For a flow with Mach number 4, P1 = 2.65 × 10^4 Pa what is the pressure behind the oblique shock wave having shock angle as 30 degrees?(a) 8.525 × 10^4 Pa(b) 11.925 × 10^4 Pa(c) 4.502 × 10^4 Pa(d) 15.278 × 10^4 PaThe question was posed to me in an interview for job.My doubt stems from Mach Number Independence in chapter Transonic and Hypersonic Flows of Aerodynamics

For a flow with Mach number 4, P1 = 2.65 × 10^4 Pa what is the pressu

1.	For a flow with Mach number 4, P1 = 2.65 × 10^4 Pa what is the pressure behind the oblique shock wave having shock angle as 30 degrees?(a) 8.525 × 10^4 Pa(b) 11.925 × 10^4 Pa(c) 4.502 × 10^4 Pa(d) 15.278 × 10^4 PaThe question was posed to me in an interview for job.My doubt stems from Mach Number Independence in chapter Transonic and Hypersonic Flows of Aerodynamics
Answer» The correct option is (b) 11.925 × 10^4 Pa Easy EXPLANATION: Given, P1 = 2.65 × 10^4 Pa, M1 = 4, β = 30° The NORMAL COMPONENT of the Mach number upstream of the shockwave is given by: MN1 = M1sinβ = 4sin⁡(30) = 2 Using the normal shock table, for Mn1 = 2 we get the relation between the pressure upstream and DOWNSTREAM \(\frac {P_2}{P_1}\) = 4.5 Since P1 = 2.65 × 10^4, we get P2 = 4.5 × 2.65 × 10^4 = 11.925 × 10^4 Pa.

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