Subsonic Bomber Aircraft

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SUBSONIC BOMBER AIRCRAFTA PROJECT REPORTSubmitted by SUDHAN.U (62205101043) SYED MUSTHAFA.H (62205101047) THIRUMALVALAVAN.M (62205101048) THIRUMURUGAN.M (62205101049)In partial fulfillment for the award of the degreeOfBACHELOR OF ENGINEERINGInAERONAUTICAL ENGINEERINGV.S.B. ENGINEERING COLLEGE, KARUR. SUBSONIC BOMBER AIRCRAFTA PROJECT REPORTSubmitted bySUDHAN.U (62205101043) SYED MUSTHAFA.H (62205101047) THIRUMALVALAVAN.M (62205101048) THIRUMURUGAN.M (62205101049)In partial fulfillment for the award of the degreeOfBACHELOR OF ENGINEERINGInAERONAUTICAL ENGINEERINGV.S.B. ENGINEERING COLLEGE, KARUR.ANNA UNIVERSITY: CHENNAI 600 025BONAFIDE CERTIFICATEThis is to certified that the project report ofSUBSONIC BOMBER AIRCRAFTis the bonafide work ofSUDHAN.U (62205101043)who carried out the project work under my supervision.SIGNATURE SIGNATUREMr. K. VELMURUGARAJAN , Mr. J.BRUCE RALPHIN ROSE,HEAD OF THE DEPARTMENT, SUPERVISOR,Dept. of Aeronautical Engg, Lecturer,V. S. B. Engineering College. Dept. of Aeronautical Engg. V. S. B. Engineering College.Date:Submitted this project for viva voice on..External Examiner Internal ExaminerANNA UNIVERSITY: CHENNAI 600 025BONAFIDE CERTIFICATEThis is to certified that the project report ofSUBSONIC BOMBER AIRCRAFTis the bonafide work ofSYED MUSTHAFA.H (62205101047)who carried out the project work under my supervision.SIGNATURE SIGNATUREMr. K. VELMURUGARAJAN , Mr. J.BRUCE RALPHIN ROSE,HEAD OF THE DEPARTMENT, SUPERVISOR,Dept. of Aeronautical Engg, Lecturer,V. S. B. Engineering College. Dept. of Aeronautical Engg. V. S. B. Engineering College.Date:Submitted this project for viva voice on..External Examiner Internal ExaminerANNA UNIVERSITY: CHENNAI 600 025BONAFIDE CERTIFICATEThis is to certified that the project report ofSUBSONIC BOMBER AIRCRAFTis the bonafide work ofTHIRUMALVALAVAN.M (62205101048)who carried out the project work under my supervision.SIGNATURE SIGNATUREMr. K. VELMURUGARAJAN , Mr. J.BRUCE RALPHIN ROSE,HEAD OF THE DEPARTMENT, SUPERVISOR,Dept. of Aeronautical Engg, Lecturer,V. S. B. Engineering College. Dept. of Aeronautical Engg. V. S. B. Engineering College.Date:Submitted this project for viva voice on..External Examiner Internal ExaminerANNA UNIVERSITY: CHENNAI 600 025BONAFIDE CERTIFICATEThis is to certified that the project report of SUBSONIC BOMBER AIRCRAFTis the bonafide work ofTHIRUMURUGAN.M (62205101049)who carried out the project work under my supervision.SIGNATURE SIGNATUREMr. K. VELMURUGARAJAN , Mr. J.BRUCE RALPHIN ROSE,HEAD OF THE DEPARTMENT, SUPERVISOR,Dept. of Aeronautical Engg, Lecturer,V. S. B. Engineering College. Dept. of Aeronautical Engg. V. S. B. Engineering College.Date:Submitted this project for viva voice on..External Examiner Internal ExaminerACKNOWLEDGEMENTFirst and foremost, we wish to acknowledge our debt to the `HARD WORK IS THE KEY TO SUCCESS` who has given us knowledge and good health.We would like to express to the chairman of our college,Mr. V.S.BALUSAMY and the principal Mr. JOHN ORAL BASKAR, for providing better working environments and educational facilities. We are much grateful Mr. K.VELMURUGARAJAN Head of the department of the Aeronautical engineering for this encouragement discussion, valuable comments and many innovative ideas in carrying out this project. Without his timely help it would have been impossible for us to complete this work.We acknowledge in no less terms the qualified and excellent assistance rendered by Mr. J.BRUCE RALPHIN ROSE, Lecturer, Department of Aeronautical Engineering. We owe a debt of gratitude for his valuable suggestions, kind inspiration and encouragement. We most sincerely acknowledge the staff members of Department of Aeronautical Engineering for their constant inspiration and suggestions. We owe a debt gratitude to our parents and friends for their advice and to keep our spirits high to complete this project.TABLE OF CONTENTCHAPTER.NO TITLE ABSTRACTLIST OF SYMBOLSINTRODUCTION1.COMPARITIVE STUDY OF SUBSONIC BOMBER 1.1 DIMENSIONS1.2 WEIGHT CONFIGURATION1.3 PERFORMANCE1.4 ENGINE CONFIGURATION1.5 ARMAMENTS2.SELECTION OF MAIN PARAMETERS 2.1 AIRFOIL SELECTION2.2 CO-EFFICIENT OF LIFT VS ANGLE OF ATTACK2.3 CO-EFFICIENT OF LIFT VS DRAG2.4 MAX.L/D VS VELOCITY2.5 RANGE VS VELOCITY2.6 ALTITUDE VS VELOCITY2.7 ASPECT RATIO VS VELOCITY2.8 WING LOADING VS VELOCITY2.9 SFC VS MACH NUMBER2.10 T/W VS VELOCITY3.WEIGHT ESTIMATION3.1 WEIGHT CALCULATION3.2 MISSION PROFILE3.3 APPROXIMATE WEIGHT ESTIMATION3.4 ACTUAL WEIGHT ESTIMATION 3.4.1 ITERATION4.ENGINE SELECTION4.1 ENGINE LOCATION4.2 THRUST CALCULATION 4.2.1THRUST VS SFC4.3 ENGINE CONFIGURATION 4.3.1 ENGINE DIMENSION4.4 CONFIGURATION 4.4.1 ADVANTAGES OF POTTED ENGINE 4.4.2 DISADVANTAGE OF POTTED ENGINE4.5 THRUST MATCHING5.AIRFOIL SELECTION5.1 CALCULATION OF CL5.2 REYNOLDS NUMBER5.3 MAXIMUM CL5.4 SKIN FRICTION DRAG FOR TURBULENT FLOW5.5 REQUIRED CL(MAX)5.6 NACA-63A0105.7 THIN AIRFOIL THEORY6.WING SELECTION6.1 EQUIVALENT ASPECT RATIO6.2 STRUCTURAL WEIGHT FOR VARYING THICKNESS OF AIRFOIL6.3 LOCATION OF CENTER OF GRAVITY7.WETTED SURFACE AREA AND DRAG ESTIMATION7.1 CALCULATION OF WETTED SURFACE AREA 7.1.1 FUSELAGE 7.1.2 WING AREA 7.1.3 HORIZONTAL TAIL 7.1.4 VERTICAL TAIL 7.1.5 ENGINE 7.1.6 UNDERCARRIAGE OR LANDING GEAR 7.1.7 1/4th OF FLAP 7.1.8 FULL FLAP7.2 DRAG CALCULATION 7.2.1 DRAG POLAR 7.2.2 CRUISE 7.2.3 TAKEOFF 7.2.4 LANDING7.3 DRAG FOR EACH ALTITUDE 7.3.1 AT SEA LEVEL 7.3.2 AT h=500m 7.3.3 AT h=1000m 7.3.4 AT h=1500m 7.3.5 AT h=2000m8.ESTIMATION OF RATE OF CLIMB8.1 CALCULATION OF RATE OF CLIMB 8.1.1 AT SEA LEVEL 8.1.2 AT h=500m 8.1.3 AT h=1000m 8.1.4 AT h=1500m 8.1.5AT h=2000m8.2 TIME REQUIRED FOR REACHING THE SERVICE CEILING9.CALCULATION OF TAKEOFF & LANDING DISTANCE9.1 LENGTH OF TAKEOFF RUN 9.1.1 GROUND RUN 9.1.2 TRANSITION RUN 9.1.3 CLIMBING9.2 LENGTH OF LANDING RUN 9.2.1 DESCENDING 9.2.2 TRANSITION RUN 9.2.3 GROUND RUN10.THREE VIEW OF SUBSONIC BOMBER AIRCRAFT10.1 FRONT VIEW10.2 TOP VIEW10.3 SIDE VIEW11.BIBLIOGRAPHYSYMBOLS USEDW-Weight of airgraftWo-Overall weightWf-weight of fuelWe-Empty weightLf fuselage lengthDf diameter of fuselageSw - wing areaTw - wing thicknessbw,b wing spanSht horizontal tail areatht horizontal tail thicknessbht - horizontal tail spanAR aspect ratioS Surface areaSvt vertical tail areatvt - vertical tail thicknessbvt vertical tail spanCdo drag polarCd coefficient of dragCL - coefficient of liftF, T thrustT/W-Thrust loadingW/S-Wing loadingA.R-Aspect ratioCr,Ct-Chord length of root, tipTr,Tt-Thickness of root, tipSp-Wetted surface areaCDp-Coefficient of drag of wetted surface areaa-Angle of attackC.G-Center of gravity-Dihedral angleR-RangeE-Endurance-Ground frictionV-Free stream velocityC-ChordLf-Length of fuselageVT-Vertical tailHT-Horizontal tail-Density(kg/m3)g-Gravitys-DistanceH-Heighth-altitudeROC rate of climbV, u velocityD DragL Liftg Acceleration of gravityWo optimum weight- sweep angleCr root chordABSTRACTFirst we start with design and development. Lets take the military as an example. Suppose the military wants to design new weapons systems that will be more accurate than the system they currently have. The first thing they have to do is get a team of scientists and whatever other personnel are needed to design the system. Then, after they come up with a design they are pleased with they have to get the engineers to develop it. All these people either have to be hired or contracted. Some of the work may be sub contracted.Then there is the acquisition of the materials needed. Some of the materials may already be on the hand while others have to be purchased domestically and others will need to be purchased from overseas. In many cases bids will be put in to various companies to see who can supply the material at the cheapest cost.After the materials are acquired theres the matter of storage. in many cases the material is either of so large in size that the storage facilities need to be specially built in order to adequately provide the needed space. this of course has to be figured into the equation.Then theres the matter of movement and distribution to may be the various military base around the country even overseas. Trucks or planes need to be acquired in order to distribute the materials if there arent enough read made transportation vehicles. Transportation costs alone can be astronomical. IN