Calculate pressure, lift and drag coefficients on a wedge in supersonic flow using shock-expansion theory and linear theory.
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@ecekacira4640 Жыл бұрын
thank you. I have a question btw how can we find cp2l cp2u values?
@MrStunna973 жыл бұрын
8:20 -> M2n is squared and needs to be square rooted before moving on to M2
@erickrobles63656 жыл бұрын
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!
@raba2d7233 жыл бұрын
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.
@safaerenpepec24774 жыл бұрын
Thank you. It was very helpful for me. Please keep uploading videos. You saved my life at last night before my exam. :)
@baviquevirechecantepuspace26153 жыл бұрын
Thank you so very much for this useful video!
@husseinibrahim21296 жыл бұрын
You have saved me a lot of time. Thanks
@oscariribe2438 жыл бұрын
what would happen if you have a half diamond shaped airfoil ?
@jdtaramona5 жыл бұрын
Oscar Iribe look Anderson’s book on Aerodynamics!!!