MEMORANDUM REPORT

l MR No. 16GlO

AID,m~G CHARACTERISTICS OF Mk. 230, Mk. 237, AND }.1}c. 238 \'

TAIL FUZES AND FLOW STUDY INSIDE TAIL OF AN -M66 BOMB \ '.

By Franklin E. Hest. Jr. \, ~

SUMMARY

N AC A

NATIONAL ADVISORYCOMMITTEEFOR

AERONAUTICS

~f;koLfcd M".~ l,KB,t... 6e",,;c.Y'

NACA LANGLEY MEMORIAL AERONAUTICAL LABORATORY

MEMOnANDUM REPORT

for the

Naval Ordnance Laboratory, Navy Department

MR No. L6G10

Aill·m~G CHARACTERISTICS OF Mk.230, Mk.237, AND Mk.238

, TAIL FUZES A!'Jl) FLOW STUDY INSIDE TAIL OF AN -M66 BOMB

By F::.~anklin E. vlest, Jr.

Tests were made in the Langley l6-foot high-speed tunnelto determine the arming characteristics of three types of bombtail fuzes and to study flow condi tions inside the tail of theAN -M66 bomb.

Mk.230 tail fuzes l'lere tested in the AN-M53, AN-M64, AN-M65,and f>N-M66 bombs. Mk.237 and Mk.238 tail fuzes were tested inthe AN -M64 and Alif -Iv166 bombs , respectively. The lowest testspeed was approximately 80 miles per .hour and the highest wasapproximately 400 miles per hour.

For any airspeed, the variation in arming distance wasfound to be less than 5 percent of the mean arming distance forthe Mk.230 tail fuzes.' For airspeeds of 110 miles per hour ormore, the variation in arming distance was found to be less than8 percent of the mean arming distance for the Mk.237 tail fuzesand less than 6 percent of the mean arming distance for theMk.238 tail fuzes. For, tests of Mk.230 tail fuzes mounted inthe AN-t-166 bbmb the arming distance of theMk.230, mod.ification 5tail fuzes for an angle of attack of -So vlaS found to biOiles8 than the arming distance of the ~fi".230,modification4 tailfuzes for an angle of attack of 00 by an amount thatvarie~ from about 17 percent at 110 miles per hour to about11 percent at 400 mO.les per hour.

Flow studies inside t~e tail of the AN-M66 bomb indicatedthat the optimum location of a tail fuze vane i~ near thetrailing edge of the tail.

}.ffi No. L6G10

INTRODUCTION

The main purpose of the present investigation, which wasmade at the request of the Naval Ordnance Laboratory, was todetermine the arming characteristics of three types of tail fuzeswhen mounted in bombs for which they were specified.

After a bomb with a tail fuze is dropped, the fuze issupposed to maintain the bomb in an Th~armed condition until it hastraveled a specified distance after which time the bomb can be setoff by some mechanism that will actuate the primer. If the fuzedoes not arm at approximately the rigl1t time, the bomb may eithercause destruction of the launching airplane or become a dud. Thus,for bombing at low altitudes the arming time of these tail fuzesmay be critical.

The secondary ptITpose of this investigation was to detel~ine

the flow conditions that existed inside the tail of the AN-M66bomb. The tail fuzes w"ere expected to have a more unfavorablelocation in the AN-M66 than in the·other bombs because due to itslarger size it had a larger ,fake. Hence, it ,vas deemed ofimportance to make a study of the flow conditions that affectedthe rates of rotation of the fuze vanes, and to determine a morefavorable location for a tail fuze va~e~~

These tests were conducted in the Langley l6-foot high-speedtunnel because its large size relative to the bomb sizes wouldmean that the tur..nel ,fall effect on the flow would be slight, andhence would not have much effect on the arming characteristics ofthe tail fuzes. As bomber speeds are expected to increase in thefuture, the use of this tunnel ,Yas also desirable because itcould reach speeds above present bomb launching speeds.

This report presents the results obtained on the armingcharacteristics of the tail fuzes, and on the flow survey insidethe tail of the AN -M66 bomb.

APPARATUS AND METHODS

Tvo modifications of the Mk.230 tail fuze were tested. Theywere modification 4, ,.;hich is shown in figure 1, and modification 5,which is shown in f-igure 2. The exterior details of the twomodifications were the same except that the Mk230, modification 5had a bracket added to hold an arming wire. Although the two

2

MR No. L6G10

modifications had different mech~~isms for detonating a bomb,their arming mechanisms were similar and, therefore, they shouldhave about the same arming characteristics. The vanes for theMk.230 tail fuzes had diameters of 5 inches and their blade angleswere approximately 400 •

Mk.237 and Mk.238 tail fuzes were also tested. Figure 3shows a photograph of· the Mk. 237 tail fuze. The Mk. 237 andMk.238 tail fuzes were similar except that the Mk.238 tail fuzeswere 4 inches longer than the Mk.237 tail fuzes. The vanes forthe Mk.237 and Mk.238 tail fuzes had diameters of 5 inches andtheir blade angles ,vere approximately 45°.

The bombs used in these tests were an AN-M53, 325 pounddepth bomb; an AN -M64, 500 pound bomb; an AN-M65, 1000 poundbomb; and an AN-~166, 2000 pound bomb.

A front view of the AN-M66 bomb mounted in the test sectionis shOwn in figure 4. Figure 5 shows a rear view' of the AN -M66bomb mounted in the test section. This mounting system was used ferall of the bombs. The Ai'1-M64, AN-M65 , and the AN -M66 bombs all hadthe same general shape. These bombs were mock-ups as their bodieswere constructed of white pine to decrease their weights. However,they '"ere identical to actual bombs in all ot.'ler (letails. Figure 6shows a sketch of the side view of the AN-M53, 325-pound depthbomb, which was an actual bomb.

Figure 7 is a photograph of a Mk.230 tail fuze mounted in anAN-M66 bomb and shows where the tail fuzes were mounted in thebombs.

To determine the a.Y'IIl1ng times of the tail fuzes constanttunnel speeds were set and an electric timer was used to measurethe el~pses of time bet'leen the pulling of an arming wire, thatreleased the tail fuze vanes, and the arming of the tail fuzes.

The flow survey ins ide the tail of the AN -M66 bomb was madeby using a pitot-static tube that was mounted on a cantileversurvey strut, which could be noved either horizontally orvertically by electric motors. The pitot-static tube extended14 inches out of the survey strut and could be inserted inside thebomb tail far enought to obtain total and static pressures at thethree different survey planes shown in figure 8.

As the distance between the total tube and the static tubeson the pitot-static tube was 3 inches, the survey planes werespaced 3 inches apart so that while static pressures werebeing measured in one survey plane total pressures could be

3

MR No. L6G10

measured in the preceding survey plane. The position of plane 2was chosen so that it would be between the vane planes of the~230 and Mk~238 tail fuzes. 'rhe d.istance of the three surveyplanes and the vane planes of the Mk230 and Mk.238 tail fuzesfrom the rear of the bomb body were:

Plane 1 9.5 inches

Mk230 vane 11.75 inches

Plane i! 12.5 inches

Mk.238 vane 13.4 inches

Plane 3 16.5 inches

In each one of the survey planes, readings were taken at13 points which were B~aced within a 6-inch squQre, Thelocation of these points are also shown in figure 8.

TESTS

Tests to determine the arming times of the Mk.230,modj.fication 4 tail fuzes whenm€l'unted in the AN-M53, AN-M64,AN -M65, and AN -M66 bombs ..rere made at an angle of attack of 00 •

The 8rm.ing times of -the Mk.230, -modif ication 5 tail fuzes whenmounted in the AN-M66 bomb were determined for an angle ofattack of _80 • 'rhe arming times of the Mk.237 and Mk. ?38 tailfuzes when mounted in the AN-M64 and AN-M66 bombs, respectively,"mre determined at an angle of attack of 00 •

An airspeed range of approximately 80 miles per hour toapproximately 400 miles per hour was covered in the tests todetermine the arffiing characteristics of the tail -fuzes.

- Tests were also made to determine the flo\V conditionsexisting at three survey planes inside the tail of the AN-M66bomb without a tail fuze mounted in the bomb. These flowconditions \Vere determined in each survey plane for free-streamvelocities of approximately 115, 264, and 416 miles per hour.Other tests were made at a free-stream velocity of 263 miles perhour to determine the effect of a Mk.~O, modification 4 tailfuze (Without vane) mounted in the bomb-on the flow conditionsat plane 2.

4

MR No. L6GIO

RESULTS AND DISCUSSION

Arm!~€L<?h~ra9terisj;i~s of tail fuzes. - The amounts of timerequu'ed for the various tail fuzes to arm are given in tables Iand II. C-qrves of the arming distances of the Mk~230, modificat.ion 4tail fuzes when mounteli -in different bombs are shown in figure 9.This figv.re shows that the Mk230, modification 4 tail fuzes armfaster in the AN -M65 bomb than in the .liI~-H~ bomb. The vanes ofthe Mk.2:p, modification 4 tail fuzes protrud.ed 2.2 inches aft ofthe trailing edge of the AN -M64 bomb tail, but on the AN -M65 bombthe vane is. located 2.2 inches ahead of the bomb-tail trailingedge. This indicates that lower velocities existed in.back oft1;J.e AN-M64 ,bomb' tai~ than inside the P.N -M65 bomb' tail.

Figure 9 also shows that the arming distance changes with achange in airspeed. If the- velocity distribution about a fuzevane and the ratio of the velocity in the plane of a fuze vane tofree-stream veloc:tty remained constant at all speeds ~d iffriction and inertia forces were absent, there would be novariation in arming distance with airspeed. However, friction andinertia forces were present in the tail fuzes and the flow surveyinside the tail of the ~.N-M66bomb (see table III) indicated thatthe velocity distribution about a Mk230 tail fuze vane and theratio of the velocity i.n the plane of the Mk.23 0 tail fuze vane tofree-stream velocity ~ did ch~Dge with a change in airspeed.

Figure 10 shows that for tests of the Mk~~30 tail fuzesmounted in the AN-M66 bomb the arming distance for the Mk.23Q,modification 5 tail fuzes for an angle of attack of _8 0 wasless than the arming distance of the Mk.2JO, modification 4 tailfuzes for an angle of attack of 0 0 "by an amount thatvaried from about 17 percent at 110 miles per hour to about11 percent at 400 miles ~er hour. The reason that Mk.230,modification 5 tail fuzes were tested was because there were notenough .Mk.230, modification 4 tail fuzes available for all of thetests. A large number of the Mk.230 tail fuzes could not betested more than once as the gears of their arming mechanismswere often damaged at test speeds of 300 miles per hour or more.Al though modifications 4 and 5 of the Mll'-230 tail fuzes are supposedto have about the same arming characteristics, their armingcharacteristics may differ slightly due to the presence of thebracket for holding an arming wire on the Mk2 30, modification 5tail fuzes.

5

ivffi No. Luno

The d.ata obtained on the ~.1].c~3D tail fuzes showed that for anyairspeed the variation in arming distance was less than 5 percentof the mean arming distance.

. The arming distances of the Mlr.237 and Mk.238 tail fuzes whenmounted in the 'AN-M64 end AN-M66 bombs, respectively, are shown

, in figure :11. Data \-Jere taken for' the Mk.233 tan fuzes for an 'airspeed of approximately 80 miles per hour, but they are notpresented in figure 11 because they ~ere too inconsistent as canbe seen in table II. For aDY airspeed of 110 miles per hour ormore, the variation in a~ing distance was less than 8 percent ofthe mean arming distance for the M1~37 tail fuzes and less than6 percent of the mean ~&ing distance. for the ~~238 tail fuzes.Inspection showed that the friction varied more in the Mk237 andMk.:238 tail fuzes than in the Mk.230 tail fuzes. This is probablythe reason why the Mk237 andMk238 tail fuzes ;vere not as accurateas the Mk~~O tail fuzes.

Figure 11 also shows an effect on the arming distance of the}~~8,tail fuzes of changing,the angle of attack 80 , for anairspeed of 149 miles,' per hour.

:F]..Q~91.ldit.i9JlS insj,IlJL.tail oL~J-M66.J?0m,10. - Table III givesvalues of the ratio of the velocity inside the tail to free­stream velocity vlv, for poin~ts 1 through 13 at planes 1, 2,and 3 (fig. 8). For plane 1 some of the values were omittedbecause the velocities at these points were too low to obtainsatisfactory data, and because data were not obtained forpoints 9 and 10 for V = 420 miles per hour.

Plots that are representative of'the velocity distributionsobtained at planes 1, 2,' and 3 are shown in ~igure 12 for afree-stream velocity of approximately 264 miles per hour.Part (c) or' figUre 12 shows the velocity distribution at plane 2foran ~ifiQ30 tail fuze, without vane, mounted in the bomb. Thepresence of this tail fuze in the bomb changed the flow verylittle. -

The plots also show that the velocity distribution improvesa~d ~~at higher velocities are obtained at the survey planes'further from the bomb body. The results obtained from this flowsurvey seem to indicate that the optimum location for a tailfuze vane would be near the trailing edge of the bomb tail.,

6

NR No. LW10

CONCLUSIONS

Tests to determine the arming characteristics of the tailfuzes and the flow conditiona inside the tail of the AN -M66 bombhave indicated the following concl~sions:

L For any airspeed, the variation in arming distance wasfound to be less than 5 percent of the mean a..1"IJling distance forthe Mk230 tail fuzes.

2. For an airspeed of 110 miles per hour or more, thevariation in arminG distance was found to be less than 8 percentof the mean arming distance for the Mk237 tail fuzes and less than6 percent of the mean arming distance for the Mk238 tail fuzes.

3. For tests of Mk.230 tail fuzes mounted in the AN-M66bomb the arming distance of the Mff~30, modification 5 tailfuzes for an angle of attack of _80 was found to be less thanthe arming distance of the HI<---230, modification 4 tail fuzes foran angle of attack of 00 by en amount that varied from about17 percent at 110 miles per hour to about 11 percent at 400 milesper hour.

4. Flow studies 5nside the tail of the Pl~-M66 bombindicated that the optimum location of a tail fuze vane is nearthe trailing edge of the tail ..

Langley Memorial Aeronautical LaboratoryNational Advisory Committee for Aeronautics

Langley Field, Va.

Franklin E. West, Jr.Aeronautical Engineer

Approved: ;IJ1 l/;;'f{p A L~Ar--'d l r~(/ V'1....-/C/e;eVI

:/,/

}r;rrJohn StackChief of Compressibility Research Division

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7

TABLE I

FUZE 'ARMING TIME

a. ;;: 0°

MR No. L6GIO

Bomb Type of Fuze Arm1ng T1me V(sec.) (mph)

AN-M53 MK230, mod. 4: 2.610 82II " II II 2.580 83II II .. II 2.578 83II II .. II 1.924 III" II II II 1.995 IIIII II .. 1.949 IIIn II " 0.700 253n II II 0.754 253.. n " 0.772 253.. II " 0.529 402

" II II 0.497 400II II n 0.493 400

AN-M64 It II 3.227 81

" .. .. 3.398 81II n II " 3.161 81.. II " II 2.182 112II n " II 2.196 IIIII " II It 2.0g0 112II II " " 1.164 201

" II It II 1.122 202

" II II " 1.048 202II " II II 0.812 301II II II " 0.758 301II MK237 3.732 III" II 4.240 III" II 4.098 IIIII II 2.320 150.. II 2.490 150-II " 2.568 150n II 2.221 150II II 1.805 201

AN-M65 MK230, mod. 4 1.750 110

" " II II 1.718 110II II II .. 1.703 110It· II II " 0.674 256II .. II ,.

0.692 255.. Q " II 0.723 255I II II II .. 0.632 299: II II II II 0.612 300I

" II II • 0.611 300

NATIONAL ADVISORYCOMMITTEE FOR AERONAUTICS

TABLE II

FUZE ARMING TIME

AN-M66 Bomb

MR No. L6GIO

Type or Fuze Arming Time V (l

(sec.) (mph) (deg.)

MK230, mod. 4 3.844 eo 0• " " 3.859 81 0" It II 3.973 81 0• II II 2.672 111 0II " " 2.718 109 0" II II 2.718 111 0

MK230, mod. 5 2.614 111 0MK230, mod. 4 1.420 201 0

II • II 1.421 200 0" • • 1.433 200 0" • II 0.915 300 0II II .. 0.902 300 0" II II 0.882 301 0n II " 0.626 402· 0II .. .. 0.604 402 0II " • 0.628 401 0

MK230) mod. 5 2.254 111 8II " " 2.240 111 8• " • 2.157 111 8" " " 1.172 202 8" " " 1.219 200 8• II II 1.153 200 8• " " 0.560 401 8• II " 0.663 401 8• II II 0.548 399 8

MK238 made one turn 80 0II 6.712 81 0II 10.103 81 0II 4.631 110 0• 4.603 110 0• 4.649 110 0II 2.670 150 0• 2.826 150 0• 2.772 150 0" 1.882 199 0• 2.087 200 0• I 2.062 199 0" 1.593 251 0• 1.570 250 0" 2.332 149 8 . "

" 2.538 149 8

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NATIONAL ADVISORYCOMMITTEE fOR AERONAUTICS

TABLE III

FLOW CONDITIONS INSIDE AI-M66 BOMB TAIL

Plane 1 2 :5

V, mph 116 266 420 114 261 263 411 116 2M 410

Point v/v v/V v/V T/V v/V. v/V· v/V vJV v/V v/Vlooat1on

1 0.544 0.583 0.585 0.629 0.672 0.7~ 0.899 O.71e 0.720 0.7192 0.213 0.292 0.368 0.528 0.525 0.604 0.592 0.575 0.596 0.6593 0.471 0.497 0.532 0.629 0.604 0.594 0.61' 0.585 0.623 0.663 '.4 ----- ---- 0.235 0.369 0.380 0.428 0.4-96 0.509 0.519 0.5865 ......--- ...---- ----- 0.337 0.316 0.366 0.388 0.370 0.433 0.4956 0.394 0.403 0.449 0.665 0.709 0.644 0.781 0.783 0.785 0.8257 ----- . --- 0.301 0.273 0.340 0.413 0.426 0.490--- ---8 0.298 0.366 0.339 0.665 0.672 0.665 0.602 0.684 0.762 0.7489 ----- 0.125 ---- 0.404 0.448 0.386 0.486 0.542 0.562 0.580

10 ----- 0.146 ----- 0.404 0.401 0.429 0.466 0.493 0.514 0.59111 0.622 0.640 0.627 0.162 0.769 0.676 0.754 0.765 0.789 0.76412 0.337 0.369 0.385 0.571 0.566 0.581 0.602 0.649 0.650 0.69713 0.544 0.569 0.585 0.565 0.658 0.707 0.657 0.708 0.729 0.723

• )(230, Mod. 4 tu~e 1n bomb, no vane. NATIONAL ADVISORYCOMMITTEE fOR AERONAUTICS

MR No. L6GIO

Figure 1 Photograph showing Mk230, modification 4 tailfuze.

W~TIOWAL ~DVI80RY COMMITTEE FOR ~EROM~UTIC8

L~WGL.Y ••MO.I~L ~••OM~UTICAL LABORATORY - L~"GL.Y FIELD, V~.

MR No. L6GIO

Figure 2.- Photograph showing Mk230, modification 5 tailfuze.

MR No. L6GIO

Figure 3.- Photograph showing Mk237 tail fuz~.

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Figure 4.- Front view of the AN-M66 2000-pound bomb mounted in the 16-foot 0

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MR No. L6GIO

Figure 7.- Mk230, modification 4 tail fuze mounted in theA~-M66 2000~pound bomb.

NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS

LANGLEY MEMORIAL AERONAUTICAL LABORATORY - LANGLEY FIELD. VA

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- velocity at various vert-icol p/Qnes.

MR No. L6GIO

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I \. \~,I ',l}

JL~~f:.::;b+~==t;t2SF-</;'1 I I ~~().

I I I I I I ~fj1__1- -1-+ ----J-+-+- ~ ~

I / I / I \. ,s.;II 1/ I f

o II 1/ I rt:J'Y~\~.3.0 /.6 0 1.5" .3.0 v

Dlsro/7Ce olo/1q iJol-loln > /ncnes

v/J/.5

(b) Pions 2, V= 26/ mph.

NATIONAL ADVISORYCOMMITTEE FOR AERONAUTICS

F/C7t./re /e. - Conlint/ed.

MR No. L6G10

(c)P/ane 2, Mk 2aO,Mod.4 -f'uze(Wlthol/;t- vone) movnred in bomb

11= 268 Inph NATIONAL ADVISORYCOMMITTEE FOR AERONAUTICS

F/ql/rs /2. - Conr/nued.

MR No. L6G10

.5

IIIIIII

J-+-+-----p....,.._-+-'#---'.~H__-----__,I 0 ~~. ~

J .~(J

" ~~.l1I 9­

-f-~--r-.o ~o.,

I ~oII ~ I (j

- +-~--I-- '> n.I " I \. (;'U

I, I rfO It () .f:.

~. ~J3.0 15 /5 3.0 ~

Disrance a/0I19 bot-fDm) InchQsNATIONAL ADVISORY

COMMITTEE FOR AERONAUTICS

1.0

(dJP/one3, V.:: 264 mph

Figure /2. - Concluded.