Engineering Questions with Answers - Multiple Choice Questions

# Aerodynamics – Physical Aspects of Supersonic Flow over Cones

1 - Question

For a given cone angle and freestream Mach number, how many oblique shock(s) is/are present?
a) 1
b) 2
c) 4
d) Infinity
Explanation: For a conical flow placed in a freestream Mach number M∞ with a particular cone angle θc, there exists two oblique shock waves which is a result of one weak and one strong solution. It is similar to the case of wedge where using θ – β – M graph we obtain two shock waves.

2 - Question

Under which condition do we get the detached shock wave on a cone?
a) θc = θcmax
b) θc > θcmax
c) θc = 0
d) θc = infinty
Explanation: For a given freestream Mach number M∞, there exists a maximum cone angle for which if we go beyond that value, the shock wave originating at the cone’s vertex gets detached. Thus, the condition for detached shock wave is θc > θcmax.

3 - Question

The shock wave present on the cone is weaker than the one on the wedge for a particular angle.
a) True
b) False
Explanation: For a particular cone angle, the shock wave formed at the cone’s vertex is usually weaker in strength compared to the shock wave formation on a wedge. This phenomenon is due to the three – dimensional relieving effect.

4 - Question

What is the relation between maximum allowed cone angle and wedge angle for attached shock wave?
a) (θmax)wedge = (θmax)cone
b) (θmax)wedge > (θmax)cone
c) (θmax)wedge < (θmax)cone
d) (θmax)wedge ≈ (θmax)cone
Explanation: Due to the three-dimensional relieving effect, for a particular freestream Mach number, the maximum cone angle allowed is larger than the maximum wedge angle before the shock wave becomes detached.

5 - Question

How are the streamlines for a conical flow behind a shock wave?
a) Parallel throughout
b) Curved at the beginning, parallel as surface tends to infinity
c) Curved till surface tends to infinity
d) Conical
Explanation: For a conical flow at a given Mach number, the shock formation occurs at the vertex of the cone. The streamlines behind the shock wave are initially curved due to 3 – dimensional space unlike streamlines behind the shockwave on a wedge which is parallel. These streamlines eventually become parallel at the cone’s surface tends to infinity.

6 - Question

The flow is parallel behind the shock wave in a cone.
a) True
b) False
Explanation: When the incoming flow passes through an oblique shock in a two – dimensional wedge, the streamline becomes parallel to the surface of the wedge. But, in case of a cone, the streamlines between the shock wave and the cone are not parallel.

7 - Question

Where does the flow remain supersonic in a conical surface?
a) Between the oblique shock and the sonic line
b) Between the oblique shock and the conical surface
c) Between the sonic line and the conical surface
d) Flow is not supersonic beyond the oblique shock
Explanation: The incoming flow over a cone is mostly supersonic between the surface of the cone and the oblique shock wave. Except in some cases when the half cone angle is large, flow sometimes becomes subsonic and one of the rays originating the cone’s vertex acts at the sonic line. The flow between the sonic line and the oblique shock thus remains supersonic.

8 - Question

What happens to the shock wave when the cone angle is less than the maximum cone angle?
a) Oblique shock formation does not occur
b) Shock wave becomes detached
c) Shock wave is attached to the cone
d) There is formation of normal shock wave