• Question Cagtegory: Aerodynamics
Filter by
Filter by
Questions Per Page:
• ## 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 …

Worldtech Asked on 27th January 2022 in
• 575 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?

Kisan Kumar Asked on 13th January 2022 in
• 572 views
• ## 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 temperature are $$200\,m/s$$, $$1\,atm$$ and $$300\,K$$. 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 …

Kumar59 Asked on 13th January 2022 in
• 506 views
• ## An airfoil is in airflow with $$0.52$$ free stream Mach number. Local Mach number at a given point is $$0.82$$. 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 $$0.82$$. …

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

What are stagnation pressure and stagnation temperature?

Worldtech Asked on 7th September 2021 in
• 757 views
• ## A circular cylinder and a sphere are in a free stream flow with their axis perpendicular to the flow. At the top of the sphere there is a pressure tap which is connected by a tube to one side of a manometer. There is a pressure tap on the surface of the cylinder which is connected to the other side of the manometer. 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 …

Kisan Kumar Asked on 1st September 2021 in
• 635 views
• ## A NACA 4421 airfoil having a chord length of $$2\,m$$ is flying at an velocity of $$70\,m/s$$ at an altitude of $$2\,km$$. 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 …

Kisan Kumar Asked on 22nd July 2021 in
• 734 views
• ## An airfoil has a lift coefficient and moment coefficient of $$-0.35$$ and $$-0.050$$ about quarter-chord at $$-6^{\circ}$$ angle of attack. The airfoil has lift coefficient and moment coefficient of $$0.70$$ and $$-0.040$$ at an angle of attack of $$4^{\circ}$$ about the same quarter chord. 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. …

techAir Asked on 22nd July 2021 in
• 838 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. …

Kisan Kumar Asked on 13th July 2021 in
• 2K 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 …