Q.1
##### What is the use of inlet section?
• a) Slow down the incoming air
• b) Increase the mach number of incoming air
• c) Increase lift by wing
• d) Increase lift curve slope of tail
Q.2
##### Inlet pressure recovery is defined as ______
• a) total pressure deliver to the engine divided by freestream total pressure
• b) total dynamic pressure
• c) incoming velocity by incoming Mach number
• d) lift to drag ratio
Q.3
##### Which of the following is a type of inlet?
• a) NACA flush inlet
• b) Flap
• c) Slat
• d) Fuselage
Q.4
##### Following diagram represents ______
• a) NACA flush inlet
• b) Helical inlet
• c) Flash inlet
• d) Pitot tube cavity
Q.5
##### Following diagram represents _____
• a) Pitot inlet
• b) Flush inlet
• c) NACA flush inlet
• d) Bell inlet
Q.6
##### Following diagram represents ______
• a) Conical inlet
• b) Spiral inlet
• c) NACA flush mount
• d) Pitot inlet
Q.7
##### Following diagram represents ______
• a) 2D ramp inlet
• b) Conical inlet
• c) Pitot inlet
• d) Flush inlet
Q.8
• a) 1.548
• b) 1.601
• c) 1.08
• d) 1.65
Q.9
##### Following diagram represents _____
• a) Mixed isentropic compression inlet
• b) Mixed Isotropic expansion
• c) Isotropic compression
• d) Isothermal expansion
Q.10
• a) True
• b) False
Q.11
• a) 0.8
• b) 0.1
• c) 0.3
• d) 0.4
Q.12
• a) 4.9
• b) 1.8
• c) 2
• d) 3.4
Q.13
##### If an aircraft has maximum Mach number of 2 and bypass ratio of 0.then, what will be the weight of the engine? (Find the approximate value. Given thrust at takeoff isUnit.)
• a) 1058.5 unit
• b) 12000 unit
• c) 120
• d) 234.585 unit
Q.14
• a) 219
• b) 100
• c) 301
• d) 183.129
Q.15
##### At which diameter we should design a supersonic after burning engine for a fighter which will have thrust at takeoffUnit and bypass ratio of 0.7.
• a) 114.67 unit
• b) 160.78 unit
• c) 350.39 unit
• d) 235.78 unit