contains a leak-proof, seal-less, magnetic drive. The advantage of using a centrifugal pump is that it is capable of continuously running while the solenoid valves are closed. The pump is connected to a surge protector, which functions as our main kill switch. A voltage regulation attached to the pump allows for the variations of the pressure head.

Fluids:Two fluids will be used in this experiment: mineral oil and a 50:50 water/glycerin mixture (based on volume). The past two University of Minnesota Micro-Gravity teams have used these fluids, which have been proven to provide consistent performance under all gravity conditions encountered aboard the research plane. The interfacial surface tension between the fluids is 14.3 mN/meter.

Fluids Density (kg/m3)

Mineral Oil 860

Water/Glycerin 1150

Tubing:Two types of tubing will be used to transfer the fluid from the pump to the valves. Flexible plastic tubing is fastened onto plastic nipples using hose clamps will be used to connect the pump to the tank and the solenoid valves. Stainless steel pipe was used to fabricate the nozzles. Timing Circuit:A 555 integrated circuit timer regulates the opening and closing of the solenoid valves. The duty cycle is controlled by a 100 kilo-ohm potentiometer. The interval between pulses is set at approximately five seconds. A nine-volt battery powers the circuit. Transistors are used to amplify the output signal to the 24 volts necessary to operate the solenoid valves. The timing circuit contains a kill switch.

Accelerometer Circuit:

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An integrated circuit accelerometer, ADXL202, connected to a digital LCD panel, will be used to obtain g-force values while in flight. A nine-volt battery powers the circuit. The analog output of the accelerometer is converted to a digital signal by an A/D converter. A basic stamp controller processes the digital output and controls the LCD.

Video Cameras:Two digital cameras (Canon ZR40) will be positioned orthogonal to each other. This will allow us to obtain multiple continuous video streams of the flow. These cameras are capable of capturing images at 30 frames per second and are equipped with a variable shutter speed. Time will be displayed in every frame to allow us to correlate the images from both cameras. Both cameras will be connected to the surge protector, and are mounted on the external frame.

Lights:Four fluorescent lights with their respective casings will be used to illuminate the testing area. The lights are connected to the frame with Velcro. Each light uses four AA batteries.

Frame:We will support our experiment with a frame made of Unistrut™. This material has been used for the last two years by the University of Minnesota Micro-Gravity Fluids research teams. The cross section of the frame is 1 5/8 in2. The outside dimensions of the frame are 42 in. L x 29 in. H x 19 in. W. This structure will support our experiment. All sharp angles and edges will be rounded and padded in accordance with the hazard checklist. Eighth inch plastic sheeting will be attached with Velcro around the outside of the frame as a secondary leak protection barrier.

Total Assembly:The frame and location of the major components are shown in Figure 5.2. The assembly will be discussed extensively in the structural load analysis section.

Component

Description

Weight

(lbs)

Dimensions

(in., LxWxH)Material

Camera #1 1 5.25x3x4 Aluminum Mounting Plate

Camera #2 1 5.25x3x4 Aluminum Mounting Plate

Tank and Fluids 70 9x9x18 Plexiglas and PVC box, Aluminum Mounting Plate, Glycerin-Water, Mineral Oil

Frame 105 42x19x29 Steel

Timing Circuit 3 4x7x3 Aluminum

Accelerometer Circuit 2 2x2x1 Plastic

Pump 7 7x3.5x4 Aluminum Mounting Plate

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Component

Description

Weight

(lbs)

Dimensions

(in., LxWxH)Material

Nozzle (2) 5 1x1x6 Steel

Tubing, Clamps 10 N/A Plastic, PVC, Aluminum

Solenoid Valves (2) 10 3x4x6 Brass

Lights (4) 5 1x1x8 Plastic, Fluorescent Bulbs

Secondary Plastic Covering 10 Varies Plastic

Total 230

Table 4.1: Summary of experimental hardware

5.0 Structural Analysis

5.1 Free Body Diagram

The centers of gravity (CG) of significant items are listed (Table 5.1) and diagrammed below (Figure 5.1):

Figure 5.1: Free Body Diagram

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Item Weight (lbs) Location (in)x y z

Frame 105 21.0 9.8 14.5Tank 67 15.0 7.0 9.8Pump 6 29.5 9.5 4.0Shelf 6 32.0 9.5 14.7

All Other Items 41 19.2 10.6 13.8CG 225 19.4 9.1 12.7

Table 5.1: CG

5.2 Listing of Weights and Materials

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Figure 5.2 – Experimental Setup (developed using SolidWorks)

Figure 5.3 – Tank Drawing (developed using SolidWorks)

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Figure 5.4: Experiment Photo

5.3 Safety Factors

Safety factors derived from analysis in the NASA-RGSFOP TEDP are presented in Table 5.2:

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http://mattsteg.homeunix.com/gallery/NASA/NASA_151?full=1

Table 5.2: Safety Factors

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6.0 Electrical Analysis

Our experiment includes six electrical circuits. These include a main 115VAC circuit, which will be powered from a single 115 VAC outlet on the aircraft, a 24VDC circuit powered by a power supply connected to the 115 VAC source, and 4 battery-powered circuits. These are a 9V timing circuit, which controls the 24V solenoid circuit, a 9V accelerometer circuit, and two digital cameras with onboard 7.4V batteries. The cameras will normally be operated in AC mode via the included 9.6 VDC power supplies. All exposed metal surfaces will be attached to our metal frame. The frame will be constructed with metal surfaces flush against each other. The frame will be grounded to the aircraft. Figure 6.1 shows a schematic of our electrical setup.

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Figure 6.1 – Schematic of Major Electrical Components

6.1 Load Tables:Power Source Details

Name 115 VAC from AircraftOutput Voltage 115 VACWire Gauge 14 AWGRated Output Current 15 Amp

Load DetailsLoad Nominal Current Draw Maximum Current Draw Wire GaugePump 1.1 Amp 1.1 Amp 18 AWGPower Supply 0.5 Amp 1.6 Amp 18 AWGCamera1 <100mA <100mA 18 AWGCamera2 <100mA <100mA 18 AWGTotal Load 2.7 Amp

The highest power electrical circuit used will be the 115 VAC circuit. This will directly power our pump, 24V power supply, and the cameras used for data acquisition (via their included DC supplies). A single power cord will connect the 115 VAC circuit to the aircraft power. The power strip is equipped with a 15A circuit breaker and a switch. The breaker will provide current limiting for the circuit and the switch will serve as the master “kill switch” for the 115 VAC and 24 VDC circuits.

Power Source DetailsName Valve Power SupplyOutput Voltage 24VDCWire Gauge 18 AWGRated Output Current 6.25A

Load DetailsLoad Nominal Current Draw Maximum Current Draw Wire GaugeMain Valve #1 0 Amp 1 Amp 18 AWGMain Valve #2 0 Amp 1 Amp 18 AWGTotal Load 2 Amp

The 24 VDC circuit will be powered by an Astrodyne MKS150-24 power supply. This supply is rated to supply 6.25 A at 24 VDC. We expect to see a maximum draw of no more than 2 A from this supply. Kill switch functionality will be provided by the power strip, as mentioned above. The supply may also be independently switched off if desired. This supply has the capability to self-limit current. 3A fuses will also be installed inline with the valves to guard against short-circuit conditions. The power supply is also self-current limiting.

Power Source Details

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Name Accelerometer PowerOutput Voltage 9VDCWire Gauge 24 AWGRated Output Current 1 A

Load DetailsLoad Nominal Current Draw Maximum Current Draw Wire GaugeAccelerometer 200 mA 200 mA 24 AWGTotal Load 200 mA

The accelerometer is used to measure accelerations in flight will be powered by a dedicated 9V battery. It will be electrically isolated from the remainder of the experiment. A separate power switch is used to disable this circuit. The timing circuit is also powered via an independent battery source. It also is equipped with a kill switch.

Power Source DetailsName Control Circuit PowerOutput Voltage 9VDCWire Gauge 24 AWGRated Output Current 1 A

Load DetailsLoad Nominal Current Draw Maximum Current Draw Wire Gauge555 IC Timer Circuit 200mA 200mA 24 AWGTotal Load 200 mA

6.2 Stored Energy:We will not be using any devices to store or create large electrical charges other than those included within our power supply.

6.3 Electrical Kill Switch:The main experiment power is all routed through a single power switch. Turning this switch off disables the experiment and cuts it off from all high voltage sources. Our emergency shutdown procedure is to turn off the main power at this switch. If necessary, we will then proceed to disable our timer and accelerometer electronics and our data acquisition cameras using their power switches after waiting for the power indicator LED on our power supply to go out.

6.4 Loss of Electrical Power:Upon loss of power, the experiment will cease operation. The pump will stop, removing the pressure head, which drives our droplet generators. The solenoid valves will remain in their closed positions. If left on, the timing circuit and the accelerometer circuit will continue to operate normally without affecting the rest of the experiment. If turned off they will simply cease operating. Our experiment is designed to be in a safe state regardless of power conditions.

7.0 Experiment Procedure Documentation

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7.1 Equipment Shipping to Ellington Field The experiment will be shipped directly to Ellington Field building 993. The experiment will be enclosed in a wood crate, and shipped one day prior to our arrival (March 12, noon). The shipping company is Independent Packing Services, Inc. Prior University of Minnesota Micro-Gravity Teams in previous years have used this company for shipment.

7.2 Ground Operations After unloading the experiment, small parts will be assembled into place and the fluids will be added to the tank. Ground testing will be performed to ensure that the experiment runs properly and that there are no leaks. We request the use of a worktable with an available 115 V, 60Hz electrical outlet.

7.3 LoadingTo load the experiment aboard the KC-135 we will require a lifting palate and a forklift. The experiment will be strapped down to the floor using the 20-inch separation of the floor connection points in the aircraft. The guides on the cage of our experiment will secure the straps.

Figure 7.1: Post-Loading Group Photo aboard NASA’s KC-135A with experiment7.4 Pre-Flight

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Pre-flight procedures will include plugging in the electrical equipment and ensuring the frame is properly fastened to the floor. The surge protector will remain off until proper altitude is reached. There are no preflight requirements other than the 115V, 60Hz electrical outlet.

7.5 Take-off/Landing No power is required during take-off or landing and all electrical systems will remain off during these time periods.

7.6 In-FlightWith our proposed flight conditions of three sets of ten zero gravity parabolas our in flight procedures are as follows. During the transition between sets the nozzle separation distance will be adjusted to the desired distance. During each individual set, droplet size and velocity will be adjusted using the external control knobs of the duty cycle and the pump speed for each individual parabola. The final settings of each parabola are set to test 18 nominal settings that will focus on the transitional regions of coalescence.

7.7 Post-FlightThe first day flight team will inform the remainder of the team of difficulties experienced in flight, if they occurred, and determine means of correction for the following flight day.

7.8 Off-LoadingThe experiment will be off-loaded from the aircraft with a forklift and lifting palate. The same shipping company, Independent Packing Services, Inc, will provide returning shipping. The return will be arranged for the first business day after the completion of our flights, tentatively scheduled for Monday, March 24.

7.9 Data AcquisitionThe droplet collisions were recorded by two Canon ZR-10 digital cameras, one positioned above the collision zone and the other to the side of the tank. Using two cameras allowed us to obtain a complete three-dimensional picture of each collision. Each camera was capable of recording data at the rate of 30 frames per second. During each flight, roughly 70 collisions occurred in micro-gravity conditions. As the video cameras were recording constantly during the flight, and micro-gravity exists for only a fraction of the flight, most of the tape was not of interest. Therefore, the raw video was edited down to contain only the collisions that occurred in micro-gravity. Each of these bits of video was then recorded onto a CD, resulting in a total of four data CDs from the flight (one CD for each camera per day). By using all digital media in the editing process, it was felt that a minimum of data loss occurred.

Once the raw video had been pared down to contain only the portions of interest, it was then possible to begin the process of making measurements of the collisions. To aid in this process, we utilized a computer program called Videopoint 2.5. This software allowed us to view our data frame by frame, and to make measurements of the size and velocity of the droplets in a 2-D plane. By stepping through the data, it then became

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possible to achieve the most accurate measurements that our video would allow. Another strength of using digital media for our data was that it allowed us to effectively use software like Videopoint to make these measurements.

The data from each CD was recorded in a spreadsheet, Appendix B, and consisted of velocity data for each droplet, droplet diameter, the distance between droplet centers at collision, and the result of the collision (bouncing or coalescence). As the cameras only recorded 30 frames per second, often the actual collision of droplets would occur between frames resulting in some inconsistency in making measurements at the time of collision. In these cases, the size of the droplet was generally obtained from the frame just before collision, while the velocity information was taken from the frame following the collision.

After matching up the two views of each collision (horizontal and vertical), the complete three-dimensional velocity vectors for both droplets could be obtained as well as the three-dimensional position of each droplet throughout the collision. This information could then be appropriately manipulated using vector algebra to obtain both the Weber number and the impact parameter for each collision. Once these non-dimensional parameters were obtained for each collision, it becomes possible to generate plots of these parameters and the collision result. A series of Matlab scripts were developed to take the data from the Excel documents, and perform all necessary needed of analysis, which is presented in Appendix A.

Before our flight a series of ground tests and calibrations was done to determine an ideal test procedure that would produce all possible outcomes of the collisions. It was decided that three parameters would be varied during the experiment. These control parameters included adjusting the needle valve setting, the nozzle separation distance and the pulse time of the timing circuit. The first two of these parameters affect the velocity of the droplets, and the third parameter affects the size of the droplets. The impact parameter of the collisions was held relatively constant, due to the laterally fixed nozzle positions, while the Weber Number varied according to the control parameter settings. Results of ground tests indicated 18 different nominal settings, which would produce collisions in all possible outcomes. A test procedure was designed based on the specified flight pattern of three sets of ten parabolas. Since the flight would include more parabolas than our nominal test settings required, it was decided to conduct multiple tests around the transitional stages of coalescence. For analysis purposes, an official ground test was conducted prior to flight in which the flight test procedure was followed. The results of this ground test were compared to both previous experiments conducted in a 1-g environment and to our flight data aboard the KC-135A zero gravity environment.

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8.0 Experimental Analysis

8.1 Ground Test AnalysisIn order to achieve data that could be compared to previous research, the droplet size and velocity of our experiment was initially scaled to test over a region similar to this existing data. Initial ground tests indicated that with a fixed pressure head, the viscous effects between the nozzle and the droplet prevented the scaled droplet from achieving the necessary velocity range. Changing our timing circuit to allow the solenoid valves to stay open a few microseconds longer therefore increased the baseline droplet size. This design change allowed the droplets to reach the specified velocity range, but in doing so, increased the testing range of the Weber Number. For the ground tests, the impact parameter varied slightly with the different nozzle distance settings as a result of the changing velocity vector due to the presence of gravity and, therefore, buoyancy forces. In the nominal testing environment, the absence of gravity allows the impact parameter to remain relatively constant. The results of the official ground tests, which are shown in Figure 8.1, illustrate the carefully calibrated testing procedure. Each of the three collision outcomes – bouncing, coalescence, and separation – were produced under the new design conditions.

Figure 8.1: Ground Test Collision Result

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The experimental results can be reduced to a one-degree-of-freedom problem through the use of the Weber number and the assumption of a relatively fixed impact parameter. The calculated impact parameter for the ground tests varies between 0.09 and 0.84, with uncertainties based on the effects of gravity and human error during data analysis. Figure 8.1 illustrates that distinct boundaries occur between the collision outcomes when graphed as a function of the Weber number. The transition from bouncing to coalescence occurs at a Weber number of approximately 100, whereas the transition from coalescence to separation occurs at a higher value of approximately 225. Qualitatively, the ground test results behaved as expected, following a similar pattern of previous related experiments, such as those conducted by L. Gary Leal (see Figure 2.2). Ground tests were conducted primarily for comparative analysis between the two gravity environments. Given that the ground test procedure produced qualitatively expected results – and all three modes of collision outcomes – the same procedure was defined to be used in flight aboard NASA’s KC-135A ‘Weightless Wonder’.

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8.2 Flight Test AnalysisGround test data and results were used to assure that the experiment and equipment experienced only negligible changes during the shipping process from Minneapolis to Houston and during the flight aboard the KC-135A aircraft. By following the same procedure throughout all of our testing, we were able to conclude that the performance of the pump, timing circuit, and needle valve – the main mechanical components of our experiment – was nominal throughout all data acquisition tests. Although the experiment worked nominally in both ground tests and in-flight tests, some quantitative differences in the data and results were expected due to changes in gravity. In-flight data predictions included slightly lower Weber numbers due to the absence of a downward velocity component, and a slightly smaller range of impact parameters than those calculated as a result of ground tests. It was decided that the changes would be negligible and the experimental procedures would not change. Therefore, the in-flight experiments should produce comparable results, although considering possible changes due to the zero gravity environment. The in-flight experiment results, shown in Figure 8.2, depict the two separate flights under design conditions, aboard the KC-135A zero gravity environment.

Figure 8.2: Flight Test Collision Result

As was found in the ground tests, the results display a distinct boundary between the bouncing and coalescence outcomes, but due to reasons that will be discussed later, the second transition – from coalescence to separation – did not occur in flight. The impact parameter was calculated and averaged for the two zero gravity flights and, as predicted, fell in a smaller range than that of the ground tests. The value was found to vary between

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0.09 and 0.78, with uncertainties due to the effects of human error during data analysis. The transition between bouncing and coalescence occurred at a Weber number of approximately 50, which, as predicted, was lower than in the ground tests. Qualitatively, the results of the in-flight experiments followed a slightly different pattern as the ground tests results, with the absence of the separation collision outcome not expected.

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8.3 Comparative AnalysisUnder the assumptions stated previously, that the experimental hardware functioned identically during the ground and in-flight tests produced the same testing conditions and the affects due to the absence of gravity were negligible, an identical testing procedure verified the repeatability of our experiment. More specifically, these assumptions lead to the conclusion that for each nominal test procedure setting, the Weber number and impact parameter should remain constant throughout the varying gravity environments. By making this comparison, very interesting results were produced. The comparative results between the 1-g and zero-g environments are shown in Figure 8.3, and have two distinct features that will be discussed in detail.

Figure 8.3: Comparative Collision Result

The first and most obvious difference between the ground and in-flight results is the absence of the third collision outcome – separation – in the zero gravity environment. In ground tests, under a ‘normal’ gravity environment, the transition between coalescence and separation occurred at a Weber number of approximately 225. Although a number of collisions were characterized by a Weber number of at least this magnitude during in-flight tests, the transition to separation did not occur. Simply stated, for identical experimental settings – meaning identical collision parameter characteristics – collision outcome differed between the two gravity environments. Second, from this conclusion, it

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follows that the boundary between bouncing and coalescence occurs at a lower Weber number in the zero gravity environment than it does under normal gravity conditions. Ground test results produced a Weber number of approximately 100 for the bouncing – coalescence boundary, whereas in-flight data indicated a shift to a lower Weber number of approximately 50 for this phenomenon to occur. Therefore, coalescence occurs earlier in an environment absent of gravity.

From the previous conclusions, it can further be argued that coalescence occurs for a wider range of the Weber number in a zero gravity environment than under ‘normal’ gravity conditions. As stated earlier, coalescence occurs upon drainage of the secondary film between the two droplets, given that the droplet motion is directed towards one another and a state of sufficient propinquity exists. Figures 8.4.A through 8.4.L, depict a violent collision in the zero gravity environment aboard the KC-135A, which ends in coalescence of the two droplets.

(A) (B) (C)

(D) (E) (F)

(G) (H) (I)

(J) (K) (L)

Figure 8.4: Time Series of Zero Gravity Coalescence

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This same collision (i.e. identical experimental settings and therefore identical collision characteristics) in ‘normal’ gravity conditions produced during ground tests, resulted in separation collision outcome of the two droplets, were the two droplets first coalesced, but their continued momentum caused the droplets to pass through each other. The series of figures show the coalescence transient stabilization over 0.5 seconds. At the beginning of the collision a deformation is noticeable in the droplets from the boundary layer forces during the film drainage stage, Figure 8.4.B. Immediately after the film drainage the droplets begin to coalescence with a transient effect. The continued momentum of the droplets is noticeable in Figure 8.4.D, where the droplets nearly pull through each other, but stay coalesced and continue a transient that is noticeable until the droplet stabilizes in Figure 8.4.L.

It was determined from our analysis and discussions that the wider region of coalescence during our zero gravity in-flight tests aboard the KC-135A was an arguably understandable result. With the focus of the collision outcome on the time dependence of the film drainage, the effects of gravity were analyzed during the coalescence process of droplet approach, film drainage, and droplet coalescence.

During the approach stage in a zero gravity environment, the trajectory of the droplet is defined and held relatively constant from the nozzle exit. The only force acting on the droplet is the drag through the secondary fluid. The drag opposes the motion of the droplet, causing the magnitude of its velocity to slightly decrease, but not affecting the direction. On the other hand, under ‘normal’ gravity conditions, the approach stage is greatly affected by the gravitational force. Due to the horizontal positioning of the nozzles in our experiment, the gravitational force acts orthogonal to the initial trajectory of the droplet at the nozzle exit. The force creates a new downward velocity component, which continues to be accelerated by gravity. Approximating the coefficient of drag on the droplet as that for a sphere, the CD is between 0.5 and 0.7. Considering the size and density of our droplets, the more dominant force on the droplets’ velocity would be the gravitational force. Therefore, the velocity vector direction is continually pulled downward, away from the horizontal, as a result of the gravitational force, and the magnitude of the velocity remains slightly larger than under a zero gravity condition.

The next stage of the collision is the drainage of the secondary fluid. This point in the collision is determined by whether the separation distance of the two droplets is less than the diameter of the droplets, if so the droplets are in the second stage of the collision. The second stage sets up the outcome of the collision. This portion of the collision has a high time dependence. For coalescence to occur all of the secondary fluid between the droplets must drain away, while the droplets are still close and their motion is directed towards one another. Simplified as a two-degree-of–freedom problem, the analysis is only dependent on the film drainage and the droplets relative motion. The dominant factor in how fast the secondary film can drain away is the interfacial surface tension between the two fluids. This is a fixed fluid property, which is not effected by the absence of gravity. The second criterion was that the droplet motion was still directed towards one another. In the case of an environment with gravity, the direction of the

27

velocity vector is continually changing due to gravity, and with the addition of boundary layer forces, as the droplets collide the motion of the droplets are less stable and more susceptible to be forced away from each other than in an environment absent of gravity. Additionally, the velocity magnitude of the droplets is larger in a ‘normal’ gravity environment, therefore allowing less time for the secondary fluid to drain.

The third stage of the collision is coalescence, which was defined earlier as occurring under a time dependence reaction with two simultaneously needed collision properties. The analysis shows that the absence of gravity favors coalescence. The dominant force acting on the collision is no longer gravity, allowing for a more stable drainage that promotes coalescence. Also, the zero gravity environment aboard the KC-135 allows for a slightly longer film drainage time than on the ground. The absence of gravity in our data shows a more wide range of coalescence during the in-flight zero gravity environment tests compared to the ‘normal’ gravity environment tests preformed on the ground before our flight.

9.0 ConclusionsThe data obtained aboard the KC-135A aircraft shows the dependability of the gravitational force on coalescence. The analysis and results indicate that the absence of gravity does favor coalescence. With the dominant force no longer being gravity, the collisions have fewer disturbances causing an increased stability that promotes the coalescence of the two droplets. Therefore, in a zero gravity environment coalescence occurs over a more wide range of Weber numbers. Moreover, the data obtained and analysis of the fluid dynamic properties during the each stage of the collision validates the result of the experiment.

The conclusions made, like most conclusions, included certain accepted assumptions. The primary assumption made was that the effect on the droplets trajectory due to gravity is negligible was an adequate assumption. The zero gravity environment aboard the KC-135A did in fact produce a slightly smaller range of impact parameters, but was not an issue to the results. The Weber number was also affected due to gravity as predicted. The zero gravity environment produced lower Weber numbers due to the absence of gravity’s acceleration. Although the range of Weber numbers was smaller, it remained higher than the transitional boundary between coalescence and separation for the ‘normal’ gravity ground tests. Ideally, the third collision outcome – separation - was desired during the in-flight test for comparative reasons, but the results were still adequate for the conclusions.

Additionally, experimentation includes uncertainty that is minimized to assure the accuracy of results. For the analysis preformed on each collision human error and decision were the main areas of uncertainty. The analysis process begins with data acquisition from the fixed digital cameras aside and above the collision region. The cameras obtained video at a rate of 30 frames a second. The collision properties were determined using a video analysis program, Videopoint 2.5, to obtain size, position, and velocity of the droplets at their collision to determine the Weber number and impact parameter. Considering the rate of the collision process and the speed the camera, the

28

analysis technique using Videopoint included uncertainties due to an inadequate number collision frames to determine the droplets properties. For more accurate analysis in later tests the use of a high speed, 100 frames per second, camera would be a valuable modification to the analysis process.

The data shows obvious shifts in transitional boundaries of coalescence between the ‘normal’ and zero gravity environments. In a zero gravity environment the low transitional stage between bouncing and coalescence was decreased to a smaller Weber number. The high transitional stage between coalescence and reflexive separation increased past our experimental procedures causing the third collision outcome – reflexive separation – never to occur at the higher Weber numbers of our test procedures. The shifts in transitional boundaries directly show the increased region of coalescence. The analysis of the fluid dynamic properties of each stage of a collision also supports the conclusions. The presence of a gravitational force creates a less stable collision. Gravity affects the impact parameter to vary over a larger range due to the continually changing direction of the droplets, which causes instability during the film drainage stage of a collision. The tests performed aboard NASA’s KC-135A aircraft indicate that an environment absent of a gravitational force promotes stable collisions, therefore favoring a wider region of coalescence.

10.0 Outreach Program

10.1 Science Museum of MinnesotaThe semester before our team flew we had a unique opportunity to talk with Science Museum coordinators from all across the country. After being granted special permission from NASA to talk about our experiment before we were accepted to the Reduced Gravity Program, we spent several hours at a conference hosted by the Science Museum of Minnesota. We were asked to present our experiment to the group and answer questions about it; however, the main focus of our presence was for the curators to brainstorm and present possible ways they could incorporate a project such as ours into their museum. With the diverse age, ethnicity, and education of the population that visit museums, the desire was to find was to reach every person interested in learning about the experiment. It proved to be a learning experience for us as well as for the attendees as we were given a number of possibilities of thing we could do during our outreach.

10.2 Local SchoolsThe team spent an afternoon talking with 8th and 3rd graders at St. Pascal’s School in St. Paul, Minnesota. We spent time explaining what NASA was and what they did, as well as about the Reduced Gravity Program. We talked about the effects of weightlessness and the necessity for our experiment to be performed under such conditions. Having the flight footage and “B-roll” allowed us to easily explain about the Weightless Wonder: its maneuvers, the layout of the inside, how the experiments were secured, and any other questions the students had. Questions from the students ranged anywhere from “How did it feel to be floating?” to the ever popular “Did you throw up?”, and even on about becoming an astronaut. It was a great opportunity for us to explain that a person does not necessarily have to be an engineer to work at NASA. We mentioned that many of the

29

astronauts had degrees in areas such as Biology or Physiology. We also stated that programs such as ours that were specifically geared toward students were a great starting point for getting to understand how NASA functions and learning if eventually working for or with NASA was something they wanted to do. Finally, we mentioned that although it was not always fun and games as we had to adhere to strict rules while in Houston, it was an unbelievable experience being able to work with such professionals and all our hard work and dedication to the experiment made it a smooth ride and allowed us to have fun!

Our visit to the school was reported in the school newsletter, which gets sent home with all the students, courtesy of Mrs. Christine Steigauf and Mrs. Joan Hauri, the teachers who allowed us to speak to their classes. Pictures and a copy of the newsletter are in Appendix C.

Similarly on May 13th Nathan, Richard, and Matt spent the entire day talking to the Physics classes of Mr. Jack Samuell at Nathan’s former school, John Marshall High in Rochester. They spent the day telling the classes about the Microgravity Program and their experiences at NASA Houston. Specifically they talked about the application process to the program, brainstorming and building our experiment, testing, and eventually how the experiment working during flight. They also explained how the reduced gravity environment is produced aboard the Weightless Wonder. As our team members were talking to classes composed mainly of juniors and seniors they emphasized the availability of programs, such as the Reduced Gravity program, that are available for undergraduate participation and research. During the visit KTTC Channel 10 news did a follow up story on our team, specifically interviewing their hometown “star” Nathan and shooting some footage of the guys talking to the students.

10.3 Local PressMaria was asked by her employer at B.F. Goodrich to give a luncheon presentation about the experiment and her experience at NASA to her fellow co-workers.

One of our local news stations, WCCO channel 4, sent reporter Bill Hudson to follow our progress as we constructed, tested, and refined our experiments for the trip to Houston. Unfortunately, he was unable to escort us to JSC as he was deployed overseas to follow the war. He did send us with video cameras to record our experience and questions to answer for a follow up story once he returned.

KTTC Channel 10 news station from came and interviewed Nathan and the rest of the team as we were preparing to ship the experiment.

10.4 Flyer’s Hometown PressNic was featured on the front page of his hometown newspaper the Verona Press. He answered a series of emails from the writer who then incorporated Nic’s responses into his article. The complete article can be found in Appendix C.

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11.0 BibliographyAshgriz N., J.Y. Poo. “Coalescence and separation in binary collisions of liquid drops.” Journal of Fluid Mechanics 221 (1990): 183-204.

Bjelogrlic N., P. Boigenzahn, S. Salber, S. Williams, and B. Crook. “Study of Pinch-Off of Liquid-Liquid Flows in Micro- and Macro-Gravity Conditions.” (2001).

Dhainaut M., and S.T. Johansen. “Literature Study on Observations and Experiments on Coalescence and Breakup of Bubbles and Drops.” SINTEF Report 24 (2002): 1-64.

Leal L.G., D.J. Pine, and Y.T. Hu. "Drop deformation, breakup, and coalescence with compatibilizer.” Physics of Fluids 12.3 (2000): 484-486.

Leal, L.G., Y.T. Hu, C. Park, and H. Yang. "The coalescence of two equal-sized drops in a two-dimensional linear flow." Physics of Fluids 3.5 (2001): 1087-1106.

Longmire E.K., T.L. Norman, and D.L. Gefroh. "Dynamics of Pinch-off in Liquid/Liquid Jets with Surface Tension.” International Journal of Multiphase Flow 27.10 (2001): 1735-1752.

Skelland A.H.P., and C.L. Caenepeel. “Effects of surface Active Agents on Mass Transfer During Droplet Formation, Fall and Coalescence.” AIChE Journal 18.6 (1972): 1154-1163.

UNISTRUT Northern, “General Engineering Catalog.” North American Edition 12 (2000).

Webster D.R., and E.K. Longmire. "Jet Pinch-off and Drop Formation in Immiscible Liquid/Liquid Systems." Experiments in Fluids 30 (2001): 47-56.N., P. Boigenzahn, S. Salber, S. Williams, and B. Crook. “Study of Pinch-Off

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APPENDICIES

32

Appendix A: Matlab ScriptsMAIN SCRIPT (analyze.m), which calls additional, functions for complete analysis.

%just a quick little script to call the desired functions and output pretty pictures.if exist('figures','dir') ==0 mkdir('figures')end%picture function outputs nicely formatted png images to the figures directory%using exportfig.m with preset options

figure(1)[Weber1,impact1,status1]=dropletprops('day1vert','day1hor');plotresults(Weber1,impact1,status1);picture('figures\day1')figure(2)[Weber2,impact2,status2]=dropletprops('day2vert','day2hor');plotresults(Weber2,impact2,status2);picture('figures\day2')figure(3)[Weberg,impactg,statusg]=dropletprops('groundvert','groundhor');[bounceg, coalesceg, reflexg]=plotresults(Weberg,impactg,statusg);picture('figures\groundtests')figure(4)Weberf=[Weber1;Weber2];impactf=[impact1;impact2];statusf=[status1;status2];[bouncef, coalescef, reflexf]=plotresults(Weberf,impactf,statusf);picture('figures\flightdata')figure(5)compareresults(bouncef, coalescef, reflexf,bounceg, coalesceg, reflexg);picture('figures\comparedresults')

%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%

%function to extract colliding droplet properties from a saved data file,%takes arguments to a vertical and horizontal camera data file, sans their extension .txt%data file is the data fields (collision # through rsult) from spreadsheet cut and pasted into a plain%tab delimited text file.

function [Weber,impact,status]=dropletprops(vertfile,horfile);

%set up constants herescale = 0.000075595; %convert pixels to meters, use .3125 in/105 pxdensity = 1150; %kg/m^3surfacetension = .0143; %N/m

%just text processing stuff to load the files correctlyfile1=cat(2,vertfile,'.txt');file2=cat(2,horfile,'.txt');

%load files into arraysvertfile = load(file1);horfile = load(file2);

%calculate the x, y and z velocites of both drops in the frame of reference of the tank%Z is up, x is to the right on the horizontal camera, y is transverse, arranged in right-handed fashion%with X we use averaging because we have 2 separate data sources for that axisdrop1vx=(-vertfile(:,5)+horfile(:,4))./2;drop1vy=vertfile(:,4);drop1vz=horfile(:,5);

drop2vx=(-vertfile(:,12)+horfile(:,11))./2;drop2vy=vertfile(:,11);drop2vz=horfile(:,12);

%grab the drop diameters also. in this case, both can be averaged,

33

%as the assumption is made that the droplets are reasonably 2 dimensional%when commenting, discovered that this code was obsolete, and was never used% drop1dia1=(vertfile(:,6)+horfile(:,6))./2;% drop1dia2=(vertfile(:,7)+horfile(:,7))./2;% % drop2dia1=(vertfile(:,13)+horfile(:,13))./2;% drop2dia2=(vertfile(:,14)+horfile(:,14))./2;

%convert position calculations to be relative to the first droplet%so that 3 dimensional calculations can be made. Collision properties will be calculated%relative to droplet 1. This was the most straightforward way of equating the position data on%each camera

% y coords in tank coordsvertcamdrop2y=vertfile(:,9)-vertfile(:,2);vertcamdrop1y=vertfile(:,2)-vertfile(:,2);% x coords in tank coordsvertcamdrop2x=-(vertfile(:,10)-vertfile(:,3));vertcamdrop1x=vertfile(:,3)-vertfile(:,3);

%x coords in tank coordshorcamdrop2x=horfile(:,9)-horfile(:,2);horcamdrop1x=horfile(:,2)-horfile(:,2);%z coords in tank coordshorcamdrop2z=horfile(:,10)-horfile(:,3);horcamdrop1z=horfile(:,3)-horfile(:,3);

%since we have 2 sets of diameter measurements for each droplet, these will be averaged%generation of a single "average diameter" value given 2 is left to a function, so that the calculation may be adjusted%for alternate concepts of "diameter" of a non-spherical body may be used easily%individual averageing is done in a function if alternate averaging needed, averaging between cameras done heredrop1diameter = (diameteraverage(vertfile(:,6),vertfile(:,7))+diameteraverage(horfile(:,6),horfile(:,7)))./2;drop2diameter = (diameteraverage(vertfile(:,13),vertfile(:,14))+diameteraverage(horfile(:,13),horfile(:,14)))./2;

%pull in the 2 values of center to center distancecvert = vertfile(:,8);chor = horfile(:,8);

%put the velocity data gathered earlier into nice vector format for convenience.%Convert from pixels to meters as well for obvious reasons like data consistency

U1 = [drop1vx, drop1vy, drop1vz].*scale;U2 = [drop2vx, drop2vy, drop2vz].*scale;

%calculate x, y, z data, recall that the frame of reference is droplet 1 (top, left on the cams)x1=vertcamdrop1x;x2 = (vertcamdrop2x+horcamdrop2x)./2;y1=vertcamdrop1y;y2=vertcamdrop2y;z1=horcamdrop1z;z2=horcamdrop2z;%average c - definately an accurate approximation to first order, and with equipment limitations that is more than good enoughc=(cvert+chor)./2;

%scale our distance measurements and put them into convenient vectorsc=c.*scale;s1=[x1,y1,z1].*scale;s2=[x2,y2,z2].*scale;drop1diameter = drop1diameter.*scale;drop2diameter = drop2diameter.*scale;

%calculate the X value and then get impact parameter from it%valuse for this paramter agree better with past experiments than those of the Weber numberX = getbigX(c,U1,U2,s1,s2);

impact = 2.*X./(drop1diameter+drop2diameter);

34

%weber number range larger than that used in the previous experiments referenced.%interestingWeber = getWeber(drop1diameter,drop2diameter,density,surfacetension,U1,U2);

%generate a vector of the collision results. 0 = bounce, 1 = coalesce, 2 = reflexive separation, -1 = data acquisition error of some sort, anything larger is ignored.%throw in a random large number if unsure of outcome, but expected the other tape has it. Top camera always has a definative yes/no answer, so this works finestatus = min(vertfile(:,15),horfile(:,15));

%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%

%function to run through the intermediate outputs of dropletprops.m and generate plots of outcomes

function [bounce, coalesce, reflex]= plotresults(Weber,impact,status);%run through entire arraynumcollisions = size(Weber,1);%initialize values to keep matlab happynumcoalesce=0;numbounce=0;numreflex=0;reflex = [0,0];bounce = [0,0];coalesce = [0,0];

%run through all values, cleck the value of status and place data into an output matrix accordinglyfor i=1:numcollisions, switch(status(i)) case -1 disp(sprintf('Bad Data/No Data in data row %d',i)) %let user know a set of data was unusable case 0 numbounce = numbounce+1; bounce(numbounce,:)=[Weber(i),impact(i)]; case 1 numcoalesce = numcoalesce+1; coalesce(numcoalesce,:)=[Weber(i),impact(i)]; case 2 numreflex = numreflex+1; reflex(numreflex,:)=[Weber(i),impact(i)]; otherwise disp('Error in Data File') break endend

%just pretty things up in case there are no reflexivesif reflex(1,:) ~= [0,0] plot(bounce(:,1),bounce(:,2),'o',coalesce(:,1),coalesce(:,2),'x',reflex(:,1),reflex(:,2),'^'); legend('Bounce','Coalesce','Reflexive');else plot(bounce(:,1),bounce(:,2),'o',coalesce(:,1),coalesce(:,2),'x'); legend('Bounce','Coalesce');endxlabel('Weber Number')ylabel('Impact Parameter x')

%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%

function D = diameteraverage(short,long)

%functionalize in case we use a different method to average droplet diameters

%D=min(short,long);D = (short+long)./2;

%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%

function X = getbigX(c,U1,U2,s1,s2)

length = size(c,1);

35

U2(2,:);warning offfor i=1:length sintheta(i,1) = sin(acos(dot((U2(i,:)-U1(i,:)),(s1(i,:)-s2(i,:)))./(norm(U2(i,:)-U1(i,:)).*norm(s1(i,:)-s2(i,:)))));endX=c.*sintheta;

%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%

%calculates average weber number given 2 droplet diameters, density, interfacial surface tension, and their velocitiesfunction We = getWeber(d1,d2,rho,sigma,U1,U2);

length = size(d1);d=(d1+d2)./2;

for i=1:length U(i,:)=norm(U2(i,:)-U1(i,:));endU;We = rho*U.*U.*d./sigma;

%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%

function picture(filename)

exportfig(gcf,filename,'format','png', 'width',7, 'fontmode','fixed', 'fontsize',12,'color','cmyk');

%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%

function compareresults(bouncef, coalescef, reflexf,bounceg, coalesceg, reflexg);

plot(bouncef(:,1),bouncef(:,2),'ob',coalescef(:,1),coalescef(:,2),'xb',bounceg(:,1),bounceg(:,2),'og',coalesceg(:,1),coalesceg(:,2),'xg',reflexg(:,1),reflexg(:,2),'g^');legend('Bounce(flight)','Coalesce(flight)','Bounce(ground)','Coalesce(ground)','Reflexive(ground)')xlabel('Weber Number')ylabel('Impact Parameter x')

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Appendix B: Spreadsheets containing Data from video analysis using Videopoint 2.5 software.

Ground Tests: Vertical Camera –Raw Data Taken from videopoint - Units of pixels and pixels/s center to center distance

Vertical camera ground test data 1=coalescence, 0 = bounce

Collision # Top Droplet distance c2c Bottom Droplet Result

X position Y Position X Velocity Y Velocity Dia Short Dia Long X position Y Position X Velocity Y Velocity Dia Short Dia Long

1 793 488 15 -15 156.1 122.1 133.4 768 357 -255 510 152 133 0

2 793 503 4.286 -250.9 149 133.1 156.7 759 350 -23.59 559.3 149.2 131.2 0

3 792 478 -112.5 -585.1 146 123.5 120.8 762 361 -137 743 159 126 0

4 796 473 363.1 -1546 153 250 128.4 756 351 -236.5 994.4 161 239 0

5 797 498 285 -660 762 332 120 1260 332 120 1260 156.3 168 0

6 797 486 45 -1200 170.1 163 152.4 765 337 105 900 181 173 0

7 794 499 15 -3570 180.4 330 180.5 771 320 165 2955 166 325.3 1

8 792 520 -120 -2730 158.2 318 216.8 757 306 -255 2535 154 323 1

9 792 485 -240 -3525 177 198 136.9 769 350 15 3090 172.1 226 1

10 795 482 -114.4 -522.8 151.1 132 126.4 762 360 -206.6 577.1 148 131 0

11 792 493 -21.08 -84.7 147 135 139.7 760 357 85.05 366.7 147.3 132 0

12 792 494 66.83 -501.7 149 133 154.4 760 343 -121.5 80.42 146.1 129 0

13 799 497 81.71 -430.1 158.1 147 150.6 762 351 0.7666 309.6 153.1 145.3 0

14 801 486 420 -1080 165.1 184 148 763 343 -30 1020 169 203 0

15 797 475 230.5 -1299 186.1 158.2 126.5 760 354 -111.8 1362 178.1 180 0

16 793 495 145.7 -1760 193.1 196.1 158.3 761 340 -33.55 1235 176 199 0

17 796 499 79.69 -2004 168 309.1 166.5 762 336 -76.83 1859 176.1 354 0

18 795 476 -226.5 -2728 176 241 134.4 761 346 -129.4 2262 176.4 188.1 1

19 795 472 0 -285 149 114.2 109.6 767 366 -60 735 157.1 107.2 0

20 799 472 61.46 -540.7 144 112.1 107.9 767 369 5.714 356.3 156.1 122.1 0

21 792 472 43.24 -2736 159.1 248 128.9 765 346 115.8 2320 154.2 225 1

22 794 481 -240 -3330 157 241.1 148 760 337 -195 2730 154 237 1

23 803 455 141.6 -2696 172 187 97.95 758 368 -147.9 2333 181.8 168.2 1

24 800 505 405 -3555 166 347.1 181 762 328 -165 3570 159.1 295 2

25 792 497 0 -3855 161 311 182 765 317 105 2910 164 369 2

26 794 500 -60 -4155 166 356.1 189.8 768 312 75 3525 152 338.1 2

27 800 468 175 -429.5 156.2 105 102.5 770 370 79.58 389.9 161.3 104 0

28 796 464 -9.686 -315.1 150.5 107.2 109.2 757 362 -79.55 593.6 152.7 104 0

29 799 467 180 -975 150 108 111.3 762 362 -60 1200 161.1 106.1 0

30 796 469 -27.87 -656.8 153.1 117 113.3 765 360 73.17 1196 156.3 115.4 0

31 797 469 109.6 -3441 148 231 108.8 765 365 76.03 2906 170.2 185 1

32 799 444 142.3 -2334 140.2 212 79.71 767 371 -12.18 1871 156.1 249.1 1

33 795 490 15 -2460 157 225 146.2 760 348 -105 2670 163.2 228 0

34 797 479 159.4 -2632 165.1 247.1 138.5 762 345 -102.9 2971 166 270 1

35 795 487 195 -2310 158 266 146.5 763 344 270 2850 162 317 1

36 794 483 7.143 -3492 162.1 271 144.1 760 343 -646.4 3299 157.4 361.1 1

37 789 495 70.68 -996.3 145.2 103.2 81.32 766 417 -335.9 1607 149.4 88.09 0

38 799 526 120 -1575 115.2 143.3 157.5 766 372 -255 1275 132 135 0

39 788 491 -18.92 -1663 142 95.19 90.61 771 402 134 1779 126 104 0

40 803 532 -45 -2835 139.1 259 175.4 760 362 -45 2610 153.1 247.1 1

41 787 530 45 -3045 144.2 263 178.2 766 353 -60 2640 157 233.3 1

42 0 0 0 0 0 0 0 0 0 0 0 0 0 -1

43 785 538 8.571 -2676 162 255.1 199.3 762 340 -107.6 2695 164 241.4 2

44 789 530 -105 -3090 154.1 305 194 769 337 -30 3000 165 308 2

45 792 549 164.7 -3150 151 305 245.2 759 306 -305.5 2501 151.1 275 2

46 799 484 321.6 -1875 145 101 88.26 769 401 -4.878 1656 141.3 108.1 0

47 795 510 257.2 -2254 144 154 140.5 764 373 -480.3 2568 144.3 149.1 0

48 798 486 180 -1605 144.4 115.5 87.6 770 403 195 1755 154.3 94 0

49 793 501 7.892 -2965 150 260 132.8 766 371 236.5 2512 142.1 219 1

50 800 495 30 -2610 138.4 221.1 111.1 761 391 60 2805 140.5 305.1 1

51 798 470 210 -2985 143.3 250.1 79.85 768 396 255 2250 155.1 312 1

52 788 510 45 -3630 146 328.4 149.6 766 362 -45 2730 157.4 301 1

53 790 496 120 -3855 158 328 116.7 770 381 90 2910 165 331.1 1

54 790 572 -153.7 -3155 145.1 303.1 272.1 766 301 17.87 3150 161.1 291 1

Ground Tests: Horizontal Camera – Raw Data Taken from videopoint - Units of pixels and pixels/s center to center distance Nozzle Dia = 0.3125" inches = 100.0 pixels

Horizontal data from Ground Test (Done by Nic)

1=coalescence, 0 = bounce


37


1 638 44 420 -2250 140 118 144 782 42 -300 -2850 138.1 88.02 0

2 618 96 443.8 -2542 138 104.1 160 804 108 -348.8 -2617 160.3 126 0

3 628 126 510 -2460 122 108.2 148.3 788 132 -810 -2550 134.1 98.18 0

4 630 222 1530 -2790 194.3 140.4 158 788 222 -1740 -2880 182.3 122 0

5 598 212 1350 -2490 130.8 200.2 195 830 210 -2100 -3060 168.2 134 0

6 626 210 1560 -3210 160 136.1 190 816 210 -1860 -3330 154.6 122 0

7 634 280 1770 -1950 144.1 136.2 160.1 810 280 -2610 -2070 154 148 1

8 600 302 2400 -2250 180 142 154.1 770 238 -2940 -2100 156.2 130 1

9 638 252 2400 -2460 168.2 128.1 160 798 254 -2970 -2460 164.6 134 1

10 634 38 305.1 -2514 124.1 102 156.1 790 42 -621 -3052 126 114.4 0

11 616 72 293 -1945 134 94.34 142.1 792 88 -518.9 -2113 124.1 94.34 0

12 636 34 155.1 -2044 130 94 144.3 780 44 -502.4 -2407 136.1 102 0

13 646 54 630.4 -2185 122.1 100 132 778 56 -440.3 -2447 124.1 108 0

14 638 216 1230 -2280 150.3 130 140.1 778 210 -1830 -2700 170.1 134 0

15 668 178 955 -2134 132.1 126.1 145 776 178 -564.9 -2367 148.1 130 0

16 642 216 1322 -2652 158.3 128 156.2 798 224 -1193 -2568 148.2 126 0

17 630 252 2159 -2467 172.6 136.1 164 794 252 -2348 -2477 170 138.1 0

18 598 304 1984 -2234 176.7 144.1 150 834 302 -2430 -2235 142.7 146 1

19 644 212 750 -2310 114 92.09 106.1 790 224 -800 -2610 126 104 0

20 648 120 115.3 -2704 118 102.1 128.2 776 128 -190.9 -2373 126.1 108 0

21 652 320 2360 -1805 160.2 130 144.1 796 316 -2495 -1952 148.2 128 1

22 638 324 2550 -1710 160.3 134.1 151 802 320 -2970 -1890 142.1 134.2 1

23 632 330 2820 -2220 160 158.3 174 806 330 -3720 -2160 154 148 1

24 634 340 3510 -2190 168 140 162 796 338 -3690 -2040 168 144 2

25 650 334 3750 -2040 172 134 176.2 826 342 -2640 -1380 182.1 148.3 2

26 650 350 4170 -2070 188 148.1 162.2 812 342 -4350 -2100 172.1 142.1 2

27 650 234 879.1 -2524 136.1 128 124 774 234 -1588 -2628 154.3 134 0

28 660 198 763 -2104 120.1 110.5 106.7 766 210 -971.8 -2118 134 112.1 0

29 632 260 851 -2227 136.1 128.1 114.3 806 274 -1010 -2263 144.1 116 0

30 612 344 1953 -1607 178.2 138 140.1 816 346 -2209 -1702 182 138.1 0

31 638 328 2310 -1620 162 166 159 800 324 -1950 -1830 166.1 156 1

32 640 322 2850 -2100 160 146.1 156 796 324 -2370 -1920 154 150.2 1

33 652 302 2580 -2238 168 164 132.4 784 312 -3424 -1937 140.1 148 0

34 624 336 4170 -1920 170 142.1 140.1 814 344 -4470 -1800 182 138 1

35 646 322 2490 -1860 200.2 150.7 140 786 320 -2850 -1710 210 126.1 1

36 656 312 1849 -1780 174 156.2 150.2 786 302 -2410 -2056 202 132 1

37 616 326 1650 -2040 134 114.2 120 736 328 -2520 -2370 140 112.1 0

38 614 330 1800 -2220 140 106 116 730 332 -2280 -2280 138 116 0

39 600 336 1221 -1663 124.1 118.1 114 746 342 -1487 -1730 132 124 0

40 596 382 2880 -1410 154.8 130.6 148 754 384 -3570 -1500 166.1 136.1 1

41 604 392 3671 -1430 164 122 160 772 390 -3312 -1443 184 132 1

42 0 0 0 0 0 0 0 0 0 0 0 0 0 -1

43 598 418 2490 -1380 238.7 120.1 161 774 414 -2940 -1320 242 132 2

44 634 364 2760 -1980 254.1 124.1 175 750 364 -2850 -1800 226 138.5 2

45 608 388 2400 -1290 276.2 128.1 173 762 378 -2760 -1530 246 140.1 2

46 610 354 2310 -2160 138.1 126 129 748 354 -2430 -1830 152 122 0

47 610 336 1920 -1890 148 118.3 122 718 332 -2010 -1890 148.1 118 0

48 612 348 2280 -1920 140 128.1 128.4 740 358 -2550 -1770 126 126 0

49 602 356 1920 -1800 212.2 134.1 155 742 348 -2370 -2070 190 132.2 1

50 610 408 2340 -1140 218.3 134 158 749 408 -2520 -1110 210 132.4 1

51 612 358 2198 -1890 138.4 210.2 162 740 354 -2730 -1710 242.4 122 1

52 609 397 2070 -1050 248.7 136 169 741 399 -2400 -1020 242.7 132 1

53 568 400 3330 -1410 278.5 122.3 176 796 396 -3300 -1080 280.5 136 1

54 574 398 3210 -1390 269.4 128.2 175.4 790 397 -3290 -1120 271 129 1

Day #1 Flight Tests: Vertical Camera –Raw Data Taken from videopoint - Units of pixels and pixels/s center to center distanceVertical Data from Day 1

1=coalescence, 0 = bounceCollision # Top Droplet distance c2c Bottom Droplet Result

X position Y Position X Velocity Y Velocity Dia Short Dia Long X position Y Position X Velocity Y Velocity Dia Short Dia Long1 735 445 472.8 -950.2 102 146 94.34 688 364 -266 1033 109.1 120 12 747 453 390 -465 111 142.1 74.03 703 403 240 1515 110.3 122.1 13 740 462 420 -1020 101 137 103.2 686 374 -60 1020 97 115 04 723 467 285 -1200 112 152.3 115.7 698 354 -45 1425 110 123.2 05 740 453 495 -1215 100 154 95.75 700 366 255 1380 115.1 112 16 749 417 465 -2325 105 260 64 692 388 105 1710 101.2 198.4 17 745 430 780 -1350 108.5 230 77.78 690 375 -90 1110 101 166 18 728 456 180 -1440 112.1 231.1 132.9 689 329 -300 1920 108 179 19 732 424 195 -2805 111 308 64.35 687 389 -345 3210 89.05 229 1

38

10 735 419 420 -3555 93.13 275 60 687 383 -90 2445 94 234 111 dead, no video12 730 455 210 -3030 112 265.2 142.4 695 317 75 2175 104 230.1 113 729 438 135 -1095 104.4 133 82.73 692 364 -30 705 103 113 014 737 430 145.9 -557.6 107 117.5 80.71 692 363 -262.3 473.9 105.1 103.2 015 738 428 300 -675 99 188.2 68.68 692 377 -60 1290 90 144 116 737 451 525 -840 105 159 89 692 374 45 1635 117 141 117 721 469 -45 -1815 106 203 139 697 332 60 1620 96 156 118 721 453 -105 -2265 108 195 114.6 689 343 -150 1575 104 146 119 733 474 105 -3000 98 294 134.7 678 351 -240 2730 112 236 120 733 432 45 -2355 106 292 58 686 398 -315 2790 117 211 121 728 426 495 -2130 111 285 66.5 680 380 210 2265 110 214 122 727 460 105 -1470 110 237 90.82 695 375 0 1425 108 248 123 729 455 345 -2355 108 248 69.64 692 396 -285 2580 104 208 124 724 441 210 -2595 91 238 63.41 685 391 -135 1980 85 193 125 731 552 45 -990 124 140 131.6 687 428 -45 1485 107 200 126 720 451 210 -2355 97 252 76.5 687 382 -255 2175 112 201 127 713 475 165 -1470 105 264 141.5 674 339 -285 1170 106 189 128 732 471 165 -2235 101 260 120.7 687 359 -90 1410 99 204 129 723 471 270 -2550 107 244 100 692 377 -15 2100 105 198 130 726 469 180 -1365 101 186 87 692 389 60 1650 102 144 131 724 487 210 -900 110 153 100 687 394 -30 1380 109 124 132 724 476 285 -1665 105 197 128 692 352 180 2310 97 151 133 719 469 135 -1560 119 183 118 692 354 -165 2220 106 140 134 718 440 330 -1950 106 184 73.35 686 374 -255 1875 100 138 135 735 455 15 -1020 111 130 68.78 701 392 30 1305 99 109 136 724 441 135 -1005 98 127 77.6 695 369 -15 1245 98 104 137 717 458 -15 -810 111 145 85 698 375 180 1935 113 106 038 720 444 135 -1515 103 186 72.5 690 378 -360 1860 101 136 139 724 439 255 -1365 103 185 57.7 692 391 -105 1965 106 119 140 719 453 60 -1305 115 197 83.57 689 375 -60 1170 105 145 141 723 490 165 -1455 113 200 177 689 316 -45 2370 108 166 142 724 475 330 -1305 122 194.4 79.38 698 400 90 2700 110 156 143 724 475 165 -2400 114 277 139 687 341 -195 2505 110 223 144 717 453 -30 -2910 103 280 83 695 373 -135 3735 112 253 145 723 444 30 -2460 124 273 100 683 352 -150 2010 105 258 146 721 444 255 -2280 105 280 102 696 345 270 1890 94 213 147 721 403 -75 -2760 112 275 43 686 378 330 2145 110 241 148 721 455 120 -1035 113 136 92.7 689 368 45 1215 110 121 149 715 435 45 -1200 119 141 136 687 334 0 1365 107 122 150 721 425 -165 -810 105 133 48 689 389 -60 1140 108 122 151 726 432 135 -1425 121 177 47 690 402 45 1875 98 132 152 722 476 150 -1200 115 170 132.5 678 351 -525 1590 116 127 053 722 430 30 -1395 112 159 40.4 692 403 -120 2265 113 154 154 726 457 90 -2265 115 188 112.8 697 348 -75 1710 107 169 155 720 474 0 -2355 118 204 135 686 343 -255 2115 128 184 156 720 442 0 -2865 119 187 74.3 690 374 15 2175 115 177 157 721 448 210 -3510 115 199 90.76 692 362 150 3195 126 182 158 715 430 -195 -3225 112 225 54.8 701 377 30 2265 116 195.5 159 720 455 345 -3630 102 210 96 692 363 -270 3330 113 212 160 721 464 240 -2805 113 299 102.6 694 365 450 2670 113 281 161 721 474 -15 -3435 129 216 114.7 692 363 -195 3465 100 311 162 720 437 0 -1080 110 126 40.5 698 403 120 1095 108 113 163 720 441 60 -1695 114 136 58.14 694 389 -60 1050 110 113 164 735 433 360 -1350 120 143 58 696 390 -90 1500 99 101 065 724 462 360 -1635 116 127 111 687 357 30 780 103 103 066 717 483 45 -2250 117 214 133 692 352 0 2625 104 167 167 720 474 120 -2265 119 181 118.8 690 359 270 2190 117 152 168 717 428 -30 -2610 115 214 69 697 362 150 1275 102 178 169 724 430 255 -2745 103 190 50.8 694 389 150 3120 115 188 170 722 455 270 -2940 119 246 98.72 699 359 165 2805 135 241 171 720 464 -15 -3405 96 253 101 694 366 -180 3300 120 225 172 721 425 300 -3030 118 283 49.82 690 386 -15 2640 126 193 1

Day #1 Flight Tests: Horizontal Camera – Raw Data Taken from videopoint - Units of pixels and pixels/s center to center distanceHorizontal Data from Day 1

1=coalescence, 0 = bounceCollision # Left Droplet distance c2c Right Droplet Result

X position Y Position X Velocity Y Velocity Dia Short Dia Long X position Y Position X Velocity Y Velocity Dia Short Dia Long1 576 440 1695 -285 122.1 128 114.3 689 457 -1620 -315 96.9 129.7 12 536 464 1560 60 112.1 176 173.2 708 484 -2820 60 116.3 144.5 13 570 439 1515 -330 120.1 137.5 123.6 687 479 -1200 330 108.7 131.9 04 541 462 1515 -60 108 160 181.5 721 485 -2190 45 112.1 161.2 05 589 456 2115 -270 110.2 139.3 106.4 694 473 -1965 135 103.1 123.6 16 575 433 2055 -465 96.42 192 95.13 668 453 -2550 -360 110.9 143.3 17 508 468 2055 165 90.05 267.1 247.2 755 479 -3555 45 105.2 203.5 18 530 468 2850 -60 93.05 246.3 241.4 771 482 -2895 -180 105.4 209.7 19 598 462 3375 -150 137.1 308 102.2 700 468 -4260 -510 101.4 241.3 1

10 595 463 3165 0 107 290 91.24 685 478 -3795 -45 108.2 355.3 111 NODATA12 534 459 3975 -270 99 339.1 244.3 778 471 -3465 -285 90.02 278.2 113 591 455 1530 -30 110.7 128.6 99.46 689 472 -1425 -270 108.9 116 014 599 459 855 0 94.56 110.5 92.66 687 488 -855 90 105.9 107.5 015 586 459 645 -225 107 133.8 77.28 662 473 -2655 -135 121.2 122.8 116 582 463 1740 -45 131 134 95.34 675 484 -2295 225 116.5 128.3 117 505 462 1605 -90 98.05 250.2 261.4 766 476 -3375 -225 108.1 212.7 118 540 460 2190 -180 107 218.2 204.4 743 484 -2520 180 108.3 201 119 552 462 2265 -180 92.05 270 151.3 703 471 -3330 -285 93.19 258.4 120 557 452 2955 -330 90 270.1 131.2 688 460 -3225 -405 105 256.4 121 569 453 2595 -315 102 302 142.3 711 462 -1815 -300 104.2 270.3 1

39

22 531 449 2940 -285 99 299 203.5 734 463 -2400 -225 96.13 296.2 123 524 463 1920 0 96.05 278.4 163.7 687 478 -2820 180 102.3 259.1 124 464 456 3330 -405 96 339.1 305.5 769 473 -4140 -135 102.2 302.9 125 456 465 1740 120 143.1 154.7 169.2 624 485 -2160 45 113.3 224.5 126 530 459 1305 -240 95 249 142.3 672 468 -2835 -375 99.05 253.8 127 508 466 3090 -135 96.05 325 229.7 737 484 -2610 45 104.4 284.3 128 482 465 2355 -60 108.3 344 250.2 732 476 -3435 -135 108.1 336.4 129 531 468 1440 -120 101 299 177.3 708 479 -2670 -90 102 278.2 130 544 459 1770 -150 110.4 169.2 117.7 660 479 -3150 150 108.2 160.3 131 521 449 990 -210 131.9 143.3 152.1 666 495 -1455 300 114.8 140.9 132 539 436 2535 -375 107.6 215.7 166.2 704 456 -1860 -195 105.4 196.5 133 552 471 2430 -60 108.1 206.5 162.6 714 485 -2025 135 110.2 175.2 134 578 453 2010 -360 107.4 136.3 99.64 676 471 -1920 30 117.5 133 135 573 410 1305 -765 105.3 140.6 87.32 658 430 -1830 -465 101.4 114.8 136 586 459 2115 -180 116.5 125 90.24 674 479 -2145 0 105.6 116.7 137 568 462 1590 -135 119.3 137.6 116.7 681 491 -1920 315 111.1 119.5 038 576 457 1785 -225 111.5 134.5 93.77 669 469 -3000 -135 116.3 134.1 139 520 462 2640 -180 99 229.2 220.7 740 479 -2895 90 102.2 186.8 140 556 459 1800 -105 107.2 220.7 168 724 462 -2085 -465 108.2 218.1 141 528 456 2730 -150 107 241.3 224.9 752 476 -2400 -315 105.2 189.8 142 570 462 2220 0 112.3 196.2 112.3 681 479 -2610 0 108.1 161.2 143 505 466 2775 -180 105.1 320 259 764 469 -3105 -180 108.7 316.1 144 514 462 2490 -15 98.18 313.1 247.2 761 471 -3810 -165 99.98 291.3 145 543 459 2775 -465 113 334 223.2 766 468 -2625 -240 93.19 299.3 146 546 455 2880 -375 102.2 296 194.7 740 472 -3495 -45 102.4 280.3 147 573 457 2685 -270 105.6 267 177.2 750 466 -2280 -90 91.08 226.5 148 579 426 2115 -525 129.1 129.7 109.8 687 446 -2070 -210 115.3 148.1 149 594 462 1215 -15 97.29 128.5 81.74 675 473 -1800 -180 109.8 118.2 150 607 456 1905 -315 104 163.2 206.3 674 471 -1935 -60 108.4 154.4 151 576 463 1695 -225 108.1 195.1 221 634 481 -2310 450 93.43 189.3 152 531 471 2070 -150 102 183.2 198.3 729 482 -2610 45 96.05 171.9 053 572 456 1470 -255 110.7 113 88.28 659 471 -2250 15 97.02 110.1 154 515 468 2115 -165 105 230 230 745 471 -2430 -150 93.34 235.4 155 496 471 2520 75 93 244 241.1 737 479 -3525 -90 96.05 238.8 156 546 466 2835 -225 107 235 165.4 711 478 -3195 -90 98.18 220.5 157 572 468 3090 -150 105 197.6 133.2 705 476 -2925 -180 99.18 169.4 158 579 462 2775 -300 99.18 206.1 108 687 465 -3045 -285 96.33 198.2 159 NODATA60 533 456 3525 -240 113.5 278.1 209.2 742 465 -3120 -195 93.19 279.3 161 570 462 3240 -210 98.02 223.1 117.3 687 471 -3855 -285 105 250.4 162 588 462 1365 -240 104.2 160.3 183.1 646 471 -1500 -195 93.19 136.4 163 595 465 1605 -150 91.24 113.2 56.09 650 476 -1920 -270 82.76 96.75 164 541 466 2295 -270 107 148.3 178.4 719 478 -2355 180 105.1 139.4 065 572 466 1785 -315 110.2 131.1 125.9 697 481 -1920 135 102.4 138.5 066 521 471 3615 -60 90 232 227 748 471 -2520 30 93.13 267.4 167 527 468 2670 -300 99 192.1 192.3 719 479 -3870 210 93.13 224.4 168 547 471 2595 -195 102 212.1 157.1 704 476 -3315 -180 90.2 197.2 169 569 468 2175 -210 105 162.2 116 685 471 -2265 -450 99.05 163.4 170 562 465 3135 -210 96.05 224.3 136.1 698 471 -2850 120 99.05 209.2 171 565 465 4035 -255 102 215.2 148 713 468 -3525 60 99 230 172 557 465 3375 -330 101 238 160 717 468 -3270 -300 96.05 223.1 1

Day #2 Flight Tests: Vertical Camera –Raw Data Taken from videopoint - Units of pixels and pixels/s center to center distance Nozzle Dia = 0.3125" inches = 104.1 pixels

Vertical Data from Day 2 (Done by Nic)




1 720 462 210 -840 108 112.1 79.4 668 402 -360 840 100 110.2 1

2 726 458 270 -930 114 142.2 79.65 676 396 0 1050 102.2 114.1 1

3 722 444 300 -1170 109.2 126 80.92 670 382 -390 930 106.2 120.1 1

4 712 462 0 -1140 110.5 106 91.76 680 376 60 1110 120.1 102.3 1

5 716 468 90 -930 106.3 97.69 93.23 680 382 0 1140 106.3 97.69 0

6 710 460 180 -1080 122.3 120 112.1 680 352 30 1050 122.1 106 1

7 706 480 0 -1260 118.1 188.1 119 672 366 -120 1080 108.7 160.2 1

8 712 490 30 -1380 106.3 194.1 151.4 672 344 -240 1860 110.2 188 1

9 722 446 270 -750 124 106 86.83 680 370 -210 630 118.3 114 1

10 716 446 90 -450 118.1 102 92.13 674 364 -60 720 112 100.1 0

11 716 430 31.46 -287.9 124.1 106 80.99 672 362 -430.2 565.1 108 94.02 0

12 718 442 150 -630 114 100 102.5 682 346 60 510 110 104 0

13 722 482 480 -1350 108 234.1 130 656 370 -660 1230 96.02 230 1

14 712 502 90 -1890 98.18 256 163.5 670 344 -330 1830 100.1 228 1

15 726 488 600 -1170 112 236 151.3 652 356 -720 1650 104.2 208.1 1

16 720 502 360 -1110 110 242.1 160.5 658 354 -570 1170 90.02 204.2 1

17 708 504 270 -1920 104.1 238.2 179.6 672 328 -120 2220 94.34 190 1

18 708 510 210 -1320 102 246 166.7 672 316 -360 1560 100 206 1

19 718 442 -60 -180 102.2 94 84.31 686 364 60 180 94.02 86 0

20 712 458 300 -2160 116 158.1 108.8 674 356 -300 1410 100 118.1 1

21 702 460 -120 -1320 110.2 134.2 105.8 674 358 -60 960 114 128.2 0

22 712 476 300 -1110 104 166 109.8 682 324 -210 1380 106 156.1 1

23 704 462 90 -1260 116.1 124 110.1 668 358 -300 1170 114.4 116 1

24 704 484 0 -2370 122 250 170.3 674 296 -90 2130 100.2 208 1

40

25 708 472 30 -1950 94 216.1 123.2 680 352 60 1980 96.08 190 1

26 702 460 -240 -2550 96.19 230.1 132.2 678 330 -60 2130 100.2 216 1

27 collision did not exist in file

28 712 466 0 -1770 98.33 232 115.9 682 354 -60 1950 90.8 216 1

29 710 462 30 -2310 98 238.1 135.5 690 328 150 1950 90 198 1

30 718 456 74.32 -323.4 94.19 98 91.39 682 372 -141.5 317.7 88.02 86 0

31 716 440 0 -600 94.02 90.2 75.15 684 372 -90 510 82.1 72 0

32 722 454 240 -1260 96.02 154.1 101 666 370 -270 1350 92.2 128.1 1

33 706 460 180 -1470 98.02 190 113.5 678 350 -180 1320 96.02 156 1

34 710 464 240 -1770 102 184.1 103.1 678 366 90 1620 92 156.1 1

35 716 458 90 -1410 100 168.2 112.9 672 354 -150 1530 102.1 152.1 1

36 704 464 30 -1860 106.2 140 114.6 672 354 -180 1110 106.2 112.2 1

37 718 468 210 -900 90 100 85.44 672 396 -30 990 80.02 90.09 0

38 708 462 30 -960 94.09 88 86.65 680 380 90 900 88 82 0

39 712 468 150 -930 98.08 110 86.4 676 398 -30 1020 80 88.02 0

40 710 462 60 -1080 102 114.3 80.99 682 386 30 1110 88.02 104 0

41 714 442 90 -750 94.09 90.02 82.65 672 398 -60 600 82.02 86.09 0

42 698 480 -60 -2370 112 178 136.5 672 346 -30 2160 112.2 168 1

43 706 474 60 -1710 110 176 125.3 664 356 -480 1920 108.1 156.1 1

44 702 494 -60 -3510 108 206 158.5 674 338 -150 3270 106.1 168 1

45 706 494 240 -2490 112.1 202 170.3 678 326 60 2310 100 208 1

46 706 540 120 -2490 106.2 214.1 165.4 678 320 60 2760 94.09 194 1

47 706 500 150 -3030 118.1 212.2 162.8 674 320 90 3240 102 236 1

48 706 498 330 -2970 106.2 240.1 150.6 678 350 90 3540 100.3 276 1

49 704 476 0 -1920 108 172.3 110.2 682 368 300 1620 110.5 158 1

50 698 486 -90 -3150 100.3 158 125.2 674 348 -180 3000 106.1 132.1 1

51 706 496 240 -3330 100.3 174.1 132.1 680 354 210 3360 110 162.1 1

52 706 474 210 -2340 122 182 126.6 672 352 -60 2220 124.1 186 1

Day #2 Flight Tests: Horizontal Camera – Raw Data Taken from videopoint - Units of pixels and pixels/s center to center distance Nozzle Dia = 0.3125" inches = 104.0 pixels

Horizontal Data from Day 2 (Done by Nic for Maria)



X position Y Position X Velocity Y Velocity Dia Short DiaLong X position Y Position X Velocity Y Velocity DiaShort Dia Long

1 664 460 900 -60 98.02 156 102 822 462 -1740 -30 112 150.2 1

2 692 468 1020 -90 102.2 154.1 99.3 790 484 -2010 30 90.2 152 1

3 687 465 920 30 109.2 123 80.92 812 456 -1050 -30 106.2 120.1 1

4 677 466 1100 0 110.5 111 91.76 820 440 -1140 -60 120.1 102.3 1

5 679 467 1140 -30 106.3 98.4 93.23 820 454 -930 90 106.3 97.69 0

6 669 468 1040 -60 122.3 123 112.1 800 460 -1080 0 122.1 106 1

7 660 470 1040 90 118.1 202.1 119 798 464 -1260 30 108.7 160.2 1

8 659 461 1670 0 106.3 194.3 151.4 795 458 -1380 -30 110.2 188 1

9 678 462 650 30 124 104 86.83 814 464 -750 0 118.3 114 1

10 675 464 720 -30 116 110 92.13 812 468 -450 -90 112 100.1 0

11 673 465 570 0 124.1 98 80.99 816 462 -287.9 60 108 94.02 0

12 672 466 530 -90 114 108 102.5 821 468 -630 30 110 104 0

13 674 466 1210 60 108 230.2 130 807 462 -1350 0 96.02 230 1

14 685 469 1740 30 98.18 246 163.5 815 502 -1890 -60 100.1 228 1

15 687 461 1565 0 112 236 151.3 806 488 -1170 -60 104.2 208.1 1

16 681 459 1200 -60 110 242.1 160.5 802 502 -1110 -90 90.02 204.2 1

17 680 460 2120 -60 104.1 238.2 179.6 793 504 -1920 0 94.34 190 1

18 683 462 1720 -90 102 246 166.7 826 510 -1320 -30 100 206 1

19 666 463 210 0 102.2 94 84.31 824 442 -180 30 94.02 86 0

20 654 462 1380 -30 116 158.1 108.8 814 458 -2160 -90 100 118.1 1

21 676 461 950 30 110.2 134.2 105.8 805 460 -1320 60 114 128.2 0

22 678 462 1260 60 104 166 109.8 809 476 -1110 30 106 156.1 1

23 679 464 1200 60 116.1 134 110.1 808 462 -1260 0 114.4 116 1

24 672 464 1980 90 122 250 170.3 818 484 -2370 -60 100.2 208 1

25 690 461 1890 90 94 216.1 123.2 814 472 -1950 -60 96.08 190 1

26 690 462 2010 0 96.19 230.1 132.2 816 460 -2550 -90 100.2 216 1

27 did not analyze - so data would match

28 692 461 1950 -60 98.33 232 115.9 809 466 -1770 0 90.8 216 1

29 698 466 1920 -60 98 238.1 135.5 808 462 -2310 -90 90 198 1

30 697 467 320 90 94.19 98 91.39 818 444 -323.4 -30 88.02 86 0

31 698 468 500 -90 94.02 90.2 75.15 814 462 -600 0 82.1 72 0

41

32 691 467 1290 -30 96.02 154.1 101 815 468 -1260 30 92.2 128.1 1

33 677 468 1320 0 98.02 190 113.5 821 460 -1470 -30 96.02 156 1

34 685 470 1620 30 102 184.1 103.1 807 480 -1770 60 92 156.1 1

35 678 473 1590 -30 100 168.2 112.9 815 490 -1410 -60 102.1 152.1 1

36 687 469 1400 60 106.2 140 114.6 806 446 -1860 -90 106.2 112.2 1

37 694 461 900 -60 90 100 85.44 802 446 -900 30 80.02 90.09 0

38 689 465 930 -90 94.09 88 86.65 793 430 -960 60 88 82 0

39 678 465 1120 0 98.08 110 86.4 812 442 -930 -30 80 88.02 0

40 675 467 1030 0 102 114.3 80.99 813 482 -1080 -60 88.02 104 0

41 673 468 590 90 94.09 90.02 82.65 817 442 -750 90 82.02 86.09 0

42 683 462 2090 30 112 178 136.5 810 480 -2370 -30 112.2 168 1

43 681 462 1940 -30 110 176 125.3 812 474 -1710 0 108.1 156.1 1

44 680 461 3100 -60 108 206 158.5 807 494 -3510 0 106.1 168 1

45 667 464 2600 -60 112.1 202 170.3 815 494 -2490 90 100 208 1

46 689 464 2760 90 106.2 214.1 165.4 809 540 -2490 30 94.09 194 1

47 679 463 3240 90 118.1 212.2 162.8 818 500 -3030 -30 102 236 1

48 672 469 3340 -60 106.2 240.1 150.6 809 498 -2970 -60 100.3 276 1

49 678 470 1720 -60 108 172.3 110.2 802 476 -1920 -60 110.5 158 1

50 677 472 3070 -30 100.3 158 125.2 805 486 -3150 90 106.1 132.1 1

51 701 462 3240 60 100.3 174.1 132.1 813 496 -3330 90 110 162.1 1

52 671 466 2250 -30 122 182 126.6 810 474 -2340 -60 124.1 186 1

42

Appendix C: Outreach Attachments (Pictures and Articles)

43

Documents

Final Report - Aerospace Engineering · Web viewTopic Area: Fluid Dynamics Department of Aerospace Engineering and Mechanics University of Minnesota 107 Akerman Hall 110 Union Street