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Aircraft Design Practice Test: Propulsion and Fuel System Integration
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Propulsion and Fuel System Integration topics include: Propulsion selection, fuel system, jet engine and propeller engine integration. Propulsion system integration refers to the technology that combines propulsion systems with aircraft structures to meet an aircraft's mission. This includes combining engines, fuel systems, and exhaust systems.  Propulsion system integration involves aerodynamic, structural, and subsystem interfaces. These interfaces can include fuel, pneumatic, hydraulic, electrical, and control systems.  Propulsion system integration also ensures that the installed... Show more
Aircraft Design Practice Test: Propulsion and Fuel System Integration
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25 Questions

1. 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?
2. ____________ is the most common type of boundary layer diverter used for supersonic applications.
3. 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.
4. Inlet location will not affect engine performance.
5. Which of the following is correct?
6. Fuel system includes ____________
7. Typical fighter is designed to operate at high angle of attack. Estimate the range of required boundary layer diverter thickness if fuselage length in front of the inlet is 10 unit.
8. Determine the corrections or otherwise of the following Assertion [A] and Reason [R]:
Assertion [A]: Total fuel CG is located near to the aircraft CG.
Reason[R]: Fuel can be located at centre, at tip or at tail.
9. Evaluate required scale factor if ratio of weight of the rubber engine and the actual selected engine is 0.8.
10. Diameter of rubber engine is 94 inch and required scale factor is 0.7 then, what will be the actual diameter of selected engine?
11. A turboprop engine is to be scaled from an existing engine. If scale factor is 0.85 then, what will be the value of diameter of our engine? Given actual diameter of selected existing engine is 8.56unit.
12. What is the function of a compressor?
13. What do you mean by scale factor in terms of rubber engine?
14. Find the ratio of weight to length of the turboprop engine which has bhp of 3000.
15. Which of the following is not the type of fuel tank?
16. Which of the following is an incorrect example for BL diverter?
17. If bypass ratio of subsonic non afterburning engine is 1.5 then, what will be the value of maximum thrust specific fuel consumption.
18. Inlet pressure recovery is defined as ______
19. Large cowl lip radius will produce ____________
20. A typical turbine engine consists of __________
21. Consider a flow with 0.5M. Now, as area decreases, velocity of the flow inside convergent section _____________
22. Integral tanks are ___________
23. Calculate the approximate value of length at which supersonic after burning engine could be design in such a way that thrust at takeoff will be 29800 unit and maximum Mach number will be 2.12.
24. Which of the following is an advantage of nose inlet?
25. What is the function of a typical nozzle?

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