Aerospace Engineering GATE 2016 Questions with Answer

Ques 1 Aerodynamics

The maximum value of coefficient of lift (C₁) for a 2D circular cylinder, provided at least one stagnation point lies on the cylinder surface, is predicted by the potential flow theory to be

Ques 2 Aerodynamics

The nozzle AB, as shown below, leading to the test section of a low speed subsonic wind tunnel, has a contraction ratio of 10:1. The pressure difference across the nozzle is maintained at 1000 N/m² and the density of air is 1.23 kg/m³ Assuming one-dimensional, steady, inviscid flow, the velocity in the test section as measured at point B is _______ m/s.

Ques 3 Aerodynamics

The rate of change of moment coefficient with respect to the angle of attack, dC_m/dα , at half chord point of a thin airfoil, as per approximations from the thin airfoil theory is

Ques 4 Aerodynamics

An untwisted wing of elliptic planform and aspect ratio 6 consists of thin symmetric airfoil sections. The coefficient of lift (C_L) at 10° angle of attack assuming inviscid incompressible flow is

Ques 5 Aerodynamics

Consider 1-D, steady, inviscid, compressible flow through a convergent nozzle. The total temperature and total pressure are T₀, P_o respectively. The flow through the nozzle is choked with a mass flow rate of m˙_o If the total temperature is increased to 4T_o, with total pressure remaining unchanged, then the mass flow rate through the nozzle

Ques 6 Aerodynamics

With increase in airfoil thickness, the critical Mach number for an airfoil is likely to

Ques 7 Aerodynamics

Due to a body in potential flow, the velocity at a point A in the flow field is 20 m/s while the free stream velocity is only 10 m/s. The value of coefficient of pressure (C_p) at the point A is

Ques 8 Aerodynamics

Which of the following airfoil will have location of the maximum camber at half chord length from the leading edge?

Ques 9 Aerodynamics

For a laminar incompressible flow past a flat plate at zero angle of attack, the variation of skin friction drag coefficient (C_f) with Reynolds number based on the chord length (Re_c) can be expressed as

Ques 10 Aerodynamics

Which of the following statement is NOT TRUE across an oblique shock wave?

Ques 11 Aerodynamics

For a completely subsonic isentropic flow through a convergent nozzle, which of the following statement is TRUE?

Ques 12 Aerodynamics

Air, with a Prandtl number of 0.7, flows over a flat plate at a high Reynolds number. Which of the following statement is TRUE?

Ques 13 Aerospace Propulsion

An un-mixed turbofan engine with a bypass ratio of 6.0, flies with a velocity of 200 m/s. The core and the bypass nozzles of the engine, that are both convergent nozzles, operate under choked condition and have exhaust static temperatures of 580 K and 295 K, respectively. The specific gas constant and the ratio of specific heats for both the streams are 287 J/kgK and 1.4, respectively. If the fuel-air ratio is negligible, the thrust per unit mass flow rate generated by the engine is _______ Ns/kg.