rugabug said:http://upload.wikimedia.org/math/2/7/b/27b8202d60430e48b08cf5b6498c1097.png
You can use MATLAB to solve for beta or if I remember when I get home I have the equation for beta in a textbook.
The equation in my book is ridiculously long. They actually split it into 3 equations.Freyster98 said: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.
Freyster98 said: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.
Freyster98 said: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!
An oblique shock angle is the angle at which a shock wave forms when an object moves at a supersonic speed. It is the angle between the shock wave and the direction of the object's motion.
The oblique shock angle can be calculated using the Prandtl-Meyer equation, which takes into account the Mach number and the ratio of specific heats of the gas. It can also be calculated using empirical relationships or through computational methods.
The oblique shock angle is affected by the Mach number, the angle of the object's motion, and the gas properties, such as the specific heat ratio. It is also influenced by the shape and size of the object.
The oblique shock angle is important in supersonic aerodynamics as it determines the strength and location of the shock wave, which can impact the performance and stability of an object. It is also important in understanding and analyzing supersonic flow phenomena.
Oblique shock angle calculations are used in various fields, such as aerospace engineering, gas dynamics, and high-speed aerodynamics. They are applied in the design and analysis of supersonic vehicles, propulsion systems, and airfoils. They are also used in the study of supersonic combustion and hypersonic flow.