fixed wing design tool
DESCRIPTION
Fixed Wing Design ToolTRANSCRIPT
Mission Profile
Profile Notes/Sources:0 Warm-up Taxi Source: "2006-2007 AIAA Graduate Team Aircraft Design Competition - Modifiied RFP"1 Max Perforamnce Take-Off @ SL2 Max Power Climb to Opt. Alt.3 Cruise out 800 nm @ Optimum Speed/Alt4 Loiter for 20 min. @ 5,000ft5 20 min. Combat @ Corner Speed/SL6 Max Power Climb to Opt. Alt.7 Cruise Back 800 nm @ Optimum Speed/Alt8 Descend to SL @ Idle Thrust Setting9 20 min Loiter @ Endurance Speel/SL
10 Landing with 30 min Reserve Fuel @ SL
Mission Analysis
Step 1 Notes/Sources:Ammunition Weight (1.62 lbs x 2000 rounds) 3,240 lbs Source: "2006-2007 AIAA Graduate Team Aircraft Design Competition - Modifiied RFP"Internal Stores Max 5,000 lbs GD GAU-8 30-mm Cannon is part of weight emptyExternal Stores Max 12,000 lbs External Stores is deemed the limiting case
Total 12,000 lbs Enter Payload based on above values, and Desired Mission (for baseline misson, assume worst case external stores)
Crew WeightCrew (1x250lbs) 250 lbs Source: "2006-2007 AIAA Graduate Team Aircraft Design Competition - Modifiied RFP"
Total 250 lbs
Step 2Aircraft Type W_PL W_TO V_MAX Range Source: Taylor, J.W.R, Jane's All The World Aircraft Published Annually by: Jane's Publishing Company, (Issues used: 1945/45, 1968/84)
(lbs) (lbs) (kts) (nm) Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 60F.R. A10A 15,000 50,000 450 540
Grumman A6 17,000 60,400 689 1,700 Tornado F.Mk2 16,000 58,400 600 750
Average: 16,000 56,267 580 997 Some initial guess for TOGW, will only be used for reference, program automatically calculates TOGW based on historical data
59,488 lbs Later this will be iterated to find weight empty
Step 3 Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 12
Climb 1Range Credit 24.5000001 nm Assume 10,000 ft/min climb (from RFP) and 350 knot ground speed during climb (from Roskam page 62); therefore, Rclimb = Alt./(10K/min)*350knotsCruise 1
775.5 nm 800 nm specified in RFP - climb 1 rangeAltitude 42,000 ft
Temperature @ Alt, T -90.6Delta 0.1668Theta 0.7116
Payload Calculations, W PL
WPL
WCREW
Weight Take Off Guess Based on Historical Data, W TO_GUESS
WTO_GUESS
Mission Fuel Weight Fractions, W F
Rcr, Cruise Range
o F
Mission Summary (Baseline Mission)
Seg. Description Altitude Temp. Density Velocity Range(ft) (°F) slug/ft^3 knots nm
0 0 59.0 ### 0.0 - 1 Warm-up Taxi 0 59.0 ### 0.0 - 2 Max Perforamnce Take-Off @ SL 0 59.0 ### TBD - 3 Max Power Climb to Opt. Alt. 42,000 -90.6 ### 350.0 25 4 Cruise out 800 nm @ Optimum Speed/Alt 42,000 -90.6 ### 459.0 800 5 Loiter for 20 min. @ 5,000ft 5,000 41.2 ### 226.6 800 6 20 min. Combat @ Corner Speed/SL 0 59.0 ### 275.0 800 7 Max Power Climb to Opt. Alt. 42,000 -90.6 ### 350.0 825 8 Cruise Back 800 nm @ Optimum Speed/Alt 42,000 -90.6 ### 459.0 1,600 9 Descend to SL @ Idle Thrust Setting 0 0.0 ### 459.0 1,600
10 20 min Loiter @ Endurance Speel/SL 0 0.0 ### 187.5 1,600 11 Landing with 30 min Reserve Fuel @ SL 0 0.0 ### 0.0 1,600
q L/D Fuel Burn Fuel Weight Betapsf (lbs) (lbs) (lbs)0 0.0000 0.0172 0.00 1.000 - - 59,488 1.0000 0.0000 0.0172 0.00 0.990 595 595 58,894 0.9900 TBD TBD 0.990 1,184 589 58,305 0.980- - - - 0.960 3,516 2,332 55,972 0.941
167 0.3940 0.0282 13.97 0.930 7,434 3,918 52,054 0.875150 0.4088 0.0291 14.07 0.986 8,161 727 51,327 0.863256 1.1794 0.1160 10.17 0.974 9,477 1,315 50,012 0.841
- - - - 0.960 11,477 2,000 48,011 0.807167 0.3379 0.0253 13.36 0.927 14,985 3,508 44,504 0.748167 0.3379 0.0253 13.36 1.000 14,985 - 44,504 0.748119 0.4400 0.0309 14.23 0.986 15,600 615 43,889 0.738
0 0.0000 0.0172 0.00 0.979 16,516 916 42,973 0.722
CL CD Wn-1/Wn
Constraint Analysis as a Function of T/W and T/S
Constant Altitude/Speed Cruise (Ps=0)Input Source: This section describes where the initial input values are referenced from
Lapse Rate α 0.243478 αFuel/Payload β 0.9801 β At Cruising AltitudeLoad Factor n 1 n Level Flight n=1Gravity g 32.2 ft/s2 g EarthExcrescence Drag R 0 slug/ft3 R Gear retracted for level flightFreesteam Velocity Velocity 774.7048 ft/s VelocityDynamic Pressure q 167.18 psf q Calculated from Velocity and Ambient Conditions
Min Drag 0.017179
Drag Polar Coefficient 0.07 Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 156
Drag Polar Coefficient 0Vertical Velocity dh/dt 0 ft/s dh/dt zero, no change in altitudeVertical Acceleration dV/dt 0 ft/s2 dV/dt zero, no change in vertical accelerationAdditional InputsAltitude 42,000 ft Altitude Cruising Alt.
Temperature @ Alt, T -90.6 TemperaturBased on Standard Day AtmosphereDelta 0.1668 DeltaTheta 0.7116 ThetaSigma 0.2344 Sigma
Density ### DensityWeight 58,305 lbs Weight
459.00 ktsM 0.823 M Wings are swept to reduce compressibility in transonic regime
Max Cruise Speed, 550 kts (Ps=0)Input Source: This section describes where the initial input values are referenced from
Lapse Rate α 0.23888 αFuel/Payload β 0.9801 β At Cruising AltitudeLoad Factor n 1 n Level Flight n=1Gravity g 32.2 ft/s2 g EarthExcrescence Drag R 0 slug/ft3 R Gear retracted for level flightFreesteam Velocity Velocity 928.2955 ft/s VelocityDynamic Pressure q 240.04 psf q Calculated from Velocity and Ambient Conditions
Min Drag 0.019679
Drag Polar Coefficient 0.07 Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 156
Drag Polar Coefficient 0Vertical Velocity dh/dt 0 ft/s dh/dt zero, no change in altitudeVertical Acceleration dV/dt 0 ft/s2 dV/dt zero, no change in vertical accelerationAdditional InputsAltitude 42,000 ft Altitude Cruising Alt.
Temperature @ Alt, T -90.6 TemperaturBased on Standard Day AtmosphereDelta 0.1668 DeltaTheta 0.7116 ThetaSigma 0.2344 Sigma
Lapse Rate Based on High Bypass Ratio Turbofan Engine,
Optimum Cruise first guess assumed to be 459 knots, Fighter Example Problem,
CD0 CD0 Includes External Stores Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 118-122, 156, 166 for Fighters
K1 K1
K2 K2 Typically Zero, Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 156
o F
slugs/ft3
VCRUISE VCRUISE Optimum Cruise first guess assumed to be 459 knots, Fighter Example Problem, Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 62
Lapse Rate Based on High Bypass Ratio Turbofan Engine,
Specified in RFP -
CD0 CD0 Drag Include Compressibility for High Mach Number, and External Stores Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 118-122, 156, 166 for Fighters
K1 K1
K2 K2 Typically Zero, Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 156
o F
Density ### DensityWeight 58,305 lbs Weight
550.00 kts Velocity in knots for my ReferenceM 0.986 M Due to the High Mach number there will be additional drag due to Compressibility
Level Combat Corner Speed 275kts (Ps=0)Input Source: This section describes where the initial input values are referenced from
Lapse Rate α 0.688611 αFuel/Payload β 1 β Specified by RFP to be Max TOGWLoad Factor n 3.180281 n Sustained Turn will require a certain g value based on the turn rate, this can be calculated from source: Raymer, "Aircraft Design, A Conceptual Approach, 3rd Edition", 1999, pg 106Gravity g 32.2 ft/s2 g EarthExcrescence Drag R 0 slug/ft3 R Gear retractedFreesteam Velocity Velocity 464.1478 ft/s Velocity 275 knots min, provided by RFPDynamic Pressure q 256.04 psf q Calculated from Velocity and Ambient Conditions
Min Drag 0.017179
Drag Polar Coefficient 0.07 Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 156
Drag Polar Coefficient 0Vertical Velocity dh/dt 0 ft/s dh/dt zero, no change in altitudeVertical Acceleration dV/dt 0 ft/s2 dV/dt zero, no change in vertical accelerationAdditional InputsAltitude 0 ft Altitude
Temperature @ Alt, T 59.0 TemperaturBased on Standard Day AtmosphereDelta 1.0000 DeltaTheta 1.0000 ThetaSigma 1.0000 Sigma
Density ### DensityWeight 59,488 lbs Weight
275.00 kts 275 knots min, provided by RFPM 0.416 M
Service Ceiling, 45,000 ft. (100 ft/min)Input Source: This section describes where the initial input values are referenced from
Lapse Rate α 0.225354 αFuel/Payload β 1 β Specified by RFP to be Max TOGWLoad Factor n 1 n Level Flight n=1Gravity g 32.2 ft/s2 g EarthExcrescence Drag R 0 slug/ft3 R Gear retractedFreesteam Velocity Velocity 774.7048 ft/s Velocity Cruise VelocityDynamic Pressure q 147.49 psf q Calculated from Velocity and Ambient Conditions
Min Drag 0.017179
Drag Polar Coefficient 0.07 Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 156
Drag Polar Coefficient 0Vertical Velocity dh/dt 1.667 ft/s dh/dt Specified 100 ft/min capability at 45,000 ft (Service Ceiling) to allow for maneuver margin. Requirement from RFPVertical Acceleration dV/dt 0 ft/s2 dV/dt zero, no change in vertical accelerationAdditional InputsAltitude 45,000 ft Altitude Max Altitude
slugs/ft3
VCRUISE_MAX VCRUISE_MAX
Lapse Rate Based on High Bypass Ratio Turbofan Engine,
CD0 CD0 Includes External Stores Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 118-122, 156, 166 for Fighters
K1 K1
K2 K2 Typically Zero, Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 156
o F
slugs/ft3
VCRUISE VCRUISE
Lapse Rate Based on High Bypass Ratio Turbofan Engine,
CD0 CD0 Includes External Stores Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 118-122, 156, 166 for Fighters
K1 K1
K2 K2 Typically Zero, Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 156
Temperature @ Alt, T -101.2 TemperaturBased on Standard Day AtmosphereDelta 0.1429 DeltaTheta 0.6910 ThetaSigma 0.2068 Sigma
Density ### DensityWeight 59,488 lbs Weight
459.00 ktsM 0.835 M
Stall Speed, 100 knotsInput Source: This section describes where the initial input values are referenced from
Lapse Rate α 0.856454 αFuel/Payload β 1 β Specified by RFP to be Max TOGWLoad Factor n 1 n Level Flight n=1Gravity g 32.2 ft/s2 g EarthExcrescence Drag R 0 slug/ft3 R Gear retractedFreesteam Velocity Velocity 168.781 ft/s Velocity Stall Speed must be no greater then 100 knots @ SL Max TOGW, from RFPDynamic Pressure q 33.86 psf q Calculated from Velocity and Ambient Conditions
Min Drag 0.037179
Drag Polar Coefficient 0.07 Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 156
Drag Polar Coefficient 0Vertical Velocity dh/dt 0 ft/s dh/dt zero, no change in altitudeVertical Acceleration dV/dt 0 ft/s2 dV/dt zero, no change in vertical accelerationAdditional InputsAltitude 0 ft Altitude
Temperature @ Alt, T 59.0 TemperaturBased on Standard Day AtmosphereDelta 1.0000 DeltaTheta 1.0000 ThetaSigma 1.0000 Sigma
Density ### DensityWeight 59,488 lbs Weight
VSTALL 100.00 kts Stall Speed must be no greater then 100 knots @ SL Max TOGW, from RFPM 0.151 M
Rate of Climb,10,000 ft/minInput Source: This section describes where the initial input values are referenced from
Lapse Rate α 0.643503 αFuel/Payload β 1 β Specified by RFP to be Max TOGWLoad Factor n 1 n Level Flight n=1Gravity g 32.2 ft/s2 g EarthExcrescence Drag R 0 slug/ft3 R Gear retractedFreesteam Velocity Velocity 590.7335 ft/s VelocityDynamic Pressure q 414.74 psf q Calculated from Velocity and Ambient Conditions
Min Drag 0.017179
Drag Polar Coefficient 0.07 Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 156
Drag Polar Coefficient 0Vertical Velocity dh/dt 166.67 ft/s dh/dt Specified 10,000 ft/min capability at SL/Max TOGW, Requirement from RFP
o F
slugs/ft3
VCRUISE VCRUISE
Lapse Rate Based on High Bypass Ratio Turbofan Engine,
CD0 CD0 Includes Flaps Down, External Stores Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 118-122, 156, 166 for Fighters
K1 K1
K2 K2 Typically Zero, Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 156
o F
slugs/ft3
VSTALL
Lapse Rate Based on High Bypass Ratio Turbofan Engine,
Assume 10,000 ft/min climb (from RFP) and 350 knot ground speed during climb (from
CD0 CD0 Includes External Stores Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 118-122, 156, 166 for Fighters
K1 K1
K2 K2 Typically Zero, Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 156
Vertical Acceleration dV/dt 0 ft/s2 dV/dt zero, no change in vertical accelerationAdditional InputsAltitude 0 ft Altitude Max Altitude
Temperature @ Alt, T 59.0 TemperaturBased on Standard Day AtmosphereDelta 1.0000 DeltaTheta 1.0000 ThetaSigma 1.0000 Sigma
Density ### DensityWeight 59,488 lbs Weight
350.00 ktsM 0.529 M
Sustained Turn Rate 12deg./sInput Source: This section describes where the initial input values are referenced from
Lapse Rate α 0.449458 αFuel/Payload β 0.75 β Specified by RFP to be 75% of Max TOGWLoad Factor n 5.137207 n Sustained Turn will require a certain g value based on the turn rate, this can be calculated from source: Raymer, "Aircraft Design, A Conceptual Approach, 3rd Edition", 1999, pg 106Gravity g 32.2 ft/s2 g EarthExcrescence Drag R 0 slug/ft3 R Gear retractedFreesteam Velocity Velocity 774.7048 ft/s Velocity 459 cruise speed, but max speed is 550Dynamic Pressure q 448.76 psf q Calculated from Velocity and Ambient Conditions
Min Drag 0.017179
Drag Polar Coefficient 0.07 Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 156
Drag Polar Coefficient 0Vertical Velocity dh/dt 0 ft/s dh/dt zero, no change in altitudeVertical Acceleration dV/dt 0 ft/s2 dV/dt zero, no change in vertical accelerationAdditional InputsAltitude 15,000 ft Altitude Specified by RFT
Temperature @ Alt, T 5.6 TemperaturBased on Standard Day AtmosphereDelta 0.5643 DeltaTheta 0.8970 ThetaSigma 0.6292 Sigma
Density ### DensityWeight 44,616 lbs Weight
459.00 kts 459 cruise speed, but max speed is 550M 0.733 M
Takeoff Ground RollInput Source: This section describes where the initial input values are referenced from
Lapse Rate α 0.852729 αFuel/Payload β 1 β Take off is max Take off wieght Beta = 1Load Factor n 1 nGravity g 32.2 ft/s2 g EarthExcrescence Drag R 0.01 slug/ft3 R Gear Down, 10 sq.ft for landing gearFreesteam Velocity Velocity 173.8444 ft/s Velocity Speed for Take offDynamic Pressure q 35.92 psf q Calculated from Velocity and Ambient Conditions
Min Drag 0.037179
Drag Polar Coefficient 0.07 Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 156
o F
slugs/ft3
VCLIMB VCLIMB Assume 10,000 ft/min climb (from RFP) and 350 knot ground speed during climb (from Roskam page 62); therefore, Rclimb = Alt./(10K/min)*350knots
Lapse Rate Based on High Bypass Ratio Turbofan Engine,
CD0 CD0 Includes External Stores Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 118-122, 156, 166 for Fighters
K1 K1
K2 K2 Typically Zero, Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 156
o F
slugs/ft3
VCRUISE VCRUISE
Lapse Rate Based on High Bypass Ratio Turbofan Engine,
CD0 CD0 Must have Flaps, Includes External Stores Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 118-122, 156, 166 for Fighters
K1 K1
Drag Polar Coefficient 0Vertical Velocity dh/dt 0 ft/s dh/dt zero, no change in altitudeVertical Acceleration dV/dt 0 ft/s2 dV/dt zero, no change in vertical accelerationAdditional InputsAltitude 0 ft Altitude Specified by RFT
Temperature @ Alt, T 59.0 TemperaturBased on Standard Day AtmosphereDelta 1.0000 DeltaTheta 1.0000 ThetaSigma 1.0000 Sigma
Density ### DensityWeight 59,488 lbs WeightCLMAX 1.900 CLMAX Weight and Speed at Take off to make CLMAX=1.9, Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 185
103.00 kts VTO Speed for Take offM 0.156 M
0.025Distance 2000 ft s_takeoff Required in RFPkto 1.2tr 3 s
Landing DistanceInput Source: This section describes where the initial input values are referenced from
Lapse Rate α 0.852729 αFuel/Payload β 0.737769 β Landing distance is based on the weight at the end of the mission, therefore, the beta chosen reflects the end of the mission before the reserve loiterLoad Factor n 1 n Sustained Turn will require a certain g value based on the turn rate, this can be calculated from source: Raymer, "Aircraft Design, A Conceptual Approach, 3rd Edition", 1999, pg 106Gravity g 32.2 ft/s2 g EarthExcrescence Drag R 0.01 slug/ft3 R Gear Down, 10 sq.ft for landing gearFreesteam Velocity Velocity 173.8444 ft/s Velocity Speed for Take offDynamic Pressure q 35.92 psf q Calculated from Velocity and Ambient Conditions
Min Drag 0.037179
Drag Polar Coefficient 0.07 Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 156
Drag Polar Coefficient 0Vertical Velocity dh/dt 0 ft/s dh/dt zero, no change in altitudeVertical Acceleration dV/dt 0 ft/s2 dV/dt zero, no change in vertical accelerationAdditional InputsAltitude 0 ft Altitude Specified by RFT
Temperature @ Alt, T 59.0 TemperaturBased on Standard Day AtmosphereDelta 1.0000 DeltaTheta 1.0000 ThetaSigma 1.0000 Sigma
Density ### DensityWeight 43,889 lbs WeightCLMAX 1.900 CLMAX Weight and Speed at Take off to make CLMAX=1.9, Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 185VL 103.00 kts VTO Speed for Take offM 0.156 M
0.025SFL 2000 ft s_landing Required in RFPkto 1.2tr 3 s
K2 K2 Typically Zero, Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 156
o F
slugs/ft3
VTO
μg μg Hot Runway Coefficient of Friction Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 185
K for take off, Source: Hernando Jimenez - "An Energy Based Approach to Aircraft Constraint Analysis - Part 2), ASDL GA Tech, AE6343, Fall 20063 seconds for rotation, typical for most fighters,
Lapse Rate Based on High Bypass Ratio Turbofan Engine,
CD0 CD0 Must have Flaps, Includes External Stores Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 118-122, 156, 166 for Fighters
K1 K1
K2 K2 Typically Zero, Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 156
o F
slugs/ft3
μg μg Hot Runway Coefficient of Friction Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 185
K for take off, Source: Hernando Jimenez - "An Energy Based Approach to Aircraft Constraint Analysis - Part 2), ASDL GA Tech, AE6343, Fall 20063 seconds for rotation, typical for most fighters,
SL 3800 ft Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 187SFL 6333.333VA 158 kts^2VSL 131.4464 ktsVSL 221.8566 ft/s
Takeoff Ground Roll HOT DAYInput Source: This section describes where the initial input values are referenced from
Lapse Rate α 0.811621 αFuel/Payload β 1 β Take off is max Take off wieght Beta = 1Load Factor n 1 nGravity g 32.2 ft/s2 g EarthExcrescence Drag R 0.01 slug/ft3 R Gear Down, 10 sq.ft for landing gearFreesteam Velocity Velocity 173.8444 ft/s Velocity Speed for Take offDynamic Pressure q 32.70 psf q Calculated from Velocity and Ambient Conditions
Min Drag 0.037179
Drag Polar Coefficient 0.07 Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 156
Drag Polar Coefficient 0Vertical Velocity dh/dt 0 ft/s dh/dt zero, no change in altitudeVertical Acceleration dV/dt 0 ft/s2 dV/dt zero, no change in vertical accelerationAdditional InputsAltitude 0 ft Altitude Specified by RFT
Temperature @ Alt, T 110.0 TemperaturAfghanistan at sea level can reach tempratures of 110 °FDelta 1.0000 DeltaTheta 1.0983 ThetaSigma 0.9105 Sigma
Density ### DensityWeight 59,488 lbs WeightCLMAX 1.900 CLMAX Weight and Speed at Take off to make CLMAX=1.9, Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 185
103.00 kts VTO Speed for Take offM 0.149 M
0.025Distance 2000 ft s_takeoff Required in RFPkto 1.2tr 3 s
Lapse Rate Based on High Bypass Ratio Turbofan Engine,
CD0 CD0 Must have Flaps, Includes External Stores Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 118-122, 156, 166 for Fighters
K1 K1
K2 K2 Typically Zero, Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 156
o F
slugs/ft3
VTO
μg μg Hot Runway Coefficient of Friction Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 185
K for take off, Source: Hernando Jimenez - "An Energy Based Approach to Aircraft Constraint Analysis - Part 2), ASDL GA Tech, AE6343, Fall 20063 seconds for rotation, typical for most fighters,
Source: This section describes where the initial input values are referenced from
At Cruising AltitudeLevel Flight n=1
Gear retracted for level flight
Calculated from Velocity and Ambient Conditions
Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 156
zero, no change in altitudezero, no change in vertical acceleration
Cruising Alt.
Based on Standard Day Atmosphere
Wings are swept to reduce compressibility in transonic regime
Source: This section describes where the initial input values are referenced from
At Cruising AltitudeLevel Flight n=1
Gear retracted for level flight
Calculated from Velocity and Ambient Conditions
Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 156
zero, no change in altitudezero, no change in vertical acceleration
Cruising Alt.
Based on Standard Day Atmosphere
Lapse Rate Based on High Bypass Ratio Turbofan Engine, Source: Hernando Jimenez - "An Energy Based Approach to Aircraft Constraint Analysis - Part 2), ASDL GA Tech, AE6343, Fall 2006
Optimum Cruise first guess assumed to be 459 knots, Fighter Example Problem, Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 62
Includes External Stores Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 118-122, 156, 166 for Fighters
Typically Zero, Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 156
Optimum Cruise first guess assumed to be 459 knots, Fighter Example Problem, Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 62
Lapse Rate Based on High Bypass Ratio Turbofan Engine, Source: Hernando Jimenez - "An Energy Based Approach to Aircraft Constraint Analysis - Part 2), ASDL GA Tech, AE6343, Fall 2006
Specified in RFP - "2006-2007 AIAA Graduate Team Aircraft Design Competition - Modified", AE 6343, Project 1, Fall 2007
Drag Include Compressibility for High Mach Number, and External Stores Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 118-122, 156, 166 for Fighters
Typically Zero, Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 156
Velocity in knots for my ReferenceDue to the High Mach number there will be additional drag due to Compressibility
Source: This section describes where the initial input values are referenced from
Specified by RFP to be Max TOGWSustained Turn will require a certain g value based on the turn rate, this can be calculated from source: Raymer, "Aircraft Design, A Conceptual Approach, 3rd Edition", 1999, pg 106
Gear retracted275 knots min, provided by RFPCalculated from Velocity and Ambient Conditions
Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 156
zero, no change in altitudezero, no change in vertical acceleration
Based on Standard Day Atmosphere
275 knots min, provided by RFP
Source: This section describes where the initial input values are referenced from
Specified by RFP to be Max TOGWLevel Flight n=1
Gear retractedCruise VelocityCalculated from Velocity and Ambient Conditions
Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 156
Specified 100 ft/min capability at 45,000 ft (Service Ceiling) to allow for maneuver margin. Requirement from RFPzero, no change in vertical acceleration
Max Altitude
Lapse Rate Based on High Bypass Ratio Turbofan Engine, Source: Hernando Jimenez - "An Energy Based Approach to Aircraft Constraint Analysis - Part 2), ASDL GA Tech, AE6343, Fall 2006
Includes External Stores Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 118-122, 156, 166 for Fighters
Typically Zero, Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 156
Lapse Rate Based on High Bypass Ratio Turbofan Engine, Source: Hernando Jimenez - "An Energy Based Approach to Aircraft Constraint Analysis - Part 2), ASDL GA Tech, AE6343, Fall 2006
Includes External Stores Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 118-122, 156, 166 for Fighters
Typically Zero, Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 156
Based on Standard Day Atmosphere
Source: This section describes where the initial input values are referenced from
Specified by RFP to be Max TOGWLevel Flight n=1
Gear retractedStall Speed must be no greater then 100 knots @ SL Max TOGW, from RFPCalculated from Velocity and Ambient Conditions
Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 156
zero, no change in altitudezero, no change in vertical acceleration
Based on Standard Day Atmosphere
Stall Speed must be no greater then 100 knots @ SL Max TOGW, from RFP
Source: This section describes where the initial input values are referenced from
Specified by RFP to be Max TOGWLevel Flight n=1
Gear retracted
Calculated from Velocity and Ambient Conditions
Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 156
Specified 10,000 ft/min capability at SL/Max TOGW, Requirement from RFP
Lapse Rate Based on High Bypass Ratio Turbofan Engine, Source: Hernando Jimenez - "An Energy Based Approach to Aircraft Constraint Analysis - Part 2), ASDL GA Tech, AE6343, Fall 2006
Includes Flaps Down, External Stores Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 118-122, 156, 166 for Fighters
Typically Zero, Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 156
Lapse Rate Based on High Bypass Ratio Turbofan Engine, Source: Hernando Jimenez - "An Energy Based Approach to Aircraft Constraint Analysis - Part 2), ASDL GA Tech, AE6343, Fall 2006
Assume 10,000 ft/min climb (from RFP) and 350 knot ground speed during climb (from Roskam page 62
Includes External Stores Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 118-122, 156, 166 for Fighters
Typically Zero, Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 156
zero, no change in vertical acceleration
Max Altitude
Based on Standard Day Atmosphere
Source: This section describes where the initial input values are referenced from
Specified by RFP to be 75% of Max TOGWSustained Turn will require a certain g value based on the turn rate, this can be calculated from source: Raymer, "Aircraft Design, A Conceptual Approach, 3rd Edition", 1999, pg 106
Gear retracted459 cruise speed, but max speed is 550Calculated from Velocity and Ambient Conditions
Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 156
zero, no change in altitudezero, no change in vertical acceleration
Specified by RFT
Based on Standard Day Atmosphere
459 cruise speed, but max speed is 550
Source: This section describes where the initial input values are referenced from
Take off is max Take off wieght Beta = 1
Gear Down, 10 sq.ft for landing gearSpeed for Take offCalculated from Velocity and Ambient Conditions
Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 156
Assume 10,000 ft/min climb (from RFP) and 350 knot ground speed during climb (from Roskam page 62); therefore, Rclimb = Alt./(10K/min)*350knots
Lapse Rate Based on High Bypass Ratio Turbofan Engine, Source: Hernando Jimenez - "An Energy Based Approach to Aircraft Constraint Analysis - Part 2), ASDL GA Tech, AE6343, Fall 2006
Includes External Stores Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 118-122, 156, 166 for Fighters
Typically Zero, Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 156
Lapse Rate Based on High Bypass Ratio Turbofan Engine, Source: Hernando Jimenez - "An Energy Based Approach to Aircraft Constraint Analysis - Part 2), ASDL GA Tech, AE6343, Fall 2006
Must have Flaps, Includes External Stores Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 118-122, 156, 166 for Fighters
zero, no change in altitudezero, no change in vertical acceleration
Specified by RFT
Based on Standard Day Atmosphere
Weight and Speed at Take off to make CLMAX=1.9, Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 185
Speed for Take off
Required in RFP
Source: This section describes where the initial input values are referenced from
Landing distance is based on the weight at the end of the mission, therefore, the beta chosen reflects the end of the mission before the reserve loiterSustained Turn will require a certain g value based on the turn rate, this can be calculated from source: Raymer, "Aircraft Design, A Conceptual Approach, 3rd Edition", 1999, pg 106
Gear Down, 10 sq.ft for landing gearSpeed for Take offCalculated from Velocity and Ambient Conditions
Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 156
zero, no change in altitudezero, no change in vertical acceleration
Specified by RFT
Based on Standard Day Atmosphere
Weight and Speed at Take off to make CLMAX=1.9, Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 185Speed for Take off
Required in RFP
Typically Zero, Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 156
Hot Runway Coefficient of Friction Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 185
K for take off, Source: Hernando Jimenez - "An Energy Based Approach to Aircraft Constraint Analysis - Part 2), ASDL GA Tech, AE6343, Fall 20063 seconds for rotation, typical for most fighters, Source: Hernando Jimenez - "An Energy Based Approach to Aircraft Constraint Analysis - Part 2), ASDL GA Tech, AE6343, Fall 2006
Lapse Rate Based on High Bypass Ratio Turbofan Engine, Source: Hernando Jimenez - "An Energy Based Approach to Aircraft Constraint Analysis - Part 2), ASDL GA Tech, AE6343, Fall 2006
Must have Flaps, Includes External Stores Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 118-122, 156, 166 for Fighters
Typically Zero, Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 156
Hot Runway Coefficient of Friction Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 185
K for take off, Source: Hernando Jimenez - "An Energy Based Approach to Aircraft Constraint Analysis - Part 2), ASDL GA Tech, AE6343, Fall 20063 seconds for rotation, typical for most fighters, Source: Hernando Jimenez - "An Energy Based Approach to Aircraft Constraint Analysis - Part 2), ASDL GA Tech, AE6343, Fall 2006
Source: This section describes where the initial input values are referenced from
Take off is max Take off wieght Beta = 1
Gear Down, 10 sq.ft for landing gearSpeed for Take offCalculated from Velocity and Ambient Conditions
Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 156
zero, no change in altitudezero, no change in vertical acceleration
Specified by RFT
Afghanistan at sea level can reach tempratures of 110 °F
Weight and Speed at Take off to make CLMAX=1.9, Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 185
Speed for Take off
Required in RFP
Lapse Rate Based on High Bypass Ratio Turbofan Engine, Source: Hernando Jimenez - "An Energy Based Approach to Aircraft Constraint Analysis - Part 2), ASDL GA Tech, AE6343, Fall 2006
Must have Flaps, Includes External Stores Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 118-122, 156, 166 for Fighters
Typically Zero, Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 156
Hot Runway Coefficient of Friction Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 185
K for take off, Source: Hernando Jimenez - "An Energy Based Approach to Aircraft Constraint Analysis - Part 2), ASDL GA Tech, AE6343, Fall 20063 seconds for rotation, typical for most fighters, Source: Hernando Jimenez - "An Energy Based Approach to Aircraft Constraint Analysis - Part 2), ASDL GA Tech, AE6343, Fall 2006
Source: Hernando Jimenez - "An Energy Based Approach to Aircraft Constraint Analysis - Part 2), ASDL GA Tech, AE6343, Fall 2006
Optimum Cruise first guess assumed to be 459 knots, Fighter Example Problem, Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 62
Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 118-122, 156, 166 for Fighters
Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 156
Optimum Cruise first guess assumed to be 459 knots, Fighter Example Problem, Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 62
Source: Hernando Jimenez - "An Energy Based Approach to Aircraft Constraint Analysis - Part 2), ASDL GA Tech, AE6343, Fall 2006
"2006-2007 AIAA Graduate Team Aircraft Design Competition - Modified", AE 6343, Project 1, Fall 2007
Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 118-122, 156, 166 for Fighters
Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 156
Sustained Turn will require a certain g value based on the turn rate, this can be calculated from source: Raymer, "Aircraft Design, A Conceptual Approach, 3rd Edition", 1999, pg 106
Specified 100 ft/min capability at 45,000 ft (Service Ceiling) to allow for maneuver margin. Requirement from RFP
Source: Hernando Jimenez - "An Energy Based Approach to Aircraft Constraint Analysis - Part 2), ASDL GA Tech, AE6343, Fall 2006
Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 118-122, 156, 166 for Fighters
Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 156
Source: Hernando Jimenez - "An Energy Based Approach to Aircraft Constraint Analysis - Part 2), ASDL GA Tech, AE6343, Fall 2006
Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 118-122, 156, 166 for Fighters
Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 156
Source: Hernando Jimenez - "An Energy Based Approach to Aircraft Constraint Analysis - Part 2), ASDL GA Tech, AE6343, Fall 2006
Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 118-122, 156, 166 for Fighters
Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 156
Source: Hernando Jimenez - "An Energy Based Approach to Aircraft Constraint Analysis - Part 2), ASDL GA Tech, AE6343, Fall 2006
Assume 10,000 ft/min climb (from RFP) and 350 knot ground speed during climb (from Roskam page 62); therefore, Rclimb = Alt./(10K/min)*350knots
Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 118-122, 156, 166 for Fighters
Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 156
Sustained Turn will require a certain g value based on the turn rate, this can be calculated from source: Raymer, "Aircraft Design, A Conceptual Approach, 3rd Edition", 1999, pg 106
Assume 10,000 ft/min climb (from RFP) and 350 knot ground speed during climb (from Roskam page 62); therefore, Rclimb = Alt./(10K/min)*350knots
Source: Hernando Jimenez - "An Energy Based Approach to Aircraft Constraint Analysis - Part 2), ASDL GA Tech, AE6343, Fall 2006
Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 118-122, 156, 166 for Fighters
Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 156
Source: Hernando Jimenez - "An Energy Based Approach to Aircraft Constraint Analysis - Part 2), ASDL GA Tech, AE6343, Fall 2006
Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 118-122, 156, 166 for Fighters
Weight and Speed at Take off to make CLMAX=1.9, Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 185
Landing distance is based on the weight at the end of the mission, therefore, the beta chosen reflects the end of the mission before the reserve loiterSustained Turn will require a certain g value based on the turn rate, this can be calculated from source: Raymer, "Aircraft Design, A Conceptual Approach, 3rd Edition", 1999, pg 106
Weight and Speed at Take off to make CLMAX=1.9, Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 185
Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 156
Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 185
Source: Hernando Jimenez - "An Energy Based Approach to Aircraft Constraint Analysis - Part 2), ASDL GA Tech, AE6343, Fall 2006Source: Hernando Jimenez - "An Energy Based Approach to Aircraft Constraint Analysis - Part 2), ASDL GA Tech, AE6343, Fall 2006
Source: Hernando Jimenez - "An Energy Based Approach to Aircraft Constraint Analysis - Part 2), ASDL GA Tech, AE6343, Fall 2006
Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 118-122, 156, 166 for Fighters
Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 156
Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 185
Source: Hernando Jimenez - "An Energy Based Approach to Aircraft Constraint Analysis - Part 2), ASDL GA Tech, AE6343, Fall 2006Source: Hernando Jimenez - "An Energy Based Approach to Aircraft Constraint Analysis - Part 2), ASDL GA Tech, AE6343, Fall 2006
Weight and Speed at Take off to make CLMAX=1.9, Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 185
Source: Hernando Jimenez - "An Energy Based Approach to Aircraft Constraint Analysis - Part 2), ASDL GA Tech, AE6343, Fall 2006
Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 118-122, 156, 166 for Fighters
Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 156
Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 185
Source: Hernando Jimenez - "An Energy Based Approach to Aircraft Constraint Analysis - Part 2), ASDL GA Tech, AE6343, Fall 2006Source: Hernando Jimenez - "An Energy Based Approach to Aircraft Constraint Analysis - Part 2), ASDL GA Tech, AE6343, Fall 2006
Output
W/S T/W (Lift T/W (Line T/W (Profi dh/dt dV/dt T/W Total10 0.01676 0.00000 1.17956 0.00000 0.00000 1.196320 0.03352 0.00000 0.58978 0.00000 0.00000 0.623330 0.05028 0.00000 0.39319 0.00000 0.00000 0.443540 0.06704 0.00000 0.29489 0.00000 0.00000 0.361950 0.08381 0.00000 0.23591 0.00000 0.00000 0.319760 0.10057 0.00000 0.19659 0.00000 0.00000 0.2972
70 0.11733 0.00000 0.16851 0.00000 0.00000 0.2858
80 0.13409 0.00000 0.14745 0.00000 0.00000 0.2815
90 0.15085 0.00000 0.13106 0.00000 0.00000 0.2819100 0.16761 0.00000 0.11796 0.00000 0.00000 0.2856110 0.18437 0.00000 0.10723 0.00000 0.00000 0.2916120 0.20113 0.00000 0.09830 0.00000 0.00000 0.2994130 0.21789 0.00000 0.09074 0.00000 0.00000 0.3086
140 0.23466 0.00000 0.08425 0.00000 0.00000 0.3189150 0.25142 0.00000 0.07864 0.00000 0.00000 0.3301160 0.26818 0.00000 0.07372 0.00000 0.00000 0.3419170 0.28494 0.00000 0.06939 0.00000 0.00000 0.3543
180 0.30170 0.00000 0.06553 0.00000 0.00000 0.3672190 0.31846 0.00000 0.06208 0.00000 0.00000 0.3805
200 0.33522 0.00000 0.05898 0.00000 0.00000 0.3942
Output
W/S T/W (Lift T/W (Line T/W (Profi dh/dt dV/dt T/W Total10 0.01190 0.00000 1.97745 0.00000 0.00000 1.989320 0.02380 0.00000 0.98872 0.00000 0.00000 1.012530 0.03569 0.00000 0.65915 0.00000 0.00000 0.694840 0.04759 0.00000 0.49436 0.00000 0.00000 0.542050 0.05949 0.00000 0.39549 0.00000 0.00000 0.455060 0.07139 0.00000 0.32957 0.00000 0.00000 0.4010
70 0.08329 0.00000 0.28249 0.00000 0.00000 0.3658
80 0.09519 0.00000 0.24718 0.00000 0.00000 0.3424
90 0.10708 0.00000 0.21972 0.00000 0.00000 0.3268100 0.11898 0.00000 0.19774 0.00000 0.00000 0.3167110 0.13088 0.00000 0.17977 0.00000 0.00000 0.3106120 0.14278 0.00000 0.16479 0.00000 0.00000 0.3076130 0.15468 0.00000 0.15211 0.00000 0.00000 0.3068
140 0.16658 0.00000 0.14125 0.00000 0.00000 0.3078150 0.17847 0.00000 0.13183 0.00000 0.00000 0.3103160 0.19037 0.00000 0.12359 0.00000 0.00000 0.3140170 0.20227 0.00000 0.11632 0.00000 0.00000 0.3186
180 0.21417 0.00000 0.10986 0.00000 0.00000 0.3240190 0.22607 0.00000 0.10408 0.00000 0.00000 0.3301
200 0.23796 0.00000 0.09887 0.00000 0.00000 0.3368
Output
W/S T/W (Lift T/W (Line T/W (Profi dh/dt dV/dt T/W Total10 0.04074 0.00000 0.63877 0.00000 0.00000 0.679520 0.08148 0.00000 0.31938 0.00000 0.00000 0.400930 0.12223 0.00000 0.21292 0.00000 0.00000 0.335140 0.16297 0.00000 0.15969 0.00000 0.00000 0.322750 0.20371 0.00000 0.12775 0.00000 0.00000 0.331560 0.24445 0.00000 0.10646 0.00000 0.00000 0.3509
70 0.28519 0.00000 0.09125 0.00000 0.00000 0.3764
80 0.32594 0.00000 0.07985 0.00000 0.00000 0.4058
90 0.36668 0.00000 0.07097 0.00000 0.00000 0.4377100 0.40742 0.00000 0.06388 0.00000 0.00000 0.4713110 0.44816 0.00000 0.05807 0.00000 0.00000 0.5062120 0.48891 0.00000 0.05323 0.00000 0.00000 0.5421130 0.52965 0.00000 0.04914 0.00000 0.00000 0.5788
140 0.57039 0.00000 0.04563 0.00000 0.00000 0.6160150 0.61113 0.00000 0.04258 0.00000 0.00000 0.6537160 0.65187 0.00000 0.03992 0.00000 0.00000 0.6918170 0.69262 0.00000 0.03757 0.00000 0.00000 0.7302
180 0.73336 0.00000 0.03549 0.00000 0.00000 0.7688190 0.77410 0.00000 0.03362 0.00000 0.00000 0.8077
200 0.81484 0.00000 0.03194 0.00000 0.00000 0.8468
Output
W/S T/W (Lift T/W (Line T/W (Profi dh/dt dV/dt T/W Total10 0.02137 0.00000 1.12433 0.00955 0.00000 1.155220 0.04274 0.00000 0.56216 0.00955 0.00000 0.614430 0.06411 0.00000 0.37478 0.00955 0.00000 0.448440 0.08547 0.00000 0.28108 0.00955 0.00000 0.376150 0.10684 0.00000 0.22487 0.00955 0.00000 0.341360 0.12821 0.00000 0.18739 0.00955 0.00000 0.3251
70 0.14958 0.00000 0.16062 0.00955 0.00000 0.3197
80 0.17095 0.00000 0.14054 0.00955 0.00000 0.3210
90 0.19232 0.00000 0.12493 0.00955 0.00000 0.3268100 0.21369 0.00000 0.11243 0.00955 0.00000 0.3357110 0.23506 0.00000 0.10221 0.00955 0.00000 0.3468120 0.25642 0.00000 0.09369 0.00955 0.00000 0.3597130 0.27779 0.00000 0.08649 0.00955 0.00000 0.3738
140 0.29916 0.00000 0.08031 0.00955 0.00000 0.3890150 0.32053 0.00000 0.07496 0.00955 0.00000 0.4050160 0.34190 0.00000 0.07027 0.00955 0.00000 0.4217170 0.36327 0.00000 0.06614 0.00955 0.00000 0.4390
180 0.38464 0.00000 0.06246 0.00955 0.00000 0.4566190 0.40601 0.00000 0.05918 0.00955 0.00000 0.4747
200 0.42737 0.00000 0.05622 0.00955 0.00000 0.4931
Output
W/S T/W (Lift T/W (Line T/W (Profi dh/dt dV/dt T/W Total10 0.02449 0.00000 0.14697 0.00000 0.00000 0.171520 0.04899 0.00000 0.07349 0.00000 0.00000 0.122530 0.07348 0.00000 0.04899 0.00000 0.00000 0.122540 0.09797 0.00000 0.03674 0.00000 0.00000 0.134750 0.12247 0.00000 0.02939 0.00000 0.00000 0.151960 0.14696 0.00000 0.02450 0.00000 0.00000 0.1715
70 0.17145 0.00000 0.02100 0.00000 0.00000 0.1924
80 0.19595 0.00000 0.01837 0.00000 0.00000 0.2143
90 0.22044 0.00000 0.01633 0.00000 0.00000 0.2368100 0.24493 0.00000 0.01470 0.00000 0.00000 0.2596110 0.26943 0.00000 0.01336 0.00000 0.00000 0.2828120 0.29392 0.00000 0.01225 0.00000 0.00000 0.3062130 0.31841 0.00000 0.01131 0.00000 0.00000 0.3297
140 0.34291 0.00000 0.01050 0.00000 0.00000 0.3534150 0.36740 0.00000 0.00980 0.00000 0.00000 0.3772160 0.39189 0.00000 0.00919 0.00000 0.00000 0.4011170 0.41639 0.00000 0.00865 0.00000 0.00000 0.4250
180 0.44088 0.00000 0.00817 0.00000 0.00000 0.4490190 0.46537 0.00000 0.00774 0.00000 0.00000 0.4731
200 0.48987 0.00000 0.00735 0.00000 0.00000 0.4972
Output
W/S T/W (Lift T/W (Line T/W (Profi dh/dt dV/dt T/W Total10 0.00266 0.00000 1.10723 0.43844 0.00000 1.548320 0.00532 0.00000 0.55361 0.43844 0.00000 0.997430 0.00798 0.00000 0.36908 0.43844 0.00000 0.815540 0.01064 0.00000 0.27681 0.43844 0.00000 0.725950 0.01331 0.00000 0.22145 0.43844 0.00000 0.673260 0.01597 0.00000 0.18454 0.43844 0.00000 0.6389
70 0.01863 0.00000 0.15818 0.43844 0.00000 0.6152
80 0.02129 0.00000 0.13840 0.43844 0.00000 0.5981
90 0.02395 0.00000 0.12303 0.43844 0.00000 0.5854100 0.02661 0.00000 0.11072 0.43844 0.00000 0.5758
110 0.02927 0.00000 0.10066 0.43844 0.00000 0.5684120 0.03193 0.00000 0.09227 0.43844 0.00000 0.5626130 0.03459 0.00000 0.08517 0.43844 0.00000 0.5582
140 0.03726 0.00000 0.07909 0.43844 0.00000 0.5548150 0.03992 0.00000 0.07382 0.43844 0.00000 0.5522160 0.04258 0.00000 0.06920 0.43844 0.00000 0.5502170 0.04524 0.00000 0.06513 0.43844 0.00000 0.5488
180 0.04790 0.00000 0.06151 0.43844 0.00000 0.5478190 0.05056 0.00000 0.05828 0.43844 0.00000 0.5473
200 0.05322 0.00000 0.05536 0.43844 0.00000 0.5470
Output
W/S T/W (Lift T/W (Line T/W (Profi dh/dt dV/dt T/W Total10 0.05227 0.00000 1.71525 0.00000 0.00000 1.767520 0.10454 0.00000 0.85763 0.00000 0.00000 0.962230 0.15682 0.00000 0.57175 0.00000 0.00000 0.728640 0.20909 0.00000 0.42881 0.00000 0.00000 0.637950 0.26136 0.00000 0.34305 0.00000 0.00000 0.604460 0.31363 0.00000 0.28588 0.00000 0.00000 0.5995
70 0.36591 0.00000 0.24504 0.00000 0.00000 0.6109
80 0.41818 0.00000 0.21441 0.00000 0.00000 0.6326
90 0.47045 0.00000 0.19058 0.00000 0.00000 0.6610100 0.52272 0.00000 0.17153 0.00000 0.00000 0.6942110 0.57500 0.00000 0.15593 0.00000 0.00000 0.7309120 0.62727 0.00000 0.14294 0.00000 0.00000 0.7702130 0.67954 0.00000 0.13194 0.00000 0.00000 0.8115
140 0.73181 0.00000 0.12252 0.00000 0.00000 0.8543150 0.78409 0.00000 0.11435 0.00000 0.00000 0.8984160 0.83636 0.00000 0.10720 0.00000 0.00000 0.9436170 0.88863 0.00000 0.10090 0.00000 0.00000 0.9895
180 0.94090 0.00000 0.09529 0.00000 0.00000 1.0362190 0.99318 0.00000 0.09028 0.00000 0.00000 1.0835
200 1.04545 0.00000 0.08576 0.00000 0.00000 1.1312
Output
W/S s (ft) T/W Total10 2,000 0.066030 2,000 0.219850 2,000 0.396570 2,000 0.595090 2,000 0.8157
110 2,000 1.0596
130 2,000 1.3286
150 2,000 1.6246
170 2,000 1.9502190 2,000 2.3085
Output
W/S s (ft) T/W Total76 2,000 0.000076 2,000 0.500076 2,000 1.000076 2,000 1.500076 2,000 2.0000
Find T/W to Equal Takeoff Length
Output
W/S s (ft) T/W Total10 2,000 0.076630 2,000 0.256850 2,000 0.465770 2,000 0.702290 2,000 0.9673
110 2,000 1.2627
130 2,000 1.5912
150 2,000 1.9560
170 2,000 2.3611190 2,000 2.8113
Find T/W to Equal Takeoff Length
n=5
T/W Total0.9622210.6160860.5606970.5779940.6243660.685275
0.754492
0.8289
0.9067690.9870611.0691161.1524921.236884
1.3220751.4079051.4942551.581032
1.6681651.755599
1.843287
Drag Polar
Ambient ConditonsUSER INPUTS CALCULATIONS
Flight Conditions Flight Conditions
486 ktas Temperature @ -90.562
Pressure Altit 42000 ft Delta 0.1668
Type of Day std std/trop/hot Theta 0.7116
Temperature, -90.562 Sigma 0.2344
Gravity, g 32.2 Density 5.571E-04
m 2.836E-07
n 5.090E-04
M 0.871
a, Speed of S 941.83 ft/sec
Airspeed, V 235.29 kcas
Airspeed, V 820.28 ft/sec
Aerodynamics Notes/SourSource: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 118 - 122W/S 70 psf Found using Constraint Analyisis
59,488 lbs Iteratively found using Mission AnalysisS 849.83 sq.ft. Wing Areab 69 ft SpanA 5.60 Aspect Ratioe_clean 0.8 Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 156e_flaps 0.7 Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 156q 187.42 psf Calculated from Ambient Flight ConditionK1 0.07 Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 118
0.37 Based on Speed and Alt. from above
0.0038
0.0200
0.0025
0.01341 Min Drag with No External Stores
0.027 Includes Stores
0.05 Includes Stores and Flaps Down, Oswald Eff = 0.7
0.02 No StoresL/D 13.79 Check against Table 2.2 from Roskamf 11.4 sq.ft. Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 118
2,850 sq.ft.cf 0.004 Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 120, figure 3.21b, fighters, cfa -2.3979 Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 122, table 3.4, fighters, cfb 1 Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 122, table 3.4, fightersc -0.1289 Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 122, table 3.5, fightersd 0.7506 Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 122, table 3.5, fightersn 1 g factor
Drag Polar
Airspeed, V o F
o F
ft2/sec slugs/ft3
ft2/sec
WTO
CL
CD_Stores 3.2 sq.ft. for Stores, Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 156
CD_FLAPS Flaps Down Zero Lift, Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 156
CD_Compressablity Compressablity, Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 166
CD0
CD
CD Takeoff
CD_Clean
SWET Wetted Area as a function of TO weight for fighters, Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 118
V V q M L/DKnots ft/s psf59.24838 100 3 0.1061768 25.1302 44.8698 0.56006974.06048 125 4 0.132721 16.0833 18.3888 0.87462588.87257 150 6 0.1592652 11.1690 8.8770 1.258199103.6847 175 9 0.1858094 8.2058 4.7995 1.709727118.4968 200 11 0.2123535 6.2825 2.8205 2.227484133.3089 225 14 0.2388977 4.9640 1.7673 2.808864
148.121 250 17 0.2654419 4.0208 1.1654 3.450153162.933 275 21 0.2919861 3.3230 0.8014 4.146319
177.7451 300 25 0.3185303 2.7922 0.5709 4.890819192.5572 325 29 0.3450745 2.3792 0.4192 5.675473207.3693 350 34 0.3716187 2.0514 0.3161 6.490428222.1814 375 39 0.3981629 1.7870 0.2440 7.324229236.9935 400 45 0.4247071 1.5706 0.1924 8.164036251.8056 425 50 0.4512513 1.3913 0.1547 8.995979266.6177 450 56 0.4777955 1.2410 0.1266 9.805658281.4298 475 63 0.5043397 1.1138 0.1053 10.57874296.2419 500 70 0.5308839 1.0052 0.0889 11.30164
311.054 525 77 0.5574281 0.9118 0.0762 11.96214325.8661 550 84 0.5839723 0.8307 0.0662 12.55340.6782 575 92 0.6105164 0.7601 0.0582 13.05741355.4903 600 100 0.6370606 0.6981 0.0518 13.47924370.3024 625 109 0.6636048 0.6433 0.0466 13.81315385.1145 650 118 0.690149 0.5948 0.0423 14.05942399.9266 675 127 0.7166932 0.5516 0.0388 14.22072414.7387 700 136 0.7432374 0.5129 0.0359 14.3017429.5508 725 146 0.7697816 0.4781 0.0334 14.30853444.3629 750 157 0.7963258 0.4468 0.0314 14.24842459.1749 775 167 0.82287 0.4184 0.0296 14.1292
473.987 800 178 0.8494142 0.3927 0.0281 13.9589488.7991 825 190 0.8759584 0.3692 0.0269 13.74542503.6112 850 201 0.9025026 0.3478 0.0258 13.49631518.4233 875 213 0.9290468 0.3282 0.0248 13.21861533.2354 900 226 0.955591 0.3102 0.0240 12.91867548.0475 925 238 0.9821351 0.2937 0.0233 12.60218562.8596 950 251 1.0086793 0.2785 0.0227 12.2741577.6717 975 265 1.0352235 0.2644 0.0221 11.93872592.4838 1000 279 1.0617677 0.2513 0.0217 11.59966607.2959 1025 293 1.0883119 0.2392 0.0212 11.25997
Max 14.308530.866xMax 12.39119
CL CD
- 0.03 0.05 0.08 0.10 0.13 0.15 0.18 0.20 -
0.2
0.4
0.6
0.8
1.0
1.2
1.4
Max L/D
CL
CD
Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 118 - 122
Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 156Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 156
Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 118
Includes Stores and Flaps Down, Oswald Eff = 0.7
Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 118
Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 120, figure 3.21b, fighters, cfSource: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 122, table 3.4, fighters, cfSource: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 122, table 3.4, fightersSource: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 122, table 3.5, fightersSource: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 122, table 3.5, fighters
Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 156
, Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 156
, Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 166
Wetted Area as a function of TO weight for fighters, Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 118
Compressibility Drag Rise
Fuel Fraction EstimatesSource: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 12
Cruise and Loiter Inputs for Bregeut Range EquationSource: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 14
Empty Weight Data for FightersSource: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", pg 27, 42, 43, 1985
Code ValidationSource: Georgia Tech, AE 6343 Fixed Wing Design Course, Fall 2007 Calculated using this Spreadsheet Tool
Validation Point 1Input
α 0.33 W/S T/W Lapse Rateβ 0.57 10 2.791 Fuel/Payloadn 2.6 20 1.5549 Load Factorg 32.2 ft/s2 30 1.168 GravityR 0.001832 slug/ft3 40 0.9933 Excrecence DragVelocity 695 ft/s 50 0.9035 Freesteam Velocityq 442.4509 psf 60 0.8562 Dynamic PressureCD0 0.019 70 0.8332 Min DragK1 0.25 80 0.8253 Drag Polar CoeffecientK2 0.005 90 0.8275 Drag Polar Coeffecientdh/dt 35 ft/s 100 0.8368 Vertical VelocitydV/dt 1.8 ft/s2 110 0.851247 Vertical Acceleration
120 0.869554130 0.890831140 0.91444150 0.939915160 0.966907170 0.995147180 1.024428190 1.054586200 1.085488
Validation Point 2Input
α 0.69 W/S T/W Lapse Rateβ 0.72 10 0.8555 Fuel/Payloadn 1 20 0.521 Load Factorg 32.2 ft/s2 30 0.4174 GravityR 0.001832 slug/ft3 40 0.3714 Excrecence DragVelocity 417 ft/s 50 0.3486 Freesteam Velocityq 159.2823 psf 60 0.3373 Dynamic PressureCD0 0.03 70 0.3326 Min DragK1 0.25 80 0.332 Drag Polar CoeffecientK2 0.005 90 0.3342 Drag Polar Coeffecientdh/dt 35 ft/s 100 0.3383 Vertical VelocitydV/dt 1.8 ft/s2 110 0.3438 Vertical Acceleration
120 0.350346130 0.357699140 0.365686150 0.37418160 0.383086
170 0.392332180 0.401861190 0.411628200 0.421598
Validation Point 3Input
α 0.69 W/S T/W Lapse Rateβ 0.72 10 1.2769 Fuel/Payloadn 1 20 0.6837 Load Factorg 32.2 ft/s2 30 0.4866 GravityR 0.001832 slug/ft3 40 0.3885 Excrecence DragVelocity 1338 ft/s 50 0.33 Freesteam Velocityq 1639.864 psf 60 0.2913 Dynamic PressureCD0 0.005 70 0.2639 Min DragK1 0.2 80 0.2436 Drag Polar CoeffecientK2 0.002 90 0.228 Drag Polar Coeffecientdh/dt 35 ft/s 100 0.2157 Vertical VelocitydV/dt 1.8 ft/s2 110 0.205821 Vertical Acceleration
120 0.197735130 0.191034140 0.185421150 0.180679160 0.176644170 0.173191180 0.170224190 0.167666200 0.165455
Validation Point 4Input
α 0.82 W/S T/W Lapse Rateβ 0.87 10 2.794 Fuel/Payloadn 1 20 1.413 Load Factorg 32.2 ft/s2 30 0.9586 GravityR 0.002315 slug/ft3 40 0.7359 Excrecence DragVelocity 1338 ft/s 50 0.6058 Freesteam Velocityq 2072.207 psf 60 0.5221 Dynamic PressureCD0 0.011 70 0.4648 Min DragK1 2 80 0.424 Drag Polar CoeffecientK2 0.005 90 0.3944 Drag Polar Coeffecientdh/dt 0 ft/s 100 0.3724 Vertical VelocitydV/dt 0 ft/s2 110 0.35601 Vertical Acceleration
120 0.34386130 0.33495140 0.328585150 0.324257160 0.321583
170 0.320272180 0.320097190 0.320878200 0.322471
Validation Point 5Input
α 0.91 W/S T/W Lapse Rateβ 0.34 10 2.5215 Fuel/Payloadn 3 20 1.2801 Load Factorg 32.2 ft/s2 30 0.8737 GravityR 0.002315 slug/ft3 40 0.676 Excrecence DragVelocity 1338 ft/s 50 0.5618 Freesteam Velocityq 2072.207 psf 60 0.4893 Dynamic PressureCD0 0.011 70 0.4407 Min DragK1 2 80 0.407 Drag Polar CoeffecientK2 0.005 90 0.3832 Drag Polar Coeffecientdh/dt 0 ft/s 100 0.3664 Vertical VelocitydV/dt 0 ft/s2 110 0.3547 Vertical Acceleration
120 0.346758130 0.341736140 0.339008150 0.338114160 0.338712170 0.340537180 0.343386190 0.347096200 0.351539
Calculated using this Spreadsheet Tool
Output
α 0.33 W/S T/W (Lift T/W (Line T/W (Profi dh/dt dV/dtβ 0.57 10 0.037606 0.022455 2.548 0.086985 0.096556n 2.6 20 0.075212 0.022455 1.274 0.086985 0.096556g 32.2 ft/s2 30 0.112818 0.022455 0.849333 0.086985 0.096556R 0.001832 slug/ft3 40 0.150424 0.022455 0.637 0.086985 0.096556
Velocity 695 ft/s 50 0.18803 0.022455 0.5096 0.086985 0.096556q 442.4509 psf 60 0.225636 0.022455 0.424667 0.086985 0.096556
CD0 0.019 70 0.263242 0.022455 0.364 0.086985 0.096556K1 0.25 80 0.300848 0.022455 0.3185 0.086985 0.096556K2 0.005 90 0.338454 0.022455 0.283111 0.086985 0.096556
dh/dt 35 ft/s 100 0.37606 0.022455 0.2548 0.086985 0.096556dV/dt 1.8 ft/s2 110 0.413666 0.022455 0.231636 0.086985 0.096556
120 0.451272 0.022455 0.212333 0.086985 0.096556130 0.488878 0.022455 0.196 0.086985 0.096556140 0.526484 0.022455 0.182 0.086985 0.096556150 0.56409 0.022455 0.169867 0.086985 0.096556160 0.601696 0.022455 0.15925 0.086985 0.096556170 0.639302 0.022455 0.149882 0.086985 0.096556180 0.676908 0.022455 0.141556 0.086985 0.096556190 0.714514 0.022455 0.134105 0.086985 0.096556200 0.75212 0.022455 0.1274 0.086985 0.096556
Output
α 0.69 W/S T/W (Lift T/W (Line T/W (Profi dh/dt dV/dtβ 0.72 10 0.011792 0.005217 0.692797 0.087582 0.058331n 1 20 0.023584 0.005217 0.346399 0.087582 0.058331g 32.2 ft/s2 30 0.035376 0.005217 0.230932 0.087582 0.058331R 0.001832 slug/ft3 40 0.047168 0.005217 0.173199 0.087582 0.058331
Velocity 417 ft/s 50 0.05896 0.005217 0.138559 0.087582 0.058331q 159.2823 psf 60 0.070752 0.005217 0.115466 0.087582 0.058331
CD0 0.03 70 0.082544 0.005217 0.098971 0.087582 0.058331K1 0.25 80 0.094336 0.005217 0.0866 0.087582 0.058331K2 0.005 90 0.106128 0.005217 0.076977 0.087582 0.058331
dh/dt 35 ft/s 100 0.11792 0.005217 0.06928 0.087582 0.058331dV/dt 1.8 ft/s2 110 0.129712 0.005217 0.062982 0.087582 0.058331
120 0.141504 0.005217 0.057733 0.087582 0.058331130 0.153296 0.005217 0.053292 0.087582 0.058331140 0.165088 0.005217 0.049486 0.087582 0.058331150 0.17688 0.005217 0.046186 0.087582 0.058331160 0.188672 0.005217 0.0433 0.087582 0.058331
170 0.200464 0.005217 0.040753 0.087582 0.058331180 0.212256 0.005217 0.038489 0.087582 0.058331190 0.224048 0.005217 0.036463 0.087582 0.058331200 0.235841 0.005217 0.03464 0.087582 0.058331
Output
α 0.69 W/S T/W (Lift T/W (Line T/W (Profi dh/dt dV/dtβ 0.72 10 0.000916 0.002087 1.188573 0.027296 0.058331n 1 20 0.001833 0.002087 0.594286 0.027296 0.058331g 32.2 ft/s2 30 0.002749 0.002087 0.396191 0.027296 0.058331R 0.001832 slug/ft3 40 0.003665 0.002087 0.297143 0.027296 0.058331
Velocity 1338 ft/s 50 0.004582 0.002087 0.237715 0.027296 0.058331q 1639.864 psf 60 0.005498 0.002087 0.198095 0.027296 0.058331
CD0 0.005 70 0.006414 0.002087 0.169796 0.027296 0.058331K1 0.2 80 0.00733 0.002087 0.148572 0.027296 0.058331K2 0.002 90 0.008247 0.002087 0.132064 0.027296 0.058331
dh/dt 35 ft/s 100 0.009163 0.002087 0.118857 0.027296 0.058331dV/dt 1.8 ft/s2 110 0.010079 0.002087 0.108052 0.027296 0.058331
120 0.010996 0.002087 0.099048 0.027296 0.058331130 0.011912 0.002087 0.091429 0.027296 0.058331140 0.012828 0.002087 0.084898 0.027296 0.058331150 0.013745 0.002087 0.079238 0.027296 0.058331160 0.014661 0.002087 0.074286 0.027296 0.058331170 0.015577 0.002087 0.069916 0.027296 0.058331180 0.016493 0.002087 0.066032 0.027296 0.058331190 0.01741 0.002087 0.062556 0.027296 0.058331200 0.018326 0.002087 0.059429 0.027296 0.058331
Output
α 0.82 W/S T/W (Lift T/W (Line T/W (Profi dh/dt dV/dtβ 0.87 10 0.008909 0.005305 2.780072 0 0n 1 20 0.017818 0.005305 1.390036 0 0g 32.2 ft/s2 30 0.026727 0.005305 0.926691 0 0R 0.002315 slug/ft3 40 0.035635 0.005305 0.695018 0 0
Velocity 1338 ft/s 50 0.044544 0.005305 0.556014 0 0q 2072.207 psf 60 0.053453 0.005305 0.463345 0 0
CD0 0.011 70 0.062362 0.005305 0.397153 0 0K1 2 80 0.071271 0.005305 0.347509 0 0K2 0.005 90 0.08018 0.005305 0.308897 0 0
dh/dt 0 ft/s 100 0.089088 0.005305 0.278007 0 0dV/dt 0 ft/s2 110 0.097997 0.005305 0.252734 0 0
120 0.106906 0.005305 0.231673 0 0130 0.115815 0.005305 0.213852 0 0140 0.124724 0.005305 0.198577 0 0150 0.133633 0.005305 0.185338 0 0160 0.142542 0.005305 0.173755 0 0
170 0.15145 0.005305 0.163534 0 0180 0.160359 0.005305 0.154448 0 0190 0.169268 0.005305 0.14632 0 0200 0.178177 0.005305 0.139004 0 0
Output
α 0.91 W/S T/W (Lift T/W (Line T/W (Profi dh/dt dV/dtβ 0.34 10 0.011035 0.005604 2.50512 0 0n 3 20 0.022069 0.005604 1.25256 0 0g 32.2 ft/s2 30 0.033104 0.005604 0.83504 0 0R 0.002315 slug/ft3 40 0.044138 0.005604 0.62628 0 0
Velocity 1338 ft/s 50 0.055173 0.005604 0.501024 0 0q 2072.207 psf 60 0.066207 0.005604 0.41752 0 0
CD0 0.011 70 0.077242 0.005604 0.357874 0 0K1 2 80 0.088277 0.005604 0.31314 0 0K2 0.005 90 0.099311 0.005604 0.278347 0 0
dh/dt 0 ft/s 100 0.110346 0.005604 0.250512 0 0dV/dt 0 ft/s2 110 0.12138 0.005604 0.227738 0 0
120 0.132415 0.005604 0.20876 0 0130 0.14345 0.005604 0.192702 0 0140 0.154484 0.005604 0.178937 0 0150 0.165519 0.005604 0.167008 0 0160 0.176553 0.005604 0.15657 0 0170 0.187588 0.005604 0.14736 0 0180 0.198622 0.005604 0.139173 0 0190 0.209657 0.005604 0.131848 0 0200 0.220692 0.005604 0.125256 0 0
T/W Total2.79161.55521.16810.99340.90360.85630.83320.82530.82760.83690.85130.86960.89090.91450.94000.96690.99521.02451.05461.0855
T/W Total0.85570.52110.41740.37150.34870.33730.33260.33210.33420.33830.34380.35040.35770.36570.37420.3831
0 20 40 60 80 100 120 140 160 180 2000.0
0.5
1.0
1.5
2.0
2.5
3.0
Validation Case 1: W/S and T/W
Calculated Using Mattingly - Master Equation
Provided Validation Points from GA TECH
W/S
T/W
0 20 40 60 80 100 120 140 160 180 2000.0
0.5
1.0
1.5
2.0
2.5
3.0
Validation Case 2: W/S and T/W
Calculated Using Mattingly - Master Equation
Provided Validation Points from GA TECH
W/S
T/W
0.39230.40190.41160.4216
T/W Total1.27720.68380.48670.38850.33000.29130.26390.24360.22800.21570.20580.19780.19110.18540.18070.17670.17320.17020.16770.1655
T/W Total2.79431.41320.95870.73600.60590.52210.46480.42410.39440.37240.35600.34390.33500.32860.32430.3216
0 20 40 60 80 100 120 140 160 180 2000.0
0.5
1.0
1.5
2.0
2.5
3.0
Validation Case 2: W/S and T/W
Calculated Using Mattingly - Master Equation
Provided Validation Points from GA TECH
W/S
T/W
0 20 40 60 80 100 120 140 160 180 2000.0
0.5
1.0
1.5
2.0
2.5
3.0
Validation Case 3: W/S and T/W
Calculated Using Mattingly - Master Equation
Provided Validation Points from GA TECH
W/S
T/W
0 20 40 60 80 100 120 140 160 180 2000.0
0.5
1.0
1.5
2.0
2.5
3.0
Validation Case 4: W/S and T/W
Calculated Using Mattingly - Master Equation
Provided Validation Points from GA TECH
W/S
T/W
0.32030.32010.32090.3225
T/W Total2.52181.28020.87370.67600.56180.48930.44070.40700.38330.36650.35470.34680.34180.33900.33810.33870.34060.34340.34710.3516
0 20 40 60 80 100 120 140 160 180 2000.0
0.5
1.0
1.5
2.0
2.5
3.0
Validation Case 4: W/S and T/W
Calculated Using Mattingly - Master Equation
Provided Validation Points from GA TECH
W/S
T/W
0 20 40 60 80 100 120 140 160 180 2000.0
0.5
1.0
1.5
2.0
2.5
3.0
Validation Case 5: W/S and T/W
Calculated Using Mattingly - Master Equation
Provided Validation Points from GA TECH
W/S
T/W
0 20 40 60 80 100 120 140 160 180 2000.0
0.5
1.0
1.5
2.0
2.5
3.0
Validation Case 1: W/S and T/W
Calculated Using Mattingly - Master Equation
Provided Validation Points from GA TECH
W/S
T/W
0 20 40 60 80 100 120 140 160 180 2000.0
0.5
1.0
1.5
2.0
2.5
3.0
Validation Case 2: W/S and T/W
Calculated Using Mattingly - Master Equation
Provided Validation Points from GA TECH
W/S
T/W
0 20 40 60 80 100 120 140 160 180 2000.0
0.5
1.0
1.5
2.0
2.5
3.0
Validation Case 2: W/S and T/W
Calculated Using Mattingly - Master Equation
Provided Validation Points from GA TECH
W/S
T/W
0 20 40 60 80 100 120 140 160 180 2000.0
0.5
1.0
1.5
2.0
2.5
3.0
Validation Case 3: W/S and T/W
Calculated Using Mattingly - Master Equation
Provided Validation Points from GA TECH
W/S
T/W
0 20 40 60 80 100 120 140 160 180 2000.0
0.5
1.0
1.5
2.0
2.5
3.0
Validation Case 4: W/S and T/W
Calculated Using Mattingly - Master Equation
Provided Validation Points from GA TECH
W/S
T/W
0 20 40 60 80 100 120 140 160 180 2000.0
0.5
1.0
1.5
2.0
2.5
3.0
Validation Case 4: W/S and T/W
Calculated Using Mattingly - Master Equation
Provided Validation Points from GA TECH
W/S
T/W
0 20 40 60 80 100 120 140 160 180 2000.0
0.5
1.0
1.5
2.0
2.5
3.0
Validation Case 5: W/S and T/W
Calculated Using Mattingly - Master Equation
Provided Validation Points from GA TECH
W/S
T/W
Mission Analysis
Step 1 Notes/Sources:Ammunition Weight (1.62 lbs x 2000 rounds) 3,240 lbs Source: "2006-2007 AIAA Graduate Team Aircraft Design Competition - Modifiied RFP"Internal Stores Max 5,000 lbs GD GAU-8 30-mm Cannon is part of weight emptyExternal Stores Max 12,000 lbs External Stores is deemed the limiting case
Total 12,000 lbs Enter Payload based on above values, and Desired Mission (for baseline misson, assume worst case external stores)
Crew WeightCrew (1x250lbs) 250 lbs Source: "2006-2007 AIAA Graduate Team Aircraft Design Competition - Modifiied RFP"
Total 250 lbs
Step 2Aircraft Type W_PL W_TO V_MAX Range Source: Taylor, J.W.R, Jane's All The World Aircraft Published Annually by: Jane's Publishing Company, (Issues used: 1945/45, 1968/84)
(lbs) (lbs) (kts) (nm) Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 60F.R. A10A 15,000 50,000 450 540
Grumman A6 17,000 60,400 689 1,700 Tornado F.Mk2 16,000 58,400 600 750
Average: 16,000 56,267 580 997 Some initial guess for TOGW, will only be used for reference, program automatically calculates TOGW based on historical data
59,488 lbs Later this will be iterated to find weight empty
Step 3 Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 12
Climb 1Range Credit 24.5000001 nm Assume 10,000 ft/min climb (from RFP) and 350 knot ground speed during climb (from Roskam page 62); therefore, Rclimb = Alt./(10K/min)*350knotsCruise 1
775.5 nm 800 nm specified in RFP - climb 1 rangeAltitude 42,000 ft
Temperature @ Alt, T -90.6Delta 0.1668Theta 0.7116
Payload Calculations, W PL
WPL
WCREW
Weight Take Off Guess Based on Historical Data, W TO_GUESS
WTO_GUESS
Mission Fuel Weight Fractions, W F
Rcr, Cruise Range
o F
Mission Analysis
Step 1 Notes/Sources:Ammunition Weight (1.62 lbs x 2000 rounds) 3,240 lbs Source: "2006-2007 AIAA Graduate Team Aircraft Design Competition - Modifiied RFP"Internal Stores Max 5,000 lbs GD GAU-8 30-mm Cannon is part of weight emptyExternal Stores Max 12,000 lbs External Stores is deemed the limiting case
Total 12,000 lbs Enter Payload based on above values, and Desired Mission (for baseline misson, assume worst case external stores)
Crew WeightCrew (1x250lbs) 250 lbs Source: "2006-2007 AIAA Graduate Team Aircraft Design Competition - Modifiied RFP"
Total 250 lbs
Step 2Aircraft Type W_PL W_TO V_MAX Range Source: Taylor, J.W.R, Jane's All The World Aircraft Published Annually by: Jane's Publishing Company, (Issues used: 1945/45, 1968/84)
(lbs) (lbs) (kts) (nm) Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 60F.R. A10A 15,000 50,000 450 540
Grumman A6 17,000 60,400 689 1,700 Tornado F.Mk2 16,000 58,400 600 750
Average: 16,000 56,267 580 997 Some initial guess for TOGW, will only be used for reference, program automatically calculates TOGW based on historical data
62,414 lbs Later this will be iterated to find weight empty
Step 3 Source: Roskam, "Airplane Design, Part I: Preliminary Sizing of Airplanes", 1985, pg 12
Climb 1Range Credit 24.5000001 nm Assume 10,000 ft/min climb (from RFP) and 350 knot ground speed during climb (from Roskam page 62); therefore, Rclimb = Alt./(10K/min)*350knotsCruise 1
775.5 nm 800 nm specified in RFP - climb 1 rangeAltitude 42,000 ft
Temperature @ Alt, T -90.6Delta 0.1668Theta 0.7116
Payload Calculations, W PL
WPL
WCREW
Weight Take Off Guess Based on Historical Data, W TO_GUESS
WTO_GUESS
Mission Fuel Weight Fractions, W F
Rcr, Cruise Range
o F