MCQOPTIONS
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MCQOPTIONS
This section includes 10 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. |
What will happen if the maximum theoretical nozzle exhaust velocity tends to a very large value? |
| A. | Working fluid ceases to be a gas |
| B. | The temperature of the working fluid increases exponentially |
| C. | The thermal energy content of the fluid becomes infinite |
| D. | The flow undergoes rapid compression |
| Answer» B. The temperature of the working fluid increases exponentially | |
| 2. |
What is the pressure ratio for the maximum theoretical value of nozzle outlet velocity? |
| A. | Infinite |
| B. | Zero |
| C. | Finite value < 1 |
| D. | Finite value > 1 |
| Answer» B. Zero | |
| 3. |
What is the expression for the maximum theoretical value of the nozzle outlet velocity (ve) with an infinite expansion, if represents the ratio of specific heats, To represents the chamber temperature, R is the gas constant? |
| A. | v<sub>e</sub> = ( sqrt{(2 gamma RT_o( gamma-1))} ) |
| B. | v<sub>e</sub> = ( sqrt{(2 gamma RT_o/( gamma-1))} ) |
| C. | v<sub>e</sub> = ( sqrt{(2( gamma+1)RT_o/( gamma-1))} ) |
| D. | v<sub>e</sub> = ( sqrt{(2( gamma-1)RT_o( gamma+1))} ) |
| Answer» C. v<sub>e</sub> = ( sqrt{(2( gamma+1)RT_o/( gamma-1))} ) | |
| 4. |
What are the standardized chamber pressure and exit pressure values used for comparing the specific impulse values or various design parameters of different rocket engines? |
| A. | 1000 psia, 1 atm |
| B. | 1000 atm, 1 psia |
| C. | 100 psia, 1 atm |
| D. | 100 atm, 1 psia |
| Answer» B. 1000 atm, 1 psia | |
| 5. |
Which of the following will improve the performance of a rocket engine? |
| A. | Decrease in gas temperature |
| B. | Increase in the molecular mass of the propellant |
| C. | Decrease in the pressure ratio |
| D. | Increase in the chamber pressure |
| Answer» E. | |
| 6. |
What is the correct definition of the nozzle area expansion ratio? |
| A. | The ratio of nozzle exit area to the throat area |
| B. | The ratio of the nozzle area at the inflection point to the throat area |
| C. | The ratio of throat area to the nozzle inlet area |
| D. | The ratio of throat area to the area at the point of inflection |
| Answer» B. The ratio of the nozzle area at the inflection point to the throat area | |
| 7. |
The area of a de Laval Nozzle is directly proportional to the ratio v/V, where v is the flow velocity and V is the specific volume. |
| A. | True |
| B. | False |
| Answer» C. | |
| 8. |
If the rocket exhaust gases are calorically perfect and have a mean molecular mass of 28 kg/kmol, and a constant specific heat ratio ( ) of 1.33, determine the nozzle exit velocity. Assume the nozzle inlet conditions to be the following: P1 = 5 MPa, V1 = 240 m/s, T1 = 750 K and exit pressure (Pe) to be 1 MPa. |
| A. | 204 m/s |
| B. | 699.21 m/s |
| C. | 712.32 m/s |
| D. | 805.56 m/s |
| Answer» E. | |
| 9. |
If at a point along the isentropic rocket nozzle, the temperature of the gas is 718 K, and the flow velocity is 150 m/s, determine the nozzle exit velocity, given the exhaust gas temperature is 460 K (Assume Cp = 1005 J/kg K) |
| A. | 840.25 m/s |
| B. | 735.58 m/s |
| C. | 913.07 m/s |
| D. | 374.95 m/s |
| Answer» C. 913.07 m/s | |
| 10. |
Which of the following will happen if there is a flow obstruction in the nozzle inner wall? |
| A. | Local conversion of kinetic to thermal energy |
| B. | Local drop in pressure around the region of obstruction |
| C. | Formation of normal shock waves at the point of obstruction |
| D. | Rapid decrease in mass flow rate |
| Answer» B. Local drop in pressure around the region of obstruction | |