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An airplane is flying at an velocity of \(100\,m/s\). Find the pressure coefficient at a point on the surface of the wing where the flow velocity is \(140\,m/s\).
An airplane is flying at an velocity of \(100\,m/s\). Find the pressure coefficient at a point on the surface of …
Aircraft performance

Airplane design

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Worldtech Asked on 16th June 2021 in Aerodynamics.
- 988 views
- 1 answers
- 0 votes
A pitot tube of an airplane which is flying at an standard sea level measures a pressure of \(1.09 \times 10^{5} N/m^{2}\). Find the velocity of the airplane.
A pitot tube of an airplane which is flying at an standard sea level measures a pressure of \(1.09 \times …
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incompressible flow

techAir Asked on 16th June 2021 in Aerodynamics.
- 1K views
- 1 answers
- 0 votes
Find the velocity of an airplane flying at a standard sea level, if the static pressure at the throat of venturi is \(100 000 N/m^{2}\).
Find the velocity of an airplane flying at a standard sea level, if the static pressure at the throat of …
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incompressible flow

Kumar59 Asked on 15th June 2021 in Aerodynamics.
- 1K 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.
- 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

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Shock waves

Supersonic flow

Worldtech Asked on 15th April 2021 in Aerodynamics.
- 1K views
- 1 answers
- 0 votes
The upstream Mach number, pressure and temperature of a supersonic flow over an expansion corner having deflection angle \(\theta =25^{^{\circ}}\) is \(M_{1}=2.2,\,p_{1}=0.8\,atm\) and \(T_{1}=360\,K\). Find the downstream Mach number, pressure, temperature, density , total pressure, total temperature, and the angles made by the forward and rearward Mach lines with local flow direction.
The upstream Mach number, pressure and temperature of a supersonic flow over an expansion corner having deflection angle \(\theta =25^{^{\circ}}\) …
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Expansion wave

Shock waves

Worldtech Asked on 26th March 2021 in Aerodynamics.
- 958 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 …
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oblique shock waves

Shock waves

Supersonic airplanes

techAir Asked on 26th March 2021 in Aerodynamics.
- 1K views
- 1 answers
- 0 votes
A flow is passing over a \({20^ \circ }\) half-angle wedge having a upstream Mach number, pressure and temperature of \(2.8,\,1\,atm\,\) and \(310\,K\). Find the wave angle and downstream Mach number, pressure and temperature.
A flow is passing over a \({20^ \circ }\) half-angle wedge having a upstream Mach number, pressure and temperature of …
Airplane design

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Mach number

Shock waves

Kumar59 Asked on 11th March 2021 in Aerodynamics.
- 978 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

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Shock waves

Supersonic flow

Worldtech Asked on 11th March 2021 in Aerodynamics.
- 1K views
- 1 answers
- 0 votes
Find the upstream Mach number if there is a entropy increase across the normal shock wave of \(220\,J/\left( {kg.K} \right)\).
Find the upstream Mach number if there is an entropy increase across the normal shock wave of \(220\,J/\left( {kg.K} \right)\).
Mach number

normal shock waves

Shock waves

thermodynamics

techAir Asked on 11th March 2021 in Aerodynamics.
- 1K views
- 1 answers
- 0 votes

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