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PREPARED BY:-1.)DIGVIJAY YADAV 2.)KUMAR MANAS 3.)ASHISH KUMAR 4.)MOHMMAD ZAFAR

Vel tech universityAeronautical dept.120 SEATER PASSENGER AIRCRAFT CONCEPTUAL DESIGN

Comparative configuration study of different types of airplanes:S.NOA/C NAMEFUNCTIONENGINECREW WING SPANLENGTHHEIGHTWING AREASPEEDRANGEALTITUDE No.MMMM2Km/hr/machKmM1.BuccaneerAttack2*5105kg R.R.RB168 spey m.k.101113.4119.334.9747.82.92`644012190 2.MIG-25RB Fox bat-BReconaissance/ attack2*10210Kg Tumansky R-15B-300113.4221.556.527.2530002900230003.FB-111A Raven Bomber2*90.58KN P&W TF30-p-7319.2023.166.1048.7723353300182004.SU-35 Super FlankerFighter2*137.3KN Al-31MF115.1621.966.846224403500180005.LCA-TejasFighter1*83.4KN GTRE GTX 35VS Augmented TB18.2013.204.41850164006.BE-200SARMultipurpose2*D-436 TPTB232.7831.432.60710360080007.Airbus cooperate jetBussinessIAE V2527-AS434.1033.8411.76.821110125008.A-318Passenger2*P&W PW6000 series234.1034.4412.51122.6.785700120009.Boeing-787PassengerRolls Royce Trent-1000260.056.716.9325.89125001310010.Bombarider C series 100Passenger2*P&W PW1500 G235.134.911.5112.3.81546312497Comparative study on specification and performance details of aircraft(1.)General:-Flight crew-2Cabin crew-4Passenger-120(2.)Avionics information:-Fly by wire systemSide stick controlLarge LCD displaySingle/dual head display(3.)It is having medium range jet areoplane which having the range of approx. 4000km(4.) Power Plant:-Turbo fan jet engineEngine name:-2*P&W4000G engineThrust:-52000lbEmission:-NOx=55% Smoke:-50%Unburned hydrocarbon=75%CO=50%From above data we can see that engine is eco-friendly.Its having alternative fuel bio-fuel. (5.)Weight:-It is medium jet airliner which has following weight specification.\Max.Take-off weight=58151kgMax.landing weight=507560kgMax.payload=14560kgCargo weight=371kg(6.)External dimension:-Length=34.9mWing span=35.1mWing area=112.3m2Height=11.5mFuselage max.diameter=3.7mS.NO.NAME OF THE AIRCRAFTPASSENGERSVELOCITYALTITUDERANGEWEIGHTWING AREAASPECT RATIOWINGSPANOVERALL LENGTHThrust Unit km/hrm kmkgm2AR m mKN1Airbus 32015687111500676042175122.67.7334.0937.57111-1202Boeing 737 max12684212237670462000124.589.4534.333.6643Embrarer 120 Jet family301621250017851125039.49.919.782062.34Boeing 747550955110009800333390510.956.959.670.62235Sukhoi super jet 10083828125002900266001237.327.8026.44606Mitsubishi regional jet78828115001530368501297.829.223.469.37Airbus Commercial Jet1561005125001100076500129.58.834.1033.84968Topolov-334-10010285011100315047900835.629.7731.2673.69Bombardier CRJ-700788291249732083492670.67.423.2432.5158.410Boeing 787 Dreamliner26491313100152002280003255.456056.7280Table: 1 Comparison of Aircraft

Worksheet layout procedure:-An imaginary profile of the 120 seater aircraft is prepared and values are as following:Wing type->Swept wingWing span->27.92mOverall length->35mHeight from ground->11mSurface area(s)=102m2

Result:-An imaginary layout of aircraft is drawn and dimensions are obtained.Comparative graphs preparation and selection of main parameters for the design

Result:- The comparative data for different aircraft were studied and the following fundamentals design parameters were solved:- S.noParameters Values 1.Cruising velocity of aircraft828km/hr2.Aspect Ratio7.653.Wing loading0.03484.Range 3700km5.Span to length ratio0.8WEIGHT ESTIMATION FORMULA

STANDARD PAYLOAD WEIGHT

CREW WEIGHT

WTo=58151kgEstimation of Payload and Crew Weight:-Take the one passenger weight=70kgNumber of passenger=120Hence,total weight of passenger=120*70=8400kgWeight of cargo for one passenger=25kgTotal payload of cargo=25*120=3000kgTotal number of crew=6Assume one crew weight=75kgToal weight of crew=75*6=450kgWPL=Wpassenger+WcargoWPL=8400+3000=11400kgWC=450kgWPL+WC=11400+450=11850kgFUEL WEIGHT FRACTION

MISSION PROFILE:-Fuel weight estimation(Wf):-Wf/WTO=1-(W6/W1)Number of segments:-1.)Take-off=W2/W1=0.992.)Climb=W3/W2=0.973.)Cruise=W4/W3=0.954.)Descent=W5/W4=0.995.)Land=W6/W5=0.997 Hence:-W6/W1= (W2/W1 )(W3/W2)( W4/W3)( W5/W4 )(W6/W5)W6/W1=(0.99*0.97*0.95*0.99*0.997)W6/W1=0.9Wf/WTo=1-0.9=0.1(Wf/58151)=0.1Wf=5815.1kgWLand=WTo-WfuelWland=58151-5815.1=52335.91kgEMPTY WEIGHT

a=-7.75*10-8 and b=0.576substitute in eqn.(1) the value of a&b we will get:-WE/WTo=(-7.75*10-8*58151)+0.576=0.571490971WE=0.571490971*58151=33232.77148kgNow actual take off weight:-(WTo)actual=WPL+Wcrew+Wfuel+Wempty(WTo)actual=12600+450+5815.1+3232.7714=52097.8744kgPercentage error of total take-off weight:-%error=[(Assumed-Actual)/(Assumed)]*100%error=[(58151-52097.8744)/58151]*100%error=10.4%S.no.Engine ThrustWeight 1.P&W1124G115KN2245kg2.P&W1521G104KN2360kg3.GEnX 53000-75000lb7550kg4.GE9076000-115000lb8283kg5.P&W4000G52000lb3225kgProperties DataUnit Take-off thrust52000LbWeight of engine3225KgSFC(1.)0.5loiter(2.)0.4cruiseLb/hour/HPWeight of fuel5815.1kgEngine selection :-From reference graph5 we got:-F/W=0.0348F=(0.0348*52097.8744)/9.81=203KN We choose the Twin-Jet Engine commercial aircraft.So the power produced by each engine is=203/2=101.5KN/engine=46182.5lb/engineTable for comparing engie:-Selected engine is P&W4000G:-

Calculation of main parameters(S,b,l):-From graph3:-W/S=512.95Hence,S=102mFrom graph4:-b2/S=7.65b2=7.65*102=780b=27.92mFrom graph2:-b/l=0.827.92/l=0.8l=35m

D=D0+Di

DRAG CLASSIFICATION

OPTION FOR VERTICAL WING CONFIGURATION

AIRFOIL GEOMETRIC PARAMETER

ASPECT RATIO

TAPER RATIO

AIRFOIL SELECTION

SWEPT WING AND TWIST ANGLE

TAIL DESIGN PROCEDURE

AFT TAIL CONFIGURATION

AIRFOIL SELECTION FOR HORIZONTAL STABILIZER

AIRFOIL SELECTION FOR VERTICAL TAIL

IN TRIANGLE ACF:-

Performance Analysis

L=5310.69KNW=52097.8744KgF=(2*40,000)lbD=4.5KN/m3

ROC=293.22m/s

Range(R)=3700KmTake-off distance determination:-Takeoff Takeoff speeds Takeoff runway required Takeoff climb required Obstacle clearance requirementsTAKE-OFF

RATE OF CLIMBLANDING

Conclusion:-Aircraft Type:-120 seater passenger aircraftAircraft specification:-AVIONICS:-(i)Fly-by-wire system(ii)Side-stick control(iii)Large LCD display

General Information:-(i)Flight crew-2(ii)Cabin crew-4(iii)Passenger-120

Engine:-

Properties DataUnit Take-off thrust52000LbWeight of engine3225KgSFC(1.)0.5loiter(2.)0.4cruiseLb/hour/HPWeight of fuel5815.1kgl=35mb=27.92mS=102mCalculation of main parameters(S,b,l):-Actual take off weight:-(WTo)actual=WPL+Wcrew+Wfuel+Wempty(WTo)actual=12600+450+5815.1+3232.7714=52097.8744kgLanding-gear type:-Retraction/ExtractionDriven by:-Hydraullic/Pneumatic System