Aerospace Engineering
GATE AE Compressible Flows PYQs
Build your understanding with focused practice from past exam papers.
Questions 11–20 of 41. Imported answers require independent review unless marked reviewed.
Question 43
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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 possible for the attached oblique shocks, which one of the following options is TRUE?
Your answerChoose one option.
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Air flowing at Mach number M = 2 from left to right accelerates to M = 3 across an expansion corner as shown in the figure. What is the value of
(the angle between the Forward and Rearward Mach lines) in degrees?The values of the Prandtl-Meyer functions are
and
. 
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You can attempt this question now. Sign in to view the answer key, explanations and discussion.Log in to check answerQuestion 59
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Consider the following Fanno flow problem: Flow enters a constant area duct at a temperature of 273 K and a Mach number 0.2 and eventually reaches sonic condition (Mach number = 1) due to friction. Assume
. The static temperature at the location where sonic condition is reached is ____________ K (rounded off to 2 decimal places).Log in to check the answer
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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 in the figure. Select all the correct statement(s) as per oblique shock theory when the flight Mach number M is increased.
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A perfect gas stored in a large reservoir exhausts into the atmosphere through a convergent duct. The reservoir pressure is
and temperature is
. The jet emerges from the nozzle at choked conditions with average velocity
, Mach number M, pressure p, temperature T, and density
. If the reservoir pressure is increased, thenYour answerChoose one option.
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You can attempt this question now. Sign in to view the answer key, explanations and discussion.Log in to check answerQuestion 41
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A scramjet engine features an intake, isolator, combustor, and a nozzle, as shown in the schematic. Station 3 indicates the combustor entry point. Assume stagnation enthalpy to be constant between Stations 1 and 3, and air to be a calorically perfect gas with specific heat ratio
. Select the correct expression for Mach number
at the inlet to the combustor from the options given. 
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You can attempt this question now. Sign in to view the answer key, explanations and discussion.Log in to check answerQuestion 44
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Consider a one-dimensional inviscid supersonic flow in a diverging duct with heat addition (
) as shown. Which of the following statement(s) is/are always TRUE? 
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You can attempt this question now. Sign in to view the answer key, explanations and discussion.Log in to check answerQuestion 14
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The point of maximum entropy on a Fanno-curve in a Temperature-Entropy (T-s) diagram represents the
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Across an oblique shock wave in a calorically perfect gas,
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A convergent nozzle fed from a constant pressure, constant temperature reservoir, is discharging air to atmosphere at 1 bar (absolute) with choked flow at the exit (marked as Q). Flow through the nozzle can be assumed to be isentropic. If the exit area of the nozzle is increased while all the reservoir parameters and ambient conditions remain the same, then at steady state
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