Aircraft Design Practice Test 6

1. Consider a flow with 0.5M. Now, as area decreases, velocity of the flow inside convergent section _____________

decreases

velocity is independent of area

increases

reduces by half always

2. Find the diameter ratio of an engine which has mach number of 0.7. Consider isentropic flow.

5.64

2.045

3.45

1.045

3. Following diagram represents ___________

typical turbo jet

turbofan

reciprocating

turboprop

4. An aircraft is supported by bicycle landing gear arrangement. If wheel base is 10 unit then, scale location of CG.

25 unit from back wheel

20 unit from front wheel

5 unit aft from front wheel

10 unit

5. Following diagram represents _____

Mixed Isotropic expansion

Isothermal expansion

Isotropic compression

Mixed isentropic compression inlet

6. Evaluate downstream Mach number if an oblique shock is observed at inlet with shock angle of 40.30°. Consider upstream Mach number is 1.65. Use following shock table.

Upstream Mach number	Shock angle	Downstream Mach Number
1.60	49.51	1.281
1.65	40.30	1.548
1.60	38.66	1.601
1.65	37.28	1.651
1.5	64.35	0.961

1.08

1.65

1.548

1.601

7. Following diagram represents ___________

piston prop aircraft

turboprop design

turbojet engine with centrifugal compressor

piston engine

8. Following diagram represents ______

Conical inlet

2D ramp inlet

Flush inlet

Pitot inlet

9. We need to design a supersonic fighter with afterburner which has maximum Mach number of 1.8. If thrust at takeoff is 10000 unit and bypass ratio is 0.71 then, find ratio of length to the diameter for this engine.

3.4

1.8

4.9

10. Propeller has diameter of 25 unit. What will be the static tip speed of the propeller? (Given n = 1200rpm.)

3004.5

2345.67 unit

1570.8 unit

7643.23