MCQOPTIONS
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MCQOPTIONS
This section includes 9 Mcqs, each offering curated multiple-choice questions to sharpen your Aircraft Design knowledge and support exam preparation. Choose a topic below to get started.
| 1. |
At which diameter we should design a supersonic after burning engine for a fighter which will have thrust at takeoff 150000 Unit and bypass ratio of 0.7. |
| A. | 114.67 unit |
| B. | 160.78 unit |
| C. | 350.39 unit |
| D. | 235.78 unit |
| Answer» B. 160.78 unit | |
| 2. |
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. |
| A. | 219 |
| B. | 100 |
| C. | 301 |
| D. | 183.129 |
| Answer» B. 100 | |
| 3. |
If an aircraft has maximum Mach number of 2 and bypass ratio of 0.71 then, what will be the weight of the engine? (Find the approximate value. Given thrust at takeoff is 10000 Unit.) |
| A. | 1058.5 unit |
| B. | 12000 unit |
| C. | 120 |
| D. | 234.585 unit |
| Answer» B. 12000 unit | |
| 4. |
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. |
| A. | 4.9 |
| B. | 1.8 |
| C. | 2 |
| D. | 3.4 |
| Answer» B. 1.8 | |
| 5. |
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 |
| Answer» B. 0.1 | |
| 6. |
Typically, diffuser length is about eight times the diameter for supersonic application. |
| A. | True |
| B. | False |
| Answer» B. False | |
| 7. |
Which of the following is a type of inlet? |
| A. | NACA flush inlet |
| B. | Flap |
| C. | Slat |
| D. | Fuselage |
| Answer» B. Flap | |
| 8. |
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 |
| Answer» B. total dynamic pressure | |
| 9. |
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 |
| Answer» B. Increase the mach number of incoming air | |