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The reservoir of a supersonic wind-tunnel has a total temperature and total pressure of $600\,K$ and $11\,atm$ . If the flow is isentropic through the nozzle of this wind tunnel, 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 …
Aircraft performance

Airplane design

Supersonic airplanes

Supersonic flow

techAir Asked on 15th April 2021 in Aerodynamics.
- 1K views
- 1 answers
- 0 votes
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 …
Aircraft performance

Airplane design

airspeed

Shock waves

Supersonic flow

Worldtech Asked on 15th April 2021 in Aerodynamics.
- 1K views
- 1 answers
- 0 votes
Find the reservoir pressure for a nozzle of a supersonic wind tunnel which has an exit-to-throat area ratio of $4.441$ . The test section pressure measured by a pitot tube is $1.5\, atm$ .
Find the reservoir pressure for a nozzle of a supersonic wind tunnel which has an exit-to-throat area ratio of $4.441$ . …
Airplane design

airspeed

Supersonic flow

Kisan Kumar Asked on 26th March 2021 in Design.
- 1K views
- 1 answers
- 0 votes
Find the lift and wave drag coefficients for an infinitely thin flat plate at an angle of attack of $8^{\circ}$ in a Mach $3$ flow.
Find the lift and wave drag coefficients for an infinitely thin flat plate at an angle of attack of $8^{\circ}$ …
drag coefficient

lift and drag

lift coefficient

Supersonic airplanes

Supersonic flow

Kumar59 Asked on 26th March 2021 in Aeronautics.
- 1K views
- 1 answers
- 0 votes
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 …
Airplane design

airspeed

Shock waves

Supersonic flow

Worldtech Asked on 11th March 2021 in Aerodynamics.
- 1K views
- 1 answers
- 0 votes
A flow passes through a normal shock wave has a pressure, temperature and Mach number of $1\,atm,\,295\,K$ and $2.8$ upstream of the shock wave. 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 …
airspeed

normal shock waves

Shock waves

Supersonic flow

Kumar59 Asked on 11th March 2021 in Aerodynamics.
- 958 views
- 1 answers
- 0 votes
What are expansion waves?
What are expansion waves? How does it originates?
Expansion wave

Supersonic airplanes

Supersonic flow

Kumar59 Asked on 18th January 2021 in Aerodynamics.
- 2K views
- 1 answers
- 0 votes
What are shock waves? How does it originates?
What are shock waves? How does it originates?
Shock waves

Supersonic airplanes

Supersonic flow

Kisan Kumar Asked on 18th January 2021 in Aerodynamics.
- 1K views
- 1 answers
- 0 votes
Calculate the wave drag on the wings of an airplane which is flying at a Mach number of $2.1$ at an altitude of $10000\, m$ . The airplane weights $70000\, N$ and has a wing area of $20\, m^2$ .
Calculate the wave drag on the wings of an airplane which is flying at a Mach number of $2.1$ at …
drag

drag force

Shock waves

Supersonic airplanes

Supersonic flow

Kumar59 Asked on 18th January 2021 in Aerodynamics.
- 2K views
- 1 answers
- 0 votes
What is a Mach wave? How does it forms?
What is a Mach wave? How does it forms?
Mach number

Mach wave

Supersonic airplanes

Supersonic flow

Kisan Kumar Asked on 18th January 2021 in Aerodynamics.
- 1K views
- 1 answers
- 0 votes

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