Q6: Air following through constant area duct encounters stationary shock as shown in figure. Find the Mach number, temperature, pressure, stagnation pressure, stagnation temperature and velocity after the shock. Ans.: M2 = 0.6746, T2 =

Q: Q2: The large compressed-air tank shown in the figure bellow exhausts from a nozzle at an exit…

A: Given Data exit velocity, Ve=235 m/s k=1.396 Cp=917 J/kg·K R=260 J/kg·K T=30 oC =30+273=303 K (a)…

Q: 11. Find the difference between Mach no.s of an aircraft flies with a velocity lower by 35 m-s1 at…

A:

Q: Q4//B/ Heat is removed from airflow in a constant-area duct, if flow enters at Mach 2.20, Ti= 310 K,…

A: Stagnation Point: The point in the flow where fluid velocity will be zero is called the stagnation…

Q: Suppose a gas flows through a constant insulated path. Parameters of temperature, pressure and mach…

A: given; ⇒initial temperature(T0)=520R⇒initial pressure(P0)=50psi⇒mack number (M0)=0.45⇒at…

Q: Do you think that the shockwave occurs in this bullet travel for both medium of gas? Sketch your…

A: Given data:   Speed of bullet = 1548 miles per hour = 692.0179 m/s The properties of the two mediums…

Q: Example (5-4): An airstream at Mach 2.0, with pressure of 100 kPa and temperature of 270 K, enter a…

A:

Q: E) The total (stagnation) temperature (To) is (in Ko ig a. 360; c. 320 ; d. 300;e 280 b.340; -) The…

A: To find Total stagnation temperature velocity of flow

Q: A convergent divergent diffuser is exposed to air at pressure of 80kPa and temperature of 350K and…

A: Given figure

Q: Show that for isentropic flow of a perfect gas if a pitot- static probe measures Po, p, and Tg, the…

A: Given: Isentropic flow of a perfect gas

Q: Calculate the pressure coefficient at this point on the wing. b. After a while, the airplane's Mach…

A: