Wedge in a Supersonic Flow Part 1

Calculate pressure, lift and drag coefficients on a wedge in supersonic flow using shock-expansion theory and linear theory.

[@josephtraverso2700]

Super helpful. Thanks for the video

[@safaerenpepec2477]

Thank you. It was very helpful for me. Please keep uploading videos. You saved my life at last night before my exam. :)

[@husseinibrahim2129]

You have saved me a lot of time. Thanks

[@baviquevirechecantepuspace2615]

Thank you so very much for this useful video!

[@DBlake97]

8:20 -> M2n is squared and needs to be square rooted before moving on to M2

[@emanuelngunza8928]

best video ever thank you very much

[@ecekacira4640]

thank you. I have a question btw how can we find cp2l cp2u values?

[@erickrobles6365]

Hi Jorg, could you tell me why it is that we only care about the normal component of mach number? I read in the book but I am still confused. thank you!

[@raba2d723]

theres two components, normal and perpendicular component. however perpendicular component is Same across the oblique shock, whereas it is the normal component that change. Therefore, we project to the normal component, in order to solve for quantities across shocks, then project back, in order to get total mach number.

[@oscariribe243]

what would happen if you have a half diamond shaped airfoil ?

[@jdtaramona]

Oscar Iribe look Anderson’s book on Aerodynamics!!!