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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 $1400\,N$ .
A NACA 0012 airfoil having a chord of $2.3\,m$ is in an airstream velocity of $70\,m/s$ at standard sea level …
airfoil

airspeed

lift

lift coefficient

lift force

Worldtech Asked on 22nd July 2021 in Aeronautics.
- 1K views
- 1 answers
- 0 votes
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

airspeed

Worldtech Asked on 16th June 2021 in Aerodynamics.
- 1K 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 …
airspeed

incompressible flow

techAir Asked on 16th June 2021 in Aerodynamics.
- 1K views
- 1 answers
- 0 votes
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.
Find the velocity of air in the test section of a low speed open circuit subsonic wind tunnel which has …
airspeed

incompressible flow

Kisan Kumar Asked on 15th June 2021 in Aeronautics.
- 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 …
airspeed

incompressible flow

Kumar59 Asked on 15th June 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
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 $\theta =25^{^{\circ}}$ …
airspeed

Expansion wave

Shock waves

Worldtech Asked on 26th March 2021 in Aerodynamics.
- 1K 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.
- 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

airspeed

Mach number

Shock waves

Kumar59 Asked on 11th March 2021 in Aerodynamics.
- 1K views
- 1 answers
- 0 votes

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