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Aerospace Oblique Shock Angle Calculation

  1. Apr 12, 2010 #1
    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. jcsd
  3. Apr 16, 2010 #2
  4. Apr 16, 2010 #3
    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.
     
  5. Apr 16, 2010 #4
    The equation in my book is ridiculously long. They actually split it into 3 equations.
     
  6. Nov 3, 2010 #5
    man u need to make an iteration using matlab i did it before and this is a code for it
     

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  7. Nov 3, 2010 #6

    boneh3ad

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    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.
     
  8. Nov 9, 2010 #7

    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.....
     
  9. Nov 10, 2010 #8
    Use maple its just great
     
  10. Nov 10, 2010 #9

    boneh3ad

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    Maple is craptastic. Mathematica is a nicer package IMO.
     
  11. Dec 18, 2011 #10
    i need this your program.can you help me? if it possible for you plz send that to me.thanks
    mhd.hadipour@yahoo.com
     
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