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Latest
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Worldtech
A NACA 0012 airfoil having a chord of \(2.3\,m\) is in an airstream velocity of \(70\,m/s\) at standard sea level conditions. Find the angle of attack for this airfoil, if the lift per unit span produced is \(1400\,N\).
airfoil
airspeed
lift
lift coefficient
lift force
on 22nd July 2021 in
Aeronautics.
849
1
0
Worldtech
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 \(140\,m/s\).
Aircraft performance
Airplane design
airspeed
on 16th June 2021 in
Aerodynamics.
752
1
0
techAir
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.
airspeed
incompressible flow
on 16th June 2021 in
Aerodynamics.
772
1
0
Kisan Kumar
Find the velocity of air in the test section of a low speed open circuit subsonic wind tunnel which has an inlet -to-throat area ratio of \(10\). The U-tube mercury manometer read as a height difference of \(10.5\,cm\) for the pressure difference between the inlet and the test section of the wind tunnel.
airspeed
incompressible flow
on 15th June 2021 in
Aeronautics.
840
1
0
Kumar59
Find the velocity of an airplane flying at a standard sea level, if the static pressure at the throat of venturi is \(100 000 N/m^{2}\).
airspeed
incompressible flow
on 15th June 2021 in
Aerodynamics.
803
1
0
Worldtech
Find the enthalpy change, internal energy change and entropy change across a shock wave.
Aircraft performance
Airplane design
airspeed
Shock waves
Supersonic flow
on 15th April 2021 in
Aerodynamics.
884
1
0
Kisan Kumar
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 \(1.5\, atm\).
Airplane design
airspeed
Supersonic flow
on 26th March 2021 in
Design.
742
1
0
Worldtech
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.
airspeed
Expansion wave
Shock waves
on 26th March 2021 in
Aerodynamics.
699
1
0
techAir
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.
airspeed
oblique shock waves
Shock waves
Supersonic airplanes
on 26th March 2021 in
Aerodynamics.
794
1
0
Kumar59
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.
Airplane design
airspeed
Mach number
Shock waves
on 11th March 2021 in
Aerodynamics.
733
1
0
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