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BUSINESS JET AIRCRAFT

BUSINESS JET AIRCRAFT

BUSINESS JETThe business jet or Private Jets are used by a Less number of people for personnel transportations mostly. It is classified into five types based on its size.

Heavy jetsSuper mid-size jetsMid-size jetsLight jetsVery light jetsFACTS ABOUT BUSINESS JET AIRCRAFTSThere are 17,721 business jets in the worldwide fleet at the end of 2011 with about 70% of the fleet in North America. The European market is the next largest, with growing activity in the Middle East, Asia, and Central America.

Since 1996 the term "fractional jet" has been used in connection with business aircraft owned by a consortium of companies. Under such arrangements, overhead costs such as flight crew, hangarage and maintenance are split among the users.FACTS ABOUT BUSINESS JET AIRCRAFTSAlmost all production business jets, such as General Dynamics' Gulfstream and the Gates Lear Jet (now built by Bombardier), have had two or three engines, though the Jetstar, an early business jet, had four. Advances in engine reliability and power have rendered four-engine designs obsolete, and only Dassault Aviation still builds three-engine models (in the Falcon line). The emerging market for so-called "very light jets" and "personal jets", has seen the introduction (at least on paper) of several single-engine designs as well.

Almost all business jets have rear-mounted engines, because the wing (mounted low for performance reasons) is too near the ground for engines to be slung underneath it.MISSION SPECIFICATIONCruise Speed =850 Km\HMaximum Speed = 0.85 MachRange =4500 kmAbosolute Ceiling = 13700 mService Ceiling = 12400 m Rate of climb = 22 m/sThrust = 22 KNCrew = 8+2Type of engine = turbofansMax Pay Load = 2240 lbsNo of engine =2 Engine

Configuration LayoutLocation of door : CockpitEngine Type : Pusher TypeNo. Of Wing : MonoplaneType of Wing : Swept BackPosition of Wing : Low wingType of tail : T-TailType of landing gear : TricycleLanding gear mechanism : RetractableLocation of engine : Fuselage Rear EndType of control systems : Ailerons & RuddevatorsRunway : Land based

Gulfstream G200General Characteristics Crew: 8+2Length (m) :18.96Wingspan(m) : 17.7Height (m) : 6.53Wing Area (m2) : 34.3Aspect ratio: 9.1 Empty Weight (Kg) : 8709Loaded Weight (Kg) : 10888Payload Weight (Kg) : 2179Max.Takeoff Weight (Kg): 10680No. of Engines : 2

Cruise Speed (Km/h) : 850Range (km) : 6300Absolute Ceiling (m) : 13716Service Ceiling (m) : 12497Rate of Climb (m/s) : 18.8Wing Loading (Kg/ m2) : 469Thrust (KN) 26.9Mach No. : 0.85Thrust/Weight Ratio : 0.17Location of door : CockpitEngine Type : Pusher TypeNo. Of Wing : MonoplaneType of Wing : Swept BackPosition of Wing : Low wingType of tail : T-TailType of landing gear : TricycleLanding gear mechanism : RetractableLocation of engine : Fuselage Rear EndType of control systems : Ailerons & RuddevatorsRunway : Land based

Learjet 60XR

General Characteristics Crew: 8+2Length (m) :17.89Wingspan(m) : 13.35Height (m) : 4.44Wing Area (m2) : 24.57Aspect ratio: 7.2Empty Weight (Kg) : 6641Loaded Weight (Kg) : 8856Payload Weight (Kg) : 2215Max.Takeoff Weight (Kg): 10659No. of Engines : 2

Cruise Speed (Km/h) : 863Range (km) : 4454Absolute Ceiling (m) : 15545Service Ceiling (m) : 13584Rate of Climb (m/s) : 22.9Wing Loading (Kg/ m2) : 432.8Thrust/Weight Ratio : 0.20Thrust (KN) 20.46Mach No. : 0.81Location of door : CockpitEngine Type : Pusher TypeNo. Of Wing : MonoplaneType of Wing : Swept BackPosition of Wing : Low wingType of tail : T-TailType of landing gear : TricycleLanding gear mechanism : RetractableLocation of engine : Fuselage Rear EndType of control systems : Ailerons & RuddevatorsRunway : Land basedHawker 400 General Characteristics Crew: 8+2Length (m) :14.76Wingspan(m) : 13.26Height (m) : 4.24Wing Area (m2) : 22.43Aspect ratio: 7.8Empty Weight (Kg) : 4558Loaded Weight (Kg) : 6147Payload Weight (Kg) : 1600Max.Takeoff Weight (Kg): 7303No. of Engines : 2

Cruise Speed (Km/h) : 820Range (km) : 3135Absolute Ceiling (m) : 13700Service Ceiling (m) : 12497Rate of Climb (m/s) : 19.2Wing Loading (Kg/ m2) : 319.98Thrust/Weight Ratio : 0.18Thrust (KN) 12.9Mach No. : 0.78Location of door : CockpitEngine Type : Pusher TypeNo. Of Wing : MonoplaneType of Wing : Swept BackPosition of Wing : Low wingType of tail : T-TailType of landing gear : TricycleLanding gear mechanism : RetractableLocation of engine : Fuselage Rear EndType of control systems : Ailerons & RuddevatorsRunway : Land basedEmbraer Phenon 300 General Characteristics Crew: 8+2Length (m) :15.9Wingspan(m) : 16.2Height (m) : 5Wing Area (m2) : 28.5Aspect ratio: 9.2Empty Weight (Kg) : 5258Loaded Weight (Kg) : 7679Payload Weight (Kg) : 2421Max.Takeoff Weight (Kg): 8157No. of Engines : 2

Cruise Speed (Km/h) : 834Range (km) : 3650Absolute Ceiling (m) : 13716Service Ceiling (m) : 12497Rate of Climb (m/s) : 15.25Wing Loading (Kg/ m2) : 286Thrust/Weight Ratio : 0.18Thrust (KN) 14.2Mach No. : 0.78Location of door : CockpitEngine Type : Pusher TypeNo. Of Wing : MonoplaneType of Wing : Swept BackPosition of Wing : Low wingType of tail : T-TailType of landing gear : TricycleLanding gear mechanism : RetractableLocation of engine : Fuselage Rear EndType of control systems : Ailerons & RuddevatorsRunway : Land based

Learjet 40 General Characteristics Crew: 8+2Length (m) :16.93Wingspan(m) : 14.56Height (m) : 4.31Wing Area (m2) : 28.95Aspect ratio: 7.3Empty Weight (Kg) : 6200Loaded Weight (Kg) : 8727Payload Weight (Kg) : 2527Max.Takeoff Weight (Kg): 9545No. of Engines : 2

Cruise Speed (Km/h) : 852Range (km) : 3439Absolute Ceiling (m) : 15540Service Ceiling (m) : 12497Rate of Climb (m/s) : 14.32Wing Loading (Kg/ m2) : 318.69Thrust/Weight Ratio : 0.17Thrust (KN) 15.56Mach No. : 0.81Location of door : CockpitEngine Type : Pusher TypeNo. Of Wing : MonoplaneType of Wing : Swept BackPosition of Wing : Low wingType of tail : T-TailType of landing gear : TricycleLanding gear mechanism : RetractableLocation of engine : Fuselage Rear EndType of control systems : Ailerons & RuddevatorsRunway : Land based



Bombardier Challenger 300 General Characteristics Crew: 8+2Length (m) :20.9Wingspan(m) : 19.45Height (m) : 6.2Wing Area (m2) : 48.57Aspect ratio: 7.8Empty Weight (Kg) : 10591Loaded Weight (Kg) : 15943Payload Weight (Kg) : 5352Max.Takeoff Weight (Kg): 17622No. of Engines : 2

Cruise Speed (Km/h) : 870Range (km) : 5741AbsoluteCeiling (m) : 13716Service Ceiling (m) : 12447Rate of Climb (m/s) : 25.4Wing Loading (Kg/ m2) : 359.49Thrust/Weight Ratio : 0.18Thrust (KN) 30.36Mach No. : 0.89Location of door : CockpitEngine Type : Pusher TypeNo. Of Wing : MonoplaneType of Wing : Swept BackPosition of Wing : Low wingType of tail : T-TailType of landing gear : TricycleLanding gear mechanism : RetractableLocation of engine : Fuselage Rear EndType of control systems : Ailerons & RuddevatorsRunway : Land based

CESSNA 560 CITATION ENCOREGeneral Characteristics Crew: 8+2Length (m) :14.9Wingspan(m) : 16.49Height (m) : 4.63Wing Area (m2) : 29.9Aspect ratio: 8.54Empty Weight (Kg) : 4627Loaded Weight (Kg) : 6636Payload Weight (Kg) : 2009Max.Takeoff Weight (Kg): 7543No. of Engines : 2


Cessna 560XL Citation Excel and XLS General Characteristics Crew: 8+2Length (m) :16Wingspan(m) : 17.17Height (m) : 5.23Wing Area (m2) : 34.5Aspect ratio: 7.8Empty Weight (Kg) : 5579Loaded Weight (Kg) : 7985Payload Weight (Kg) : 2406Max.Takeoff Weight (Kg): 9163No. of Engines : 2


Cessna 680 Citation Soverign General Characteristics Crew: 8+2Length (m) :19.37Wingspan(m) : 19.24Height (m) : 6.2Wing Area (m2) : 47.4Aspect ratio: 9.09Empty Weight (Kg) : 7893Loaded Weight (Kg) : 12319Payload Weight (Kg) : 4426Max.Takeoff Weight (Kg): 12608No. of Engines : 2


Cessna 750 Citation XGeneral Characteristics Crew: 8+2Length (m) :22Wingspan(m) : 19.38Height (m) : 5.84Wing Area (m2) : 49Aspect ratio: 7.8Empty Weight (Kg) : 9798Loaded Weight (Kg) : 14424Payload Weight (Kg) : 4426Max.Takeoff Weight (Kg): 16374No. of Engines : 2


Gulfstream G150General Characteristics Crew: 8+2Length (m) :17.3Wingspan(m) : 16.94Height (m) : 5.82Wing Area (m2) : 34.3Aspect ratio: 8.7Empty Weight (Kg) : 6849Loaded Weight (Kg) : 9843Payload Weight (Kg) : 2994Max.Takeoff Weight (Kg): 11839No. of Engines : 2


Hawker 4000 HorizonGeneral Characteristics Crew: 8+2Length (m) :21.1Wingspan(m) : 18.8Height (m) : 6Wing Area (m2) : 49.3Aspect ratio: 7.1Empty Weight (Kg) : 10659Loaded Weight (Kg) : 15915Payload Weight (Kg) : 5256Max.Takeoff Weight (Kg): 17917No. of Engines : 2

Cruise Speed (Km/h) : 859Range (km) : 5287Absolute Ceiling (m) : 13716Service Ceiling (m) : 12397Rate of Climb (m/s) : 17Wing Loading (Kg/ m2) : 363.25Thrust/Weight Ratio : 0.16Thrust (KN) 28.9Mach No. : 0.84Location of door : CockpitEngine Type : Pusher TypeNo. Of Wing : MonoplaneType of Wing : Swept BackPosition of Wing : Low wingType of tail : T-TailType of landing gear : TricycleLanding gear mechanism : RetractableLocation of engine : Fuselage Rear EndType of control systems : Ailerons & RuddevatorsRunway : Land basedLearjet 25General Characteristics Crew: 8+2Length (m) :14.5Wingspan(m) : 12.84Height (m) : 3.73Wing Area (m2) : 21.53Aspect ratio: 7.6Empty Weight (Kg) : 3645Loaded Weight (Kg) : 5007Payload Weight (Kg) : 1362Max.Takeoff Weight (Kg): 6804No. of Engines : 2


Learjet 45General Characteristics Crew: 8+2Length (m) :17.68Wingspan(m) : 14.58Height (m) : 4.3Wing Area (m2) : 28.95Aspect ratio: 7.2Empty Weight (Kg) : 6146Loaded Weight (Kg) : 8716Payload Weight (Kg) : 2570Max.Takeoff Weight (Kg): 9752No. of Engines : 2

Cruise Speed (Km/h) : 859Range (km) : 3925Absolute Ceiling (m) : 15545Service Ceiling (m) : 12597Rate of Climb (m/s) : 15Wing Loading (Kg/ m2) : 321.26Thrust/Weight Ratio 0.16Thrust (KN) 15.57Mach No. : 0.81Location of door : CockpitEngine Type : Pusher TypeNo. Of Wing : MonoplaneType of Wing : Swept BackPosition of Wing : Low wingType of tail : T-TailType of landing gear : TricycleLanding gear mechanism : RetractableLocation of engine : Fuselage Rear EndType of control systems : Ailerons & RuddevatorsRunway : Land based



Falcon 2000EX General Characteristics Crew: 8+2Length (m) :20.23Wingspan(m) : 19.33Height (m) : 7.06Wing Area (m2) : 49Aspect ratio: 7.6Empty Weight (Kg) : 9405Loaded Weight (Kg) : 12678Payload Weight (Kg) : 3273Max.Takeoff Weight (Kg): 18597No. of Engines : 2

Cruise Speed (Km/h) : 850Range (km) : 6020Absolute Ceiling (m) : 15500Service Ceiling (m) : 12497Rate of Climb (m/s) : 22.24Wing Loading (Kg/ m2) : 435Thrust/Weight Ratio : 0.14Thrust (KN) 26.3Mach No. : 0.8Location of door : CockpitEngine Type : Pusher TypeNo. Of Wing : MonoplaneType of Wing : Swept BackPosition of Wing : Low wingType of tail : T-TailType of landing gear : TricycleLanding gear mechanism : RetractableLocation of engine : Fuselage Rear EndType of control systems : Ailerons & RuddevatorsRunway : Land based

Literature SurveyLiterature Survey concepts are evaluated, compared to the requirements, revised, re-evaluated, and so on until convergence to one or more satisfactory concepts is achieved. Average Value Taken From GraphMAXIMUM TAKEOFF: 12000 kgCRUISE SPEED: 850 km/hrRANGE: 4500 kmEMPTY WEIGHT: 6500 kgMAXIMUM SPEED: 942 kmSERVICE CEILING: 12497 mWING LOADING: 363 kg/m2WING AREA:38 m2WING SPAN: 15 mSTALL SPEED: 54.75 mpsRATE OF CLIMB:90 m/min

Mission Profile

MISSIONS0-1: Engine Start & Warmup1-2: Takeoff & Climb2-3: Cruise3-4: Loiter & Descent4-5: Landing & Shutoff

Estimation of Fuel fractionMission0-1: W1/W0 = 0.97 (Historical value)1-2: W2/W1 = 0.9 (Historical value)2-3: W3/W2 = 0.68 (Range Equation)3-4: W4/W3 = 0.95 (Endurance value)4-5: W5/W4 = 0.992 (Historical Equation)

Range EquationWi/Wi-1 = e-RC/V(L/D) X 0.866Range = 1757248 ftC = 0.7(per hour) = 0.000194(per sec)Velocity = 0.85M = 774.64 ft/sL/D = 13W3/W2 = 0.68Endurance EquationWi/Wi-1 = e-EC/(L/D)Endurance = 2700 sC = 0.000222 (S)L/D = 13W4/W3 = 0.95WEIGHT ESTIMATION W0 = Wcrew + Wpayload + Wfuel + Wempty

W0 = 14255.62 KgWeight of Fuel

= 0.40Wf = 5702.11 KgTank Capacity = 2228.96 gal

Empty Weight = 7412.92 KgWing DesignMatching PlotGulfstream G20059.84598.970.340.170.2828Learjet 60XR58.944255.790.390.20.330.36Hawker 40053.823194.050.410.180.330.29Embraer Phenon 30050.462807.730.350.180.240.25Learjet 4053.423234.420.340.170.230.31Learjet 5557.933803.020.350.180.290.31Bombardier Challenger 30052.643564.370.430.180.370.32CESSNA 560 CITATION ENCORE47.642474.810.470.20.390.3Cessna 560XL Citation Excel and XLS48.612605.480.410.20.320.29Cessna 680 Citation Soverign49.192816.340.380.190.330.31Cessna 750 Citation X51.733278.140.360.190.280.23Gulfstream G15053.943386.020.340.170.310.27Hawker 4000 Horizon52.653565.230.330.160.250.3Learjet 2553.843100.20.390.20.450.29lLearjet 4554.753304.560.320.160.220.32Learjet 6058.9142510.390.20.330.36Falcon 2000EX53.83723.20.290.140.280.28

WING SELECTIONWING GEOMETRY DESIGN The geometry of the wing is a function of four parameters, namely the 1) Wing loading (W/S),2) Sweepback angle at quarter chord (qc). The Take-off Weight that was estimated in the previous analysis is used to find the Aspect Ratio (b2/S), The value of S also enables us to calculate the Taper ratio ()Form Raymer book we choose our, Taper Ratio () = 0.33

WING CHORD DESIGN:

Dihedral AngleAIRFOIL SELECTIONChord line: It is the straight line connecting leading edge (LE) and trailing edge (TE).Chord (c): It is the length of chord line.Thickness (t): measured perpendicular to chord line as a % of it (subsonic typically 12%).Camber (d): It is the curvature of section, perpendicular distance of section mid-points from chord line as a % of it (sub sonically typically 3%).Angle of attack (): It is the angular difference between chord line and airflow directioNACA 4 Digit1st digit: maximum camber (as % of chord).2nd digit (x10): location of maximum camber (as % of chord from leading edge (LE)).3rd & 4th digits: maximum section thickness (as % of chord).NACA 5 Digit1st digit (x0.15): design lift coefficient.2nd & 3rd digits (x0.5): location of maximum camber (as % of chord from LE).4th & 5th digits: maximum section thickness (as % of chord).NACA 6 Digit1st digit: identifies series type.2nd digit (x10): location of minimum pressure (as % of chord from leading edge (LE)).3rd digit: indicates acceptable range of CL above/below design value for satisfactory low drag performance (as tenths of CL).4th digit (x0.1): design CL.5th & 6th digits: maximum section thickness (%c)

IDEAL LIFT COEFFICIENT CLC - Ideal Lift coefficient of the aircraft CLC= 2WAV / *VE 2S = (2*10297.13*9.81)/ {0.29*(236.11)^2*42.5} = 0.29CLCW Ideal Lift coefficient of the WingCLCW= CLC / 0.95 = 0.31 CLi- Ideal Lift coefficient of the Airfoil CLi= CLCW/ 0.9 =0.31/0.9 = 0.34IDEAL LIFT COEFFICIENT(AIRFOIL)= 0.3

Maximum lift coefficient (STALL SPEED):CLC max=Max. lift coeff. Of aircraft =2WTO/ VS^2 S =(2*14255.62*9.81)/{1.225*(54.75)^2*42.5) = 1.79CCLMAX(WING)= Max. lift coeff. Of wing =CLCMAX/0.95 = 1.88CLCMAX(GROSS)=Gross lift coeff. Of airfoil(with use of Flaps) =CLCMAX(WING)/0.9 = 2.09CLC(AIRFOIL)= CLCMAX(GROSS) -CL =2.09- 0.7 =1.39

MAX. LIFT COEFFICIENT(AIRFOIL)= 1.39

Thickness: 24.0%Camber: 2.8%Trailing edge angle: 32.3oLower flatness: 14.6%Leading edge radius: 7.4%Max CL: 1.36

Max CL angle: 15.0Max L/D: 27.038Max L/D angle: 6.0Max L/D CL: 0.761Stall angle: 1.5Zero-lift angle: -1.0Root Airfoil

LIFT TO DRAG RATIO OF NACA 23024

Tip Airfoil

Thickness: 21.0%Camber: 1.9%Trailing edge angle: 28.3oLower flatness: 22.2%Leading edge radius: 6.2%Max CL: 1.244Max CL angle: 15.0

Max L/D: 25.219Max L/D angle: 7.0Max L/D CL: 0.873Stall angle: 3.0Zero-lift angle: -1.0LIFT TO DRAG RATIO OF NACA 23021

AVERAGE CL max

Flap SelectionTypes of flap systems include:

Krueger flap: hinged flap on the leading edge. Often called a "droop". Plain flap: rotates on a simple hinge.Split flap: upper and lower surfaces are separate, the lower surface operates like a plain flap, but the upper surface stays immobile or moves only slightly. Gouge flap: a cylindrical or conical aerofoil section which rotates backwards and downwards about an imaginary axis below the wing, increasing wing area and chord without affecting trim. Invented by Arthur Gouge for Short Brothers in 1936..Flap Selection Fowler flap: slides backwards before hinging downwards, thereby increasing both camber and chord, creating a larger wing surface better tuned for lower speeds. It also provides some slot effect. The Fowler flap was invented by Harlan D. Fowler . Fairey-Youngman flap: moves body down before moving aft and rotating. Slotted flap: a slot (or gap) between the flap and the wing enables high pressure air from below the wing to re-energize the boundary layer over the flap. This helps the airflow to stay attached to the flap, delaying the stall. Blown flaps: systems that blow engine air over the upper surface of the flap atcertain angles to improve lift characteristics

Selected Flap

Double Slotted FlapPOWER PLANT SELECTIONThe literature survey indicated a thrust to weight ratio of 0.28 was appropriate. Hence:

Engine total take-off thrust = 0.28 14255.62 9.81= 31.19 kN (3991.57 Kg)

With two engines this equates to 19.58 kN per engine (1995.79 kg) Sl.noName of the enginetypeThrust (KN)1Honey well TFE731-20(Garrett)turbofan202General Electric CF700turbofan18.73Pratt & Whitney JTIA8turbofan15.84Honey well TFE731-40R-200GTurbofan18.9s:

Calculated thrust and weight of the engine are satisfied with the General Honey wellTFE731-20 therefore chosen this engine.

BUSINESS JET AIRCRAFTDesigned ByShahul Hameed Riyasudeen A (SP10AEU021)SriHari Haran E.S (SP10AEU023)Jagadesh R (SP10AEU006)

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