• Question Cagtegory: Aerodynamics
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• ## What are stagnation pressure and stagnation temperature ?

What are stagnation pressure and stagnation temperature ?

Asked on 7th September 2021 in
• 31 views
• ## Find the location of this tap on cylindrical surface such that there is no deflection of fluid in the manometer.

A circular cylinder and a sphere are in a free stream flow with their axis perpendicular to the flow. At …

Asked on 1st September 2021 in
• 67 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
• 118 views
• ## Find the location of the aerodynamic center.

An airfoil has a lift coefficient and moment coefficient of $$-0.35$$ and $$-0.050$$ about quarter-chord at $$-6^{\circ}$$ angle of attack. …

Asked on 22nd July 2021 in
• 121 views
• ## Can an airfoil fly upside-down ?

A positively cambered airfoil has a zero-lift angle of $$-3.5^{\circ}$$. The lift slope for this airfoil is $$0.12$$ per degree. …

Asked on 13th July 2021 in
• 125 views
• ## 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 on 16th June 2021 in
• 123 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
• 113 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 • 110 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}$$.

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
• 127 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 …