Lift and Drag Calculations Including Coeficients

Eqn. A3

Lift and Drag Equations

5.) C_L₀= -0.14490

6.) C_L₁= -0.02924

7.) C_D₀= -0.07854

8.) C_D₁= -6.15920(10)^-3

9.) C_D₂= -6.21408(10)^-4

L = Aerodynamic Lift.

D = Aerodynamic Drag.

r = Gas Density (Slugs / Ft.³)

V = Velocity (Ft. / Sec.)

Sref = Shuttle reference surface area (2,690 Ft.²)

m = Mass of shuttle (203,000 lbs.)

C_L= Coefficient of Lift. (Mach > 2.5)

C_D= Coefficient of Drag. (Mach > 2.5)

a = Angle of attack (Degrees)