(adsbygoogle = window.adsbygoogle || []).push({}); 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 M^{2}.

Cd~2.2

n=1x10^{15}/m^{3}

T=975 K

Β=45 degrees

A=10 m^{2}

m_{o}=2.67 x 10^{-26}kg

v_{o}=7.8 x 10^{3}m/s

Θ=Τ=1

Θ upper=135 degrees

Θ lower=45 degrees

2. Relevant equations

I cannot use the basic C_{D}, C_{L}equations. I need to use a set of boundary condition equations based on kinetic theory.

C_{L}=4Ε/√(Π) *v_{th[/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!}

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# Drag calculation based on kinetic theory, flux

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