Aerospace Engineering > GATE 2011 > Shock Waves
Consider an inviscid, adiabatic flow of air at free stream Mach Number, M∞ = 2, across a compression corner (θ = 20°) as shown. The free stream total enthalpy is h∞ = 810 kJ kg–1. Assume that air is calorically perfect with γ = 1.4, R = 287 J kg–1 K–1.
The total temperature at point P is
A
806.37 K
B
1128.92 K
C
1612.74 K
D
2257.84 K

Correct : a

Similar Questions

Shock structures for flow at three different Mach numbers over a given wedge are shown in the figure below. Assuming that only the weak shock solutions are poss...
#51 MCQ
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...
#110 MSQ
Across an oblique shock wave in a calorically perfect gas, _______.
#163 MSQ

Related Topics

GATE Aerospace Engineering 2011 GATE AE 2011 Q51 compression corner adiabatic flow total temperature supersonic flow compressible flow aerodynamics oblique shock wave compression corner inviscid adiabatic flow total enthalpy

Unique Visitor Count

Total Unique Visitors

Loading......

Question Options

Contributed by: