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- Question 1 of 15
During the ground roll manoeuvre of an aircraft, the force(s) acting on it parallel to the direction of motionCorrectIncorrect
- Question 2 of 15
An aircraft in a steady climb suddenly experiences a 10% drop in thrust. After a new equilibrium is reached at the same speed, the new rate of climb isCorrectIncorrect
- Question 3 of 15
In an aircraft, the dive manoeuvre can be initiated byCorrectIncorrect
- Question 4 of 15
In an aircraft, elevator control effectiveness determinesCorrectIncorrect
- Question 5 of 15
The Mach angle for a flow at Mach 2.0 isCorrectIncorrect
- Question 6 of 15
Bernoulli’s equation is valid under steady stateCorrectIncorrect
- Question 7 of 15
The ratio of flight speed to the exhaust velocity for maximum propulsion efficiency isCorrectIncorrect
- Question 8 of 15
A rocket is to be launched from the bottom of a very deep crater on Mars for earth return. The specific impulse of the rocket, measured in seconds, is to be normalized by the acceleration due to gravity atCorrectIncorrect
- Question 9 of 15
In a semi-monocoque construction of an aircraft wing, the skin and spar webs are the primary carriers ofCorrectIncorrect
- Question 10 of 15
The logarithmic decrement measured for a viscously damped single degree of freedom system is 0.125. The value of the damping factor in % is closest toCorrectIncorrect
- Question 11 of 15
An aircraft has a steady rate of climb of 300 m/s at sea level and 150 m/s at 2500 m altitude. The time taken (in sec) for this aircraft to climb from 500 m altitude to 3000 m altitude isCorrectIncorrect
- Question 12 of 15
An airfoil generates a lift of 80 N when operating in a freestream flow of 60 m/s. If the ambient pressure and temperature are 100 kPa and 290 K espectively (specific gas constant is 287 J/kg-K), the circulation on the airfoil in m2/s isCorrectIncorrect
- Question 13 of 15
A rocket motor has combustion chamber temperature of 2600 K and the products have molecular weight of 25 g/mol and ratio of specific heats 1.2. The universal gas constant is 8314 J/kg-mole-K. The value of theoretical c* (in m/s) isCorrectIncorrect
- Question 14 of 15
If an aircraft takes off with 10% less fuel in comparison to its standard configuration, its range isCorrectIncorrect
- Question 15 of 15
An oblique shock wave with a wave angle β is generated from a wedge angle of θ. The ratio of the Mach number downstream of the shock to its normal component isCorrectIncorrect