For the flat plate and double wedge airfoil shown in the below figure, calculate the flow...

Transcribed Image Text:

For the flat plate and double wedge airfoil shown in the below figure, calculate the flow Mach numbers and static and total pressure at zones 2, 2', 3, and 3', assuming the static pressure at region 1 is 0.8 atm. M₁=3 12° M₁=3 12% #8500000 3 For the flat plate and double wedge airfoil shown in the below figure, calculate the flow Mach numbers and static and total pressure at zones 2, 2', 3, and 3', assuming the static pressure at region 1 is 0.8 atm. M₁=3 12° M₁=3 12% #8500000 3

Answer rating: 100% (QA)

The image you provided illustrates a supersonic flow Mach 3 encountering a flat plate with a double wedge airfoil When the flow meets the leading edge... View the full answer