• Question Cagtegory: Aerodynamics
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• ## Find the circulation around a spinning circular cylinder in free stream flow of velocity $$40\,m/s$$ at a standard sea level conditions, if the lift produced by the cylinder is $$8\,N/m$$ of span.

Find the circulation around a spinning circular cylinder in free stream flow of velocity $$40\,m/s$$ at a standard sea level …

Asked 16 hours ago in
• 4 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 16 hours ago in
• 5 views

A pitot tube of an airplane which is flying at an standard sea level measures a pressure of $$1.09 \times … Asked 16 hours ago in • 4 views • 0 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}$$.

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

Asked 2 days ago in
• 9 views
• ## 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 …

Asked on 15th April 2021 in
• 69 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
• 111 views
• ## 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 $$\theta =25^{^{\circ}}$$ …

Asked on 26th March 2021 in
• 97 views
• ## 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 …

Asked on 26th March 2021 in
• 110 views
• ## Find the wave angle, 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 …

Asked on 11th March 2021 in
• 80 views
An oblique shock wave is generated with a wave angle of $${30^ \circ }$$ in a Mach $$4$$ flow, at …