GATE Aerodynamics: Airfoils and wings: coefficients, Kutta-Joukowski theorem, thin airfoil theory, finite wing theory, critical and drag divergence Mach numbers – Previous Year Questions
23 GATE previous year questions on Airfoils and wings: coefficients, Kutta-Joukowski theorem, thin airfoil theory, finite wing theory, critical and drag divergence Mach numbers (Aerodynamics, Aerospace Engineering) with answers and explanations, from every paper.
- GATE 2021 AE Q25 – Which statements about the Kutta condition are correct?
- GATE 2021 AE Q26 – For a cambered airfoil in thin-airfoil theory, which are correct?
- GATE 2021 AE Q51 – An elliptic wing has aspect ratio 10, section lift slope 2 per radian and angle of attack 5°. Its induced-drag coefficient is (three decimals)
- GATE 2022 AE Q26 – NACA 2412 airfoil has
- GATE 2022 AE Q51 – A wing has (y)= 0(1-2 y /b) for y b/2. Span b=10 m, peak circulation 20 m²/s, density 1.2 kg/m³ and speed 80 m/s. Wing lift (nearest integer N) is .
- GATE 2022 AE Q54 – Consider a thin symmetric airfoil at 2 degree angle of attack in a uniform flow at 50 m/s. The pitching moment coefficient about its leading edge is…
- GATE 2023 AE Q14 – A two-dimensional potential flow solution for flow past an airfoil has a streamline pattern as shown in the figure. Which of the following conditions…
- GATE 2023 AE Q18 – The figures shown in the options are schematics of airfoil shapes (not to scale). For a civilian transport aircraft designed for a cruise Mach number…
- GATE 2023 AE Q46 – For an airfoil, which critical and drag-divergence Mach-number relations are correct?
- GATE 2023 AE Q56 – A thin cambered airfoil has zero lift at −1.1°. Below stall, its lift coefficient at 4° (two decimal places) is .
- GATE 2026 AE Q20 – The fundamental purpose of the Kutta condition in the thin airfoil theory is .
- GATE 2026 AE Q29 – Which of the following statements is/are TRUE regarding critical and drag divergence Mach numbers of a wing?
- GATE 2026 AE Q35 – An elliptic wing has a span of 6 m and a planform area of 6 m2. When generating a lift coefficient of 0.6, the induced drag it incurs is 10-3 (rounded…
- GATE 2026 AE Q48 – What is/are the use(s) of the single horseshoe vortex model of finite wing aerodynamic theory?
- GATE 2026 AE Q54 – For an airfoil section the pitching moment coefficient is determined about a reference point that is 0.3 times the chord behind the leading edge. It…
- GATE 2026 AE Q56 – Consider a finite wing of aspect ratio 10 with span effectiveness factor 0.95. Its airfoil section has a lift slope of 0.106 per degree and a…
- GATE 2026 AE Q63 – Thin airfoil theory predicts the zero-lift angle of attack L=0 of NACA 2412 airfoil as -2.1. The corresponding prediction of L=0 for NACA 5410 airfoil…
- GATE 2025 AE Q18 – For a NACA 4415 airfoil, the location of maximum camber, as a fraction of the chord length from the leading edge, is .
- GATE 2025 AE Q19 – A positively cambered airfoil is placed in a uniform flow (velocity, U ) at its zero-lift angle of attack. M is the corresponding pitching moment.…
- GATE 2025 AE Q36 – A lifting surface has a spanwise circulation distribution of () = A 3 (where A 0) over its span -b2 y b2, and y = -b2 is the spanwise coordinate.…
- GATE 2024 AE Q24 – Consider steady, incompressible, inviscid flow past two airfoils shown in the figure. The coefficient of pressure at the trailing edge of the airfoil…
- GATE 2024 AE Q35 – Using thin airfoil theory, the lift coefficient of a NACA 0012 airfoil placed at 5o angle of attack in a uniform flow is (rounded off to 2 decimal…
- GATE 2024 AE Q64 – An airplane of mass 1000 kg is in a steady level flight with a speed of 50 m/s. The wing has an elliptic planform with a span of 20 m and planform…