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. |
Determine the Prandtl number for a liquid having thermal conductivity of 4.6 W/mK, Cp of 8 kJ/kgK. Assume the viscosity to be 1.25 Cp. |
| A. | 1.59 |
| B. | 7.21 |
| C. | 5.91 |
| D. | 2.17 |
| Answer» E. | |
| 2. |
The quantity μCp/k, where μ is the absolute gas viscosity, Cp is the specific heat of gas at constant pressure and k is the thermal conductivity is called as _________ |
| A. | Nusselt number |
| B. | Bartz number |
| C. | Prandtl number |
| D. | Froude number |
| Answer» D. Froude number | |
| 3. |
The quantity hgD/k, where hg is the gas film coefficient, D is the diameter of the chamber and k denotes the gas conductivity is __________ |
| A. | Bartz number |
| B. | Froude number |
| C. | Nusselt number |
| D. | Prandtl number |
| Answer» D. Prandtl number | |
| 4. |
Which of the following might simplify the determination of film coefficient? |
| A. | Combustion oscillations |
| B. | Boundary layer behavior |
| C. | Uniform velocity profile |
| D. | Complex geometry |
| Answer» D. Complex geometry | |
| 5. |
_____ largely determines the numerical heat transfer rate and __________ largely determines the value of wall temperatures. |
| A. | Gas film coefficient; liquid film coefficient |
| B. | Gas film coefficient; thermal conductivity |
| C. | Thermal conductivity; liquid film coefficient |
| D. | Liquid film coefficient; gas film coefficient |
| Answer» B. Gas film coefficient; thermal conductivity | |
| 6. |
For absolute chamber gas temperature Tg, absolute liquid temperature Tl, absolute wall temperature on the gas side of the wall Twg, overall film coefficient h, gas film coefficient hg and liquid film coefficient hl, determine the expression for heat transferred per unit area q. |
| A. | q = hl (To – Twg) |
| B. | q = h (To – Twg) |
| C. | q = hg (To – Twg) |
| D. | q = hg/h (Twg – To) |
| Answer» D. q = hg/h (Twg – To) | |
| 7. |
For absolute chamber gas temperature Tg, absolute liquid temperature Tl, overall film coefficient h, gas film coefficient hg and liquid film coefficient hl, determine the expression for heat transferred per unit area q. |
| A. | q = h/(hg hl) x (Tg – Tl) |
| B. | q = hg (Tg – Tl) |
| C. | q = hghl/h x (Tg – Tl) |
| D. | q = h (Tg – Tl) |
| Answer» E. | |
| 8. |
The whole process of heat transfer through the chamber wall is a combination of ________ through the chamber wall and ________ through the flowing fluids. |
| A. | conduction; convection |
| B. | convection; radiation |
| C. | radiation; conduction |
| D. | conduction; conduction |
| Answer» B. convection; radiation | |
| 9. |
Steady state heat transfer through a liquid-cooled rocket chamber wall can be considered as ___________ |
| A. | series type with strong temperature gradient |
| B. | parallel type with weak temperature gradient |
| C. | series type with weak temperature gradient |
| D. | parallel type with strong temperature gradient |
| Answer» B. parallel type with weak temperature gradient | |
| 10. |
If dT/dL denotes temperature gradient with respect to thickness L at the surface A, k denotes the thermal conductivity, then the heat transferred per unit area is given by __________ |
| A. | Q/A = -k dT/dL |
| B. | Q/A = -(1/k) dT/dL |
| C. | Q/A = k dT/dL |
| D. | Q/A = (1/k) kdT/dL |
| Answer» B. Q/A = -(1/k) dT/dL | |