Questions Archive - Page 35 of 38

Consider the supersonic flow over a flat plate at an angle of attack. Outline a method to calculate the strengths of trailing edge shock and expansion waves, and direction of the flow downstream of the trailing edge.

Outline a method to calculate the strengths of trailing edge shock and expansion waves , and direction of the flow …

techAir Asked on 3rd July 2019 in Aerodynamics.

Apply Kutta-joukowski theorem for a two dimensional body of arbitrary shape by making a physical argument.

Worldtech Asked on 2nd July 2019 in Aerodynamics.

Explain on a physical basis why the sphere has a higher Mcr than the cylinder.

techAir Asked on 2nd July 2019 in Aerodynamics.

Consider a diamond-wedge airfoil, with a half angle of 10 degree. The airfoil is at an angle of attack of …

Worldtech Asked on 17th February 2019 in Aerodynamics.

The airfoil section of a wing is an NACA 2213 at the wing root, tapering to an NACA 2205 at …

techAir Asked on 18th February 2019 in Aerodynamics.

Consider a circular cylinder (oriented with its axis perpendicular to the flow) and a symmetric diamond-wedge airfoil with a half-angle …

techAir Asked on 16th February 2019 in Aerodynamics.

Consider a velocity field where x and y components of velocity are given by u=4x and v=-4y. Obtain the equation …

Worldtech Asked on 4th January 2019 in Fluid dynamics.

A velocity field has radial and tangential components of velocity as \({V_r} = 0\) and \({V_\theta } = 4r\).Obtain equation of streamlines.

Worldtech Asked on 4th January 2019 in Fluid dynamics.

x and y components of a velocity field are given as \(u = \frac{{4x}}{{\left( {{x^2} + {y^2}} \right)}}\) and \(v …

Worldtech Asked on 4th January 2019 in Fluid dynamics.

For a velocity field of incompressible flow given by \(u = 4x\) and \(v = – 4y\), calculate the stream function …

techAir Asked on 3rd January 2019 in Fluid dynamics.