What is curve generated in shock polar for Mach number equal to infinity?

Circle

Ellipse

Parabola

Hyperbola

Correct Answer : Circle

Explanation : When Mach number reaches infinity the shock polar is a circle. The circle lies between 0.41 to 2.45 characteristic Mach number values, which gives the diameter of the circle. This is the only circular curve other than the sonic circle in shock polar.

Recently Updated in Aerodynamics Questions

If there is a supersonic flow over a blunt edge, then the detached shock is observed. Where is the oblique shock observed in the detached shock?

On the blunt edge point

Far away from the edge

Just above the blunt edge point

Near the trailing edge of the section

Correct Answer : Option (C) : Just above the blunt edge point

Explanation : In a detached shock, the normal shock is observed on the blunt edge and then slowly loses strength and becomes an oblique shock just above the edge point. Finally the detached shock becomes a Mach line far away from the edge.

What is true about the flow properties above and below the discontinuity?

The pressure on both sides are different

The pressure on both sides are equal

The flow direction of both sides are different

The density and temperature are the same on both the sides

Correct Answer : Option (B) : The pressure on both sides are equal

Explanation : On either side of the discontinuity the flow direction needs to be same. The pressure is also same on both sides as the flow is not turning.

What is the shape of the pressure curve on the upper surface of a thin diamond wedge airfoil at zero angle of attack?

Pressure increases and becomes constant

Pressure decrease follows a parabolic path

Pressure decreases linearly in a straight line

Pressure increases instantly and becomes constant, and then suddenly becomes negative and becomes constant

Correct Answer : Option (D) : Pressure increases instantly and becomes constant, and then suddenly becomes negative and becomes constant

Explanation : According to shock expansion theory, shock wave interactions determine the aerodynamic loads on the surface of the airfoil. Oblique shock and expansion waves decrease and increase the pressure respectively.