For a thin airfoil kept at a supersonic flow of Mach number 3 at an in – McqOptions

MCQOPTIONS

1.	For a thin airfoil kept at a supersonic flow of Mach number 3 at an inclination of 2 degrees, what is the coefficient of pressure?
A.	0.47
B.	1.51
C.	1.78
D.	2.83
Answer» E.

Discussion

No Comment Found

Related MCQs

The linearized pressure distribution for Mach number greater than 5 matches the coefficient of pressure derived from the exact shock theory.
Which of these assumptions is not made while formulating the linearized supersonic flow?
For a thin airfoil kept at a supersonic flow of Mach number 3 at an inclination of 2 degrees, what is the coefficient of pressure?
For a biconvex airfoil, what sign convention is used for the value of while computing the coefficient of pressure?
Linearized equations give the exact results as obtained by the non linear equations.
What is the coefficient of lift according to the linearized theory over a flat plate kept at an inclination of 4 degrees having freestream Mach number of 3?
For an airfoil kept at supersonic flow, how does the coefficient of pressure vary with an increase in Mach number?
The linearized perturbation velocity potential equation for supersonic flow takes form of which of these partial differential equations?
Which of these is the linearized perturbation velocity potential equation over a thin airfoil in a supersonic flow?