• Question Tag: Supersonic flow
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• ## Find the nozzle’s exit temperature and density if its exit pressure is $$1\,atm$$.

The reservoir of a supersonic wind-tunnel has a total temperature and total pressure of $$600\,K$$ and $$11\,atm$$. If the flow …

Asked on 15th April 2021 in
• 485 views
• ## Find the enthalpy change, internal energy change and entropy change across a shock wave.

Find the enthalpy change, internal energy change and entropy change across a shock wave whose upstream air temperature and pressure …

Asked on 15th April 2021 in
• 563 views
• ## Find the reservoir pressure for a nozzle of a supersonic wind tunnel.

Find the reservoir pressure for a nozzle of a supersonic wind tunnel which has an exit-to-throat area ratio of $$4.441$$. …

Asked on 26th March 2021 in
• 396 views
• ## Find the lift and wave drag coefficients for an infinitely thin flat plate.

Find the lift and wave drag coefficients for an infinitely thin flat plate at an angle of attack of $$8^{\circ}$$ …

Asked on 26th March 2021 in
• 451 views
• ## Find the pressure, temperature , Mach number,  total pressure and total temperature behind the oblique shock wave.

An oblique shock wave is generated with a wave angle of $${30^ \circ }$$ in a Mach $$4$$ flow, at …

Asked on 11th March 2021 in
• 550 views
• ## Find $${P_2},{T_2},\,{\rho _2},\,{M_2},{P_{02}}$$ and $${T_{02}}$$ downstream of the shock wave.

A flow passes through a normal shock wave has a pressure, temperature and Mach number of  $$1\,atm,\,295\,K$$ and $$2.8$$ upstream …

Asked on 11th March 2021 in
• 359 views
• ## What are expansion waves ?

What are expansion waves ? How does it originates ?

Asked on 18th January 2021 in
• 830 views
• ## What are shock waves ?

What are shock waves ? How does it originates ?

Asked on 18th January 2021 in
• 675 views
• ## Calculate the wave drag on the wings of an airplane.

Calculate the wave drag on the wings of an airplane which is flying at a Mach number of $$2.1$$ at …

Asked on 18th January 2021 in
• 786 views