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Calculate lift, wave-drag and pressure coefficients of an infinitely thin flat plate which is in a Mach \(2.5\) freestream flow at an angle of attack of \(5^{^{\circ}}\), using linearized theory.
Calculate lift, wave-drag and pressure coefficients of an infinitely thin flat plate which is in a Mach \(2.5\) freestream flow …
Aircraft performance

drag coefficient

lift and drag

Supersonic airplanes

Worldtech Asked on 27th January 2022 in Aerodynamics.
- 575 views
- 1 answers
- 0 votes
What are jet engine and scramjet engine ?
What are jet engine and scramjet engine ?
Aircraft performance

Supersonic airplanes

turbojet

techAir Asked on 7th September 2021 in Propulsion.
- 763 views
- 1 answers
- 0 votes
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.
- 641 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.
- 652 views
- 1 answers
- 0 votes
An oblique shock wave is generated at a compression corner having a deflection angle of \(20^{^{\circ}}\). The oblique shock wave is reflected from a straight horizontal wall which is present above the compression corner. The upstream flow properties are \(M_{1}=3.4,\,p_{1}=1\,atm,\,T_{1}=300\,K\). Find the Mach number, pressure and temperature behind the reflected shock wave and angle made by the reflected shock wave with the upper wall.
An oblique shock wave is generated at a compression corner having a deflection angle of \(20^{^{\circ}}\). The oblique shock wave …
airspeed

oblique shock waves

Shock waves

Supersonic airplanes

techAir Asked on 26th March 2021 in Aerodynamics.
- 658 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.
- 1K 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.
- 838 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.
- 991 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.
- 865 views
- 1 answers
- 0 votes
An airplane flying at a Mach number of 2.2 makes a Mach wave at the nose. What angle does it make with the flow direction?
An airplane flying at a Mach number of 2.2 makes a Mach wave at the nose. What angle does it …
Mach number

Mach wave

Supersonic airplanes

Supersonic flow

Kumar59 Asked on 18th January 2021 in Flight mechanics.
- 780 views
- 1 answers
- 0 votes

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