Question 31. Consider the low earth orbit (LEO) and the geo synchronous orbit (GSO). Then

Question 32. Which one of the following shows the CORRECT variation of stagnation temperature along the axis of an ideal ram jet engine?

Question 33. A rocket motor has a chamber pressure of 100 bar and chamber temperature of 3000 K. The ambient pressure is 1 bar. Assume that the specific heat at constant pressure is 1 kJ/kg-K. Also assume that the flow in the nozzle is isentropic and optimally expanded. The exit static temperature in K is

Question 34. Given that the Laplace transform, L(eat) = 1/(s - a) then L(e5t sinh 5t)

Question 35. Which one of the following criteria leads to maximum turn rate and minimum radius in a level turn flight?

Question 36. A function y(t) satisfies the differential equation d2y/dt2 -2 dy/dt + y = 0 and is subject to the initial conditions y(t = 0) = 0 and dy/dt (t = 0) = 1. The value of y(t = 1) is

Question 37. A glider is launched from a 500m high hilltop. Following data is available for the glider: Zero lift drag coefficient CD0 = 0.02 , aspect ratio AR = 10 and Oswald efficiency factor e = 0.95. The maximum range of the glider in km is _________

Question 38. Consider an airplane with rectangular straight wing at dihedral angle T = 100 . Lift curve slope of wing airfoil section (constant over the whole span of the wing) is cla = 5.4/rad. The roll stability derivative, Clb in per radian is __________

Question 39. A thin long circular pipe of 10 mm diameter has porous walls and spins at 60 rpm about its own axis. Fluid is pumped out of the pipe such that it emerges radially relative to the pipe surface at a velocity of 1 m/s. [Neglect the effect of gravity.] What is the radial component of the fluid's velocity at a radial location 0.5 m from the pipe axis?

Question 40. A wing and tail are geometrically similar, while tail area is one-third of the wing area and distance between two aerodynamic centres is equal to wing semi-span (b/2). In addition, following data is applicable: ∈α = 0.3, CL = 1.0, CLα 0.08/ deg., c = 2.5 , b = 30m , CMac = 0, ηt = 1. The symbols have their usual aerodynamic interpretation. The angle of incidence of tail to trim the wing-tail combination for a 5% static margin is