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• What are stagnation pressure and stagnation temperature ?

What are stagnation pressure and stagnation temperature ?

Asked on 7th September 2021 in
• 116 views
• Find the lift per unit span and the circulation at an angle of attack of $$4^{\circ}$$, for this airfoil.

A NACA 4421 airfoil having a chord length of $$2\,m$$ is flying at an velocity of $$70\,m/s$$ at an altitude …

Asked on 22nd July 2021 in
• 145 views
• 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 …

Asked on 22nd July 2021 in
• 152 views
• 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 …

Asked on 16th June 2021 in
• 131 views

A pitot tube of an airplane which is flying at an standard sea level measures a pressure of $$1.09 \times … Asked on 16th June 2021 in • 146 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$$.

Find the velocity of air in the test section of a low speed open circuit subsonic wind tunnel which has …

Asked on 15th June 2021 in
• 153 views
• Find the velocity of an airplane flying at a standard sea level, if the static pressure at the throat of venturi is $$100 000 N/m^{2}$$.

A venturi is attached on a side of an airplane fuselage, has an throat to inlet area ratio of $$0.8$$.  …

Asked on 15th June 2021 in
• 142 views
• 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 …

Asked on 15th April 2021 in
• 198 views
• Find the reservoir pressure for a nozzle of a supersonic wind tunnel.

Find the reservoir pressure for a nozzle of a supersonic wind tunnel which has an exit-to-throat area ratio of $$4.441$$. …

Asked on 26th March 2021 in
• 133 views
The upstream Mach number, pressure and temperature of a supersonic flow over an expansion corner having deflection angle $$\theta =25^{^{\circ}}$$ …