Q3. A supersonic flow of air has a pressure of 1 x 10 N/m² and a temperature of 350 K. After expanding through a 35° tum, =? the Mach number is 3.5. Determine: · Angles 6,0, and 6,. Final flow properties p2 and Tz.

Q: a) An aircraft is flying at a Mach number of 0.95 at an altitude where the pressure is 30kPa and the…

A:

Q: Q2: the static pressure to stagnation pressure ratio is 0.82. the stagnation temperature is 300k.…

A: Given data:

Q: Q3. A supersonic flow of air has a pressure of 1 x 105 N/m2 and My a temperature of 350 K. After…

A: given data;⇒pressure(P)=1*105N/m2⇒temperature(T)=350K⇒mack number(M)=3.5

Q: The village shaman is up to no good again. Having calibrated their pulley system, they now have a…

A: (a) Given data: Wind speed: 5 m/s Amount of potion: n = 104 moles Initial temperature: 20°C Final…

Q: b) Air flowing at a velocity of '1039.6' km/hr has a static pressure of '83.17' kN/m2 and a…

A:

Q: 1. An air flow with a Mach number of 2.0 passes through an oblique shock wave inclined at an angle…

A: Solution   Calculate the deflection angle α          tanα=2tanθM2sin2θ-1M2γ+cos2θ+2

Q: Q4:-A shock wave is moving down a constant area duct containing air. The air ahead of the shock wave…

A:

Q: (Q) A converging-diverging nozzle discharges an over-expanded jet into a room. Calculate the…

A: