Aerodynamics II — Summer 2019

Plot Variation of Cwith Re, and aspect ratio. L

Define mean aerodynamic chord [MAC] and procedure to find MAC.

Derive expression for classical thin airfoil theory.

Define:- Turbulent flow, Transition and dihedral.

State Kelvin Circulation Theorem.

Explain The Vortex lattice method.

Explain Kutta-Joukowsky Transformation and details procedure about transformation of circle into symmetric airfoil.

Write Kutta Condition and explain with sketch.

Differentiate between finite and infinite wing. Derive expression for ‘a’ (C α slope) and ‘a ’ L- 0.

What is Transformation? Explain transformation of a circle into a straight line with a neat sketch.

What is bound vortex and Horse shoe vortex?

Explain Numerical Nonlinear Lifting Line Method

Explain Prandtle lifting line theory and derive expression for downwash velocity.

Explain Prandtl-Glauert Compressibility correction,

Explain formation of primary and secondary vortex on delta wing.

Derive Linearised Supersonic Pressure Coefficient formula.

Explain the area rule with neat sketch.

At a given point on the surface of an airfoil, the pressure coefficient is -0.3 at very low speeds. If the free stream Mach Number is 0.6. Calculate Cp at this point.

Derive expression for induced velocity by finite and infinite ,vortex tube

What is whitcomb airfoil

Astraight finite wing has aspect ratio 8 operating at angle of attack 40.calculate C (induced drag coefficient) and Cassume Di L that wing identical to flat plate

Using KJT transform cylinder into symmetrical airfoil1

State Helmholtz’s theorem

Consider flow over the NACA 2412 airfoil where Re 3240000. x Calculate the boundary layer thickness at 1.5 m from leading edge

Define Critical Mach number and Drag Divergence Mach Number? Explain both the terms in detail with a proper diagram.