Aerospace Engineering GATE 2013 Questions with Answer

Ques 1 Aerodynamics

The x and y velocity components of a two dimensional flow field are, u=(cy)/(x²+y²) v=(cx)/(x²+y²) where c is a constant. The streamlines are a family of

Ques 2 Aerodynamics

Which one of the following statements is NOT TRUE for a supersonic flow?

Ques 3 Aerodynamics

Consider a compressible flow where an elemental volume of the fluid is δ9, moving with velocity Which one of the following expressions is TRUE?

Ques 4 Aerodynamics

Consider a thin flat plate airfoil at a small angle α to an oncoming supersonic stream of air. Assuming the flow to be inviscid, C_d/C₁² is

Ques 5 Aerodynamics

The critical Mach number for a flat plate of zero thickness, at zero angle of attack, is

Ques 6 Aerodynamics

Consider one-dimensional isentropic flow at a Mach number of 0.5. If the area of cross-section of a streamtube increases by 3% somewhere along the flow, the corresponding percentage change in density is

Ques 7 Aerodynamics

The potential flow model for a storm is represented by the superposition of a sink and a vortex. The stream function can be written in the (r,0) system as ψ=-(Λ/(2π))θ+(Γ/(2π))ln r, where Λ=Γ=100 m²/s. Assume a constant air density of 1.2 kg/m³ The gauge pressure at a distance of 100 m from the storm eye is

Ques 8 Aerodynamics

Three identical eagles of wing span s are flying side by side in a straight line with no gap between their wing tips. Assume a single horse shoe vortex model (of equal strength ) for each bird. The net downwash experienced by the middle bird is

Ques 9 Aerodynamics

Streamline pattern of flow past a cylinder is shown in the figure below. The oncoming flow is steady, irrotational and incompressible. The flow is from left to right. Bernoulli's equation CANNOT be applied between the points

Ques 10 Aerodynamics

Consider a supersonic stream at a Mach number M=2. undergoing a gradual expansion. The stream is turned by an angle of 3 degrees due to the expansion. The following data is given.

Ques 11 Aerodynamics

Circulation theory of lift is assumed for a thin symmetric airfoil at an angle of attack α. Free stream velocity is U.
If the circulation at the quarter chord (c/4) of the airfoil is Γ₁ the normal velocity is zero at

Ques 12 Aerodynamics

Circulation theory of lift is assumed for a thin symmetric airfoil at an angle of attack α. Free stream velocity is U.
A second identical airfoil is placed behind the first one at a distance of c/2 from the trailing edge of the first. The second airfoil has an unknown circulation Γ₂ placed at its quarter chord. The normal velocity becomes zero at the same chord-wise locations of the respective airfoils as in the previous question. The values of Γ₁ and Γ₂ are respectively

Ques 13 Aerospace Propulsion

Consider two engines P and Q. In P, the high pressure turbine blades are cooled with a bleed of 5% from the compressor after the compression process and in Q the turbine blades are not cooled. Comparing engine P with engine Q, which one of the following is NOT TRUE?