Which of the following best describes a shock polar?

Shock polar is the graphical representation of weak shocks properties

Shock polar is the locus of all the velocities behind the shock for varying deflection angle from zero to the maximum deflection angle

Shock polar is the graphical representation of normal shock properties

Shock polar is the locus of all the shock angles behind the shock for varying Mach number from one to infinity

Correct Answer : Shock polar is the locus of all the velocities behind the shock for varying deflection angle from zero to the maximum deflection angle

Explanation : Shock polar is a graphical representation of oblique shock properties. It is the loci of all such points for deflection angle from zero to maximum deflection, representing all the velocities behind the shock.

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.