The GATE Grind

GATE Aerodynamics: Compressible flows: isentropic flow, normal and oblique shocks, Prandtl-Meyer flow, nozzles and diffusers – Previous Year Questions

16 GATE previous year questions on Compressible flows: isentropic flow, normal and oblique shocks, Prandtl-Meyer flow, nozzles and diffusers (Aerodynamics, Aerospace Engineering) with answers and explanations, from every paper.

  1. GATE 2021 AE Q24 (1 mark, Multiple select) – Across an oblique shock, which statements hold?
  2. GATE 2021 AE Q39 (2 marks, Multiple choice) – The shown optical arrangement for visualizing compressible-flow density gradients, without a knife edge, is
  3. GATE 2021 AE Q43 (2 marks, Multiple select) – A normal shock moves into stationary gas. Unprimed properties use the laboratory frame; primed properties use the shock-fixed frame. Subscripts 1,2…
  4. GATE 2022 AE Q25 (1 mark, Multiple select) – Across an oblique shock wave in a calorifically perfect gas,
  5. GATE 2022 AE Q55 (2 marks, Numerical answer) – A convergent-divergent nozzle with adiabatic walls is designed for an exit Mach number of 2.3. It is discharging air to atmosphere under the…
  6. GATE 2023 AE Q33 (1 mark, Numerical answer) – The ratio of the speed of sound in H2 (molecular weight 2 kg/kmol) to that in N2 (molecular weight 28 kg/kmol) at temperature 300 K and pressure 2 bar…
  7. GATE 2023 AE Q37 (2 marks, Multiple choice) – 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…
  8. GATE 2023 AE Q44 (2 marks, Multiple select) – Consider a one-dimensional inviscid supersonic flow in a diverging duct with heat addition (Qin) as shown. Which of the following statement(s) is/are…
  9. GATE 2026 AE Q21 (1 mark, Multiple choice) – In the figure shown below, the flow at the nozzle exit is .
  10. GATE 2026 AE Q64 (2 marks, Numerical answer) – Consider a centered Prandtl-Meyer expansion fan at a = 4 corner in a Mach 1.78 air flow, as shown in the figure below. The angle (see figure) made by…
  11. GATE 2025 AE Q49 (2 marks, Numerical answer) – 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 20o. The pressure ratio is p…
  12. GATE 2025 AE Q51 (2 marks, Numerical answer) – The mass flow rate in a supersonic wind tunnel is 2 kg/s when the stagnation pressure and stagnation temperature are 1 MPa and 800 K, respectively. If…
  13. GATE 2024 AE Q22 (1 mark, Multiple choice) – On Day 1, an aircraft flies with a speed of V 1 m/s at an altitude where the temperature is T 1 K. On Day 2, the same aircraft flies with a speed of…
  14. GATE 2024 AE Q23 (1 mark, Multiple choice) – Consider a steady, isentropic, supersonic flow (Mach number M > 1) entering a Convergent-Divergent (CD) duct as shown in the figure. Which one of the…
  15. GATE 2024 AE Q43 (2 marks, Multiple choice) – 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…
  16. GATE 2024 AE Q44 (2 marks, Multiple choice) – 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…