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A NACA 4421 airfoil having a chord length of \(2\,m\) is flying at an velocity of \(70\,m/s\) at an altitude …
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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 …
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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 …
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- 1 answers
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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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Find the velocity of air in the test section of a low speed open circuit subsonic wind tunnel which has …
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A venturi is attached on a side of an airplane fuselage, has an throat to inlet area ratio of \(0.8\). …
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Find the enthalpy change, internal energy change and entropy change across a shock wave whose upstream air temperature and pressure …
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Find the reservoir pressure for a nozzle of a supersonic wind tunnel which has an exit-to-throat area ratio of \(4.441\). …
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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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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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Question Tag: airspeed
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Find the location of the aerodynamic center.
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Find the angle of attack for this airfoil, if the lift per unit span produced is \(1400\,N\).
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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.
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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 \(140\,m/s\).
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