lec28 Shock Expansion Method

[@dipalimane1692]

Thank you sir.

[@RitTinga]

Good day! I do not speak foreign languages, I write through an interpreter. How will this profile work on a round wing at speeds up to 100 km/h, Does it make sense to make a round wing with this profile? It is planned to design and build an ultralight aircraft with a circular wing in the form of a disk in the plan. Such a profile is easier to manufacture from wood in artisanal conditions. “thanks.

[@switchtv2842]

From where do you find the pressure rations P2/P01 etc. ? What charts or tables? I cant figure this out :( pls help

[@isxp]

Switch TV, I believe your confusion is about the ratio across the expansion fan (or PM Fan/PM wave, all mean the same thing). The ratio across any isentropic wave has constant stagnation properties. To your question though, the value of p2/p01 would come from an isentropic table, where some input (either Mach number (m2), or PM number (v2), etc), got you a location in a table, at the location of the expansion wave/fan/etc, the pressure ratio p2/p02 is the same thing as p2/p01 because the stagnation pressures across this isentropic expansion fan/wave are constant. He might write p2/p01, but thinking of it as p2/p02 is fine, as long as you know their equivalent. Your textbook/calculator doesn't know where you're at in your problem, so it will typically convey p/p0 and it's up to you to know when the p0's are equal. Answer: they're equal across isentropic processes, like compression waves and expansion fans, but not normal and oblique shocks.