Drag calculation based on kinetic theory, flux

[orbitsnerd]

Homework Statement

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
m_o=2.67 x 10^-26 kg
v_o=7.8 x 10³ m/s
Θ=Τ=1
Θ upper=135 degrees
Θ lower=45 degrees

Homework 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) *vth[/SUB/v_d * sin(Β)*cos(Β) exp (-v_d*sin(Β/vth[/SUB)^2)+...etc
and a similar equation for C_D

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!

 

[Jhero]

Thank you for your post. It seems like you are working on a complex problem involving the aerodynamics of a flat plate orbiting at an angle of attack around the Earth. I understand that you are not able to use the basic CD, CL equations and are looking for help with the boundary condition equations based on kinetic theory.

Unfortunately, I am not familiar with the specific equations you have mentioned and I do not have enough information about your problem to provide a solution. It would be helpful if you could provide more context and background information about your problem, such as the specific boundary conditions you are working with and any other relevant equations or assumptions.

In any case, I suggest consulting with a colleague or professor who is knowledgeable in this field for assistance. They may be able to provide more specific guidance and help you better understand the equations you are working with.

I wish you the best of luck with your research and calculations. Keep up the good work!