Parameters
Aircraft Presets
Weight W120.0 kN
Wing Area S105.0 m²
Aspect Ratio AR9.0
Zero-lift Drag CD00.0200
Oswald Efficiency e0.80
Max Lift Coeff CLmax2.20
Altitude h10.0 km
Thrust T120.0 kN
SFC (Specific Fuel Consumption)18.0 mg/Ns
Fuel Weight Fraction W_fuel/W0.35
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Stall Speed Vs [km/h]
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(L/D)max
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Max Climb Rate RC [m/s]
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Range R [km]
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Min-Drag Speed V_md [km/h]
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Service Ceiling [km]
Equations
Parabolic drag polar: $C_D = C_{D0} + \dfrac{C_L^2}{\pi AR\, e}$
Stall speed: $V_s = \sqrt{\dfrac{2W}{\rho S C_{L\max}}}$
Min-drag speed: $V_{md} = \sqrt{\dfrac{2W}{\rho S}\sqrt{\dfrac{C_{D0}}{\pi AR\, e}}}$
Max L/D: $(L/D)_{max} = \dfrac{1}{2}\sqrt{\dfrac{\pi AR\, e}{C_{D0}}}$
Rate of climb: $RC = \dfrac{(T - D)V}{W}$
Breguet range: $R = \dfrac{C_L}{C_D}\cdot\dfrac{V}{SFC}\cdot\ln\!\left(\dfrac{W_1}{W_2}\right)$
Engineering Note: Used for initial sizing of aerodynamic designs, flight envelope analysis, and wing optimization before full NASTRAN/CFD analysis. Validates hand calculations for propulsion-aerodynamics coupling.