Aerospace Oblique Shock Angle Calculation

1. Apr 12, 2010

Freyster98

I'm trying to write a MATLAB .m-file that will calculate the lift and drag on a supersonic airfoil using only the angle of attack, mach number, and geometry of the airfoil. I'm getting stuck on the oblique shock angle calculation because I cannot find an equation that is solved for the shock angle (beta). Does anyone know what equation I can use for this? Other than that, I think I'm all set. Any help you can give would be greatly appreciated. Thanks!

2. Apr 16, 2010

rugabug

3. Apr 16, 2010

Freyster98

I have that equation, but I just found out I don't have the symbolic math toolbox for MATLAB and that's why I couldn't solve the equation for beta. I used Maple to solve for beta and got a ridiculously long result.

4. Apr 16, 2010

rugabug

The equation in my book is ridiculously long. They actually split it into 3 equations.

5. Nov 3, 2010

ahmedeltabee

man u need to make an iteration using matlab i did it before and this is a code for it

Attached Files:

• theta_beta_M.m
File size:
325 bytes
Views:
268
6. Nov 3, 2010

Or just use the freaking fsolve or solve commands to do it numerically, since I assume that is what you are supposed to do anyway.

7. Nov 9, 2010

bcilek

Symbolic Math Toolbox! That is really something i desire very much i wonder why they did not put the inverse laplace transform capability on MATLAB.....

8. Nov 10, 2010

sorter

Use maple its just great

9. Nov 10, 2010