This set of Rocket Propulsion Multiple Choice Questions & Answers (MCQs) focuses on “Sample Thrust Chamber Design Analysis”.
1. Determine the propellant mass flow rate for a TSFC of 3200 kg/Ns and a total thrust of 50 kN.
a) 21.65 kg/s
b) 12.56 kg/s
c) 16.52 kg/s
d) 15.62 kg/s
View Answer
Explanation: Propellant flow rate ṁ = F/c, where F is the total thrust and c is the specific fuel consumption.
Then ṁ = 50,000/3200 = 15.62 kg/s.
2. Find the fuel flow rate for a total propellant flow of 10 kg/s and a mixture ratio of 2.3.
a) 4.71 kg/s
b) 7.41 kg/s
c) 1.47 kg/s
d) 4.17 kg/s
View Answer
Explanation: Fuel flow rate ṁf = ṁ/(r+1), where ṁ is the total propellant mass flow rate and r is the mixture ratio.
So ṁf = 10/2.4 = 4.17 kg/s.
3. Calculate the flow rate of LOX to the combustion chamber in a LOX-H2 rocket engine if the total propellant flow rate is 17 kg/s and mixture ratio is 3.2.
a) 11.33 kg/s
b) 15.92 kg/s
c) 12.95 kg/s
d) 13.67 kg/s
View Answer
Explanation: ṁo = ṁr/(r+1)
So ṁo = 17*3.2/4.2 = 12.95 kg/s.
4. Determine the nozzle throat area for a rocket engine producing a total thrust of 10 kN, chamber pressure of 5.2 MPa and thrust coefficient of 1.9.
a) 10.12 cm2
b) 12.10 cm2
c) 11.20 cm2
d) 21.10 cm2
View Answer
Explanation: Nozzle throat area At = F/P1CF, where P1 is the chamber pressure, CF is the thrust coefficient and F is the total thrust provided by the rocket engine.
Then At = 10000/(5.2 x 106 x 1.9)
= 10.12 cm2.
5. If the semi-divergence angle of a conical nozzle is 15°, throat diameter is 8.326 cm and exit area is 0.54 m2, determine the nozzle length.
a) 139.2 cm
b) 239.1 cm
c) 312.9 cm
d) 231.9 cm
View Answer
Explanation: Nozzle length L = (D2 – D1) / 2tanλ, where D2 is the nozzle exit cross-section diameter, D1 is the nozzle inlet diameter and λ is the semi-divergence angle of the conical nozzle.
Exit diameter D2 = √(4*Ae/π), where Ae is the exit area.
Then D2 = 82.92 cm
So, L = (82.92 – 8.326)/0.536 = 139.2 cm.
6. The pressure drop across injector is usually set between _________ of the chamber pressure.
a) 45 and 65%
b) 30 and 45%
c) 15 and 25%
d) 5 and 15%
View Answer
Explanation: The pressure drop across the injector is set between 15 and 25% of the chamber pressure. This is done partly for obtaining high velocities of propellant injection. High velocities will help in easy atomization and droplet breakup which in turn helps in complete combustion.
7. Which of the following is a realistic value of the discharge coefficient?
a) 0.5
b) 1.5
c) 5.5
d) 10.5
View Answer
Explanation: Velocity is maximum for a given pressure drop if the injector discharge coefficient is 1. For rounded and clean injection holes, discharge coefficients can be about 0.80.
8. In which of the following ignition techniques does the system use a solid propellant squib or grain of few seconds of burning duration?
a) Spark plug ignition
b) Pyrotechnic ignition
c) Ignition by electrically heated wires
d) Precombustion chamber ignition
View Answer
Explanation: In pyrotechnic ignition, a squib or grain of solid propellant of few seconds of burning duration is used for the sake of ignition. This is one of the common ways of ignition in a solid propellant rocket engine.
9. Which of the following is the correct expression for energy radiated by a body (Assume ε to be emissivity, A to be surface area, T to be temperature, f to be geometric factor)
a) E = (1/f)εσAT4
b) E = fεσAT4
c) E = (1/f)εσAT2
d) E = fεσAT2
View Answer
Explanation: E = fεσAT4 is the correct expression for energy radiated by a body. Here σ is the Stefan-Boltzmann constant and it has a value of 5.67 x 10-8 W/m2K4.
10. Which of the following gases show a strong emission band in the region of radiant heat transfer?
a) Ammonia
b) Hydrogen
c) Oxygen
d) Nitrogen
View Answer
Explanation: Gases with symmetrical molecules like hydrogen, oxygen and nitrogen typically doesn’t show a strong band in the region of radiant heat transfer. Heteropolar gases, on the other hand, shows strong activity in that band.
Sanfoundry Global Education & Learning Series – Rocket Propulsion.
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