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.
Evaluate downstream Mach number if an oblique shock is observed at inlet with shock angle of 40.30°. Consider upstream Mach number is 1.Use following shock table.
- 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.
Typically, diffuser length is about eight times the diameter for supersonic application.
- a) True
- b) False
Q.11.
If bypass ratio of subsonic non afterburning engine is found to be 2.1 then, what will be the specific fuel consumption of the same engine at cruise?
- a) 0.8
- b) 0.1
- c) 0.3
- d) 0.4
Q.12.
We need to design a supersonic fighter with afterburner which has maximum Mach number of 1.If thrust at takeoff isunit and bypass ratio is 0.then, find ratio of length to the diameter for this engine.
- 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.
Calculate the approximate value of length at which supersonic after burning engine could be design in such a way that thrust at takeoff will beunit and maximum Mach number will be 2.12.
- 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