1. The problem statement, all variables and given/known data A flat plate is orbiting at an altitude of 250 km around the earth, at an angle of attack Β=45 degrees. Assume that the atmosphere is composed of only atomic oxygen which reflect from the surface diffusely. Calculate the lift and drag if it has an area of 10 M2. Cd~2.2 n=1x1015/m3 T=975 K Β=45 degrees A=10 m2 mo=2.67 x 10-26 kg vo=7.8 x 103 m/s Θ=Τ=1 Θ upper=135 degrees Θ lower=45 degrees 2. Relevant equations I cannot use the basic CD, CL equations. I need to use a set of boundary condition equations based on kinetic theory. CL=4Ε/√(Π) *vth[/SUB/vd * sin(Β)*cos(Β) exp (-vd*sin(Β/vth[/SUB)^2)+....etc and a similar equation for CD 3. The attempt at a solution I have drifting gas equations, stationary gas equations and a ton more. Pn/Pinf=((1+Ε)/sqrt(Π))*(vd cos theta/vth).... Τ/Pinf=(1-Ε)/sqrt(Π)*vd sin(Θ)... q/mninf(2kTinf/m)^(3/2)=alphac(1-Ε)/(4*sqrtΠ)... Any help here? Thanks!