MCQOPTIONS
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MCQOPTIONS
This section includes 9 Mcqs, each offering curated multiple-choice questions to sharpen your Rocket Propulsion knowledge and support exam preparation. Choose a topic below to get started.
| 1. |
Determine the jet exhaust velocity, if the flow has an exit Mach number of 3 and temperature of 700 K. (Assume γ= 1.4 and Cp = 1005 J/kgK) |
| A. | 1591 m/s |
| B. | 2041 m/s |
| C. | 991 m/s |
| D. | 781 m/s |
| Answer» B. 2041 m/s | |
| 2. |
Determine the rocket thrust coefficient for a total thrust of 20 kN, chamber pressure of 500 kPa and a throat diameter of 10 cm. |
| A. | 2.39 |
| B. | 6.51 |
| C. | 4.97 |
| D. | 5.09 |
| Answer» E. | |
| 3. |
If a nozzle has an optimum expansion ratio of 9, determine the nozzle cone exit diameter for a throat diameter of 15 mm. |
| A. | 30 mm |
| B. | 135 mm |
| C. | 45 mm |
| D. | 90 mm |
| Answer» D. 90 mm | |
| 4. |
For a slightly over-expanded supersonic exhaust from a nozzle with exit area of 0.110 m2, flow pressure of 180 kPa and an atmospheric pressure of 100 kPa, determine the approximate distance between the nozzle and the first shock diamond. |
| A. | 30.2 cm |
| B. | 25.9 cm |
| C. | 28.5 cm |
| D. | 33.6 cm |
| Answer» E. | |
| 5. |
A gas tank discharges faster if it is thermally isolated than if it is kept isothermal. |
| A. | True |
| B. | False |
| Answer» C. | |
| 6. |
Find the critical pressure ratio for a nozzle flow from a chamber of pressure 300 kPa to the atmospheric pressure of 100 kPa. Assume γ = 1.4. |
| A. | 0.637 |
| B. | 0.528 |
| C. | 0.981 |
| D. | 0.243 |
| Answer» C. 0.981 | |
| 7. |
If isentropic efficiency for expansion in a nozzle having a mass flow rate of 90 kg/s is 0.95, find the exit area. Given the low speed entrance pressure is 250 kPa, temperature is 375 °C and outside atmospheric pressure is 101 kPa. Assume Cp = 1005 J/(kgK) and γ = 1.33. |
| A. | 0.133 m2 |
| B. | 0.210 m2 |
| C. | 0.295 m2 |
| D. | 0.225 m2 |
| Answer» E. | |
| 8. |
What is another name for the nozzle area ratio? |
| A. | Nozzle expansion ratio |
| B. | Nozzle contraction ratio |
| C. | Nozzle convergence ratio |
| D. | Nozzle divergence ratio |
| Answer» B. Nozzle contraction ratio | |
| 9. |
How are delivered performance values estimated for a propulsion system? |
| A. | Static tests or flight tests of full-scale models |
| B. | Dimensional analysis and similitude of models |
| C. | A theoretical analysis using the known relations |
| D. | Using computational simulation |
| Answer» B. Dimensional analysis and similitude of models | |