List of top Aerospace Engineering Questions

A simply supported beam is changed to a beam with fixed ends. The order of static indeterminacy will
If a member is subjected to an axial tensile load then the plane inclined at \(45^\circ\) to the axis of the loading carries
The work done in producing strain on a material per unit volume is called
The Prandtl–Glauert rule gives the relation between
When Mach tends to infinity the radius of shock polar is
When heat is added in a constant area duct without friction (i.e., in Rayleigh flow), which of the following statements is true?
If a rod tapers uniformly from 30 mm to 15 mm diameter in a length of 350 mm, if it is subjected to an axial load of 5.6 kN and the extension of the rod is 0.025 mm, then the modulus of elasticity of the rod is
Toughness is the ability of the material to absorb energy
In a supersonic flow, the indicated Pitot pressure \(p_t\) is measured by a Pitot probe for calculating the flow Mach number, which of the following relation is used
A gas is said to be thermally perfect when
For compressible flow, which one of the following is true?
If the Mach number tends to infinity, what would be the measured density?
The correct statement, for a flow across an oblique shock is
If a series of shock waves is used to decelerate supersonic flow to subsonic speed, then the variation of the shock wave will be
Which one of the following statements is not true for a supersonic flow?
According to Kutta condition, if the trailing edge is cusped, then the velocities leaving the top (\(V_1\)) and bottom (\(V_2\)) surfaces at the trailing edge should be
In thin airfoil theory the lift curve slope is usually considered as
The velocity induced at a point \(P\) by the semi-infinite vortex filament is
The incompressible continuity equation in polar coordinates is written as
Fire Stoke’s 1st comparison of pressure forces and friction forces acting on any given fluid element shows that
The velocity potential \(\phi\) for a vortex flow is given by
In lifting flow over a cylinder the location of stagnation points when \(\Gamma = 4\pi U R\) is
At low values of incidence, the center of pressure
The amount of lift generated in the non-rotating flow over a circular cylinder is
Kutta-Joukowski’s theorem is defined for