List of top Aerodynamics Questions on Shock

A supersonic stream of an ideal gas at Mach number \( M_1 = 5 \) is turned by a ramp, as shown in the figure. The ramp angle is 20°. The pressure ratio is \( \frac{p_2}{p_1} = 7.125 \) and the specific heat ratio is \( \gamma = 1.4 \). The pressure coefficient on the ramp surface is __________ (rounded off to two decimal places).

A supersonic stream of an ideal gas at Mach number \( M_1 = 5 \) is turned by a ramp, as shown in the figure. The ramp angle is 20°. The pressure ratio is \( \frac{p_2}{p_1} = 7.125 \) and the specific heat ratio is \( \gamma = 1.4 \). The pressure coefficient on the ramp surface is ___________ (rounded off to two decimal places).

A supersonic stream of an ideal gas at Mach number \( M_1 = 5 \) is turned by a ramp, as shown in the figure. The ramp angle is 20°. The pressure ratio is \( \frac{p_2}{p_1} = 7.125 \) and the specific heat ratio is \( \gamma = 1.4 \). The pressure coefficient on the ramp surface is \_\_\_\_\_\_\_\_ (rounded off to two decimal places).
A supersonic stream of an ideal gas at Mach number \( M_1 = 5 \) is turned by a ramp, as shown in the figure. The ramp angle is 20°. The pressure ratio is \( \frac{p_2}{p_1} = 7.125 \) and the specific heat ratio is \( \gamma = 1.4 \). The pressure coefficient on the ramp surface is \_\_\_\_\_\_\_\_ (rounded off to two decimal places).
A supersonic stream of an ideal gas at Mach number \( M_1 = 5 \) is turned by a ramp, as shown in the figure. The ramp angle is 20°. The pressure ratio is \( \frac{p_2}{p_1} = 7.125 \) and the specific heat ratio is \( \gamma = 1.4 \). The pressure coefficient on the ramp surface is \_\_\_\_\_\_\_\_ (rounded off to two decimal places).

Attached weak oblique shocks over the same wedge are sketched for three different upstream Mach numbers \(M_1, M_2, M_3 > 1\). Which ordering is TRUE? 

Air at Mach number \(M=2\) expands around a convex corner to \(M=3\). What is the angle \(\delta\) between the forward and rearward Mach lines of the Prandtl–Meyer expansion fan (in degrees)? Given \(\nu(3)=49.76^\circ\) and \(\nu(2)=26.38^\circ\). 

A supersonic aircraft has an air intake ramp that can be rotated about the leading edge \(O\) such that the shock from the leading edge meets the cowl lip as shown. Select all the correct statement(s) as per oblique shock theory when flight Mach number \(M\) increases.

For an airfoil, which of the relations about the critical Mach number $M_{cr}$ and drag divergence Mach number $M_{dd}$ are correct?