• Question Cagtegory: Aerodynamics
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• ## Calculate lift, wave-drag and pressure coefficients of an infinitely thin flat plate which is in a Mach $$2.5$$ freestream flow at an angle of attack of $$5^{^{\circ}}$$, using linearized theory.

Calculate lift, wave-drag  and pressure coefficients of an infinitely thin flat plate which is in a Mach $$2.5$$ freestream flow …

Asked on 27th January 2022 in
• 183 views
• ## Why is critical Mach number of a sphere higher than a cylinder ?

Why is critical Mach number of a sphere higher than a cylinder ?

Asked on 13th January 2022 in
• 165 views
• ## Find the velocity, pressure and temperature at, $$(0.07\,m, 0.07\,m)$$.

Velocity potential of a subsonic compressible flow is $\phi(x,y) = V_{\infty}x + \frac{5}{\sqrt{1 – M_{\infty}^{2}}}e^{-2\pi\sqrt{1-M_{\infty}^{2}}y}sin2\pi x$ Freestream velocity, pressure and …

Asked on 13th January 2022 in
• 174 views
• ## Find the pressure coefficient at this point.

An airfoil is in airflow with $$0.52$$ free stream Mach number. Local Mach number at a given point is $$0.82$$. …

Asked on 13th January 2022 in
• 177 views
• ## What are stagnation pressure and stagnation temperature ?

What are stagnation pressure and stagnation temperature ?

Asked on 7th September 2021 in
• 462 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
• 338 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
• 389 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
• 486 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
• 1K 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
• 302 views