Normal Shock: Asymptotic Downstream Mach Number (M2) | GATE AE 2015 Question 64

```

Aerospace Engineering > GATE 2015 > Normal Shock Waves

For a normal shock, the relation between the upstream Mach number (M₁) and the downstream Mach number (M₂) is given by M₂²=((γ-1)M₁²+2)/(2γM₁²+1-γ) For an ideal gas with γ=1.4 the asymptotic value of the downstream Mach number is

Correct : 0.37 to 0.39

Similar Questions

A strong normal shock wave, with a pressure ratio of 29 across it, is travelling into stationary air (γ=1.4) at T=280 K in a straight duct (see figure). T...

#458 Fill in the Blanks

A student needs to find velocity across a stationary normal shock. He measures density and pressure across the shock as shown in the figure below. 1bar=105Pa. (...

#662 NAT

If → denotes increasing order of intensity, then the meaning of the words dry → arid → parched is analogous to diet → fast → ______. Which one of the given opt...

#10 MCQ

Related Topics

normal shock Mach number relation downstream Mach number asymptotic Mach number ideal gas gamma Aerospace Engineering GATE 2015 GATE AE 2015 Q64 compressible flow

Unique Visitor Count

Total Unique Visitors

Loading......