College : Vardhaman College Of Engineering
Degree : B.Tech
Department : Aeronautical Engineering
Semester : VI
Subject :Aerospace Propulsion-II
Document type : Question Paper
Website : vardhaman.org
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Vardhaman Aerospace Propulsion-II Question Paper
Four Year B. Tech VI Semester Regular Examinations May – 2014
(Aeronautical Engineering)
Date: 31 May, 2014
Time: 3 hours
Max Marks: 75
Answer ONE question from each Unit
Related : Vardhaman College Of Engineering Network Security & Cryptography B.Tech Question Paper : www.pdfquestion.in/6400.html
All parts of the question must be answered in one place only :
Unit – I
1. a) With a neat sketch explain single stage velocity triangle and derive expression for work output. 8M
b) Discuss the limitations in the design of gas turbine. 7M
2. a) Explain vortex theory. 7M
b) Explain film cooling and transpiration cooling as applied to blade cooling in gas turbine. 8M
Unit – II
3. a) Discuss the principle of scram jet engine and list out any four advantages of scram jet engine. 7M
b) With neat sketch explain the working principle of turbo fan engine. 8M
4. a) An ideal ramjet is flying at Mach 2 where the ambient temperature is 293 K. The fuel has a heating value of 45,000 KJ/Kg and the temperature inside the combustion chamber is 2500 K. Find the jet exit velocity and fuel ratio. If the air mass flow through the engine is 200 Kg/s, what is the thrust produced and the thrust specific fuel consumption? For air, ? = 1.4 and Cp= 1.0035 KJ/Kg K, which are assumed to remain constant. 8M
b) Explain thrust augmentation technique. 7M
Unit – III
5. Starting with the basic derivation solve the following :
The effective jet exit velocity from a jet engine is 2700 m/s .The forward flight velocity is 1350 m/s and the airflow rate is 78.6 kg/s.
Calculate:
i. Thrust
ii. Thrust power and
iii. Propulsive efficiency 15M
6. A rocket flies at 10,080 kmph with an effective exhaust jet velocity of 1400 m/s and propellant flow rate is 5.0 kg/s. If the heat of reaction of the propellant is 6500 KJ/kg of the propellant mixture determine:
i. Propulsion efficiency and propulsion power
ii. Engine output and thermal efficiency
iii. Overall efficiency 15M
Unit – IV
7. a) With neat sketch explain plasma rocket propulsion. 8M
b) Write short notes on internal ballistics. 7M
8. a) List out the various types of electrical rocket propulsion system? Explain any one. 8M
b) List out the methods used for cooling of rocket engines thrust chamber? Explain any one. 7M
Unit – V
9. a) With neat sketch explain the working of ion rocket propulsion. 8M
b) Write short notes on staging of rockets. 7M
10. a) With neat sketch explain the working of solar rocket engine. 8M
b) What are the factors important in comparision of different types of rockets? 7M
Flight Vechicle Design :
(Aeronautical Engineering)
Date: 3 June, 2014
Time: 3 hours
Max Marks: 75
Answer ONE question from each Unit
All Questions Carry Equal Marks
All parts of the question must be answered in one place only
Unit – I :
1. a) Briefly discuss the phases of aircraft design. 8M
b) What are the performance data of the existing aircraft that can be used as guidelines for the conceptual design of aircraft? Explain considering four design parameters? Also explain how you would use the data. 7M
2. a) Explain the take –off weight build up and the empty weight estimation for a new aircraft design 8M
b) Discuss the performance requirement of air craft. 7M
Unit – II :
3. What are the implications of wing loading (W/S) value on aircraft design, mainly stall speed, climb, range, endurance, ceiling altitude, take off and landing distance. 15M
4. a) What are the volume consideration while sizing fuselage. 10M
b) Discuss flat wrap lofting. 5M
Unit – III :
5. a) Describe installed engine thrust correction. 5M
b) Discuss the effect of altitude and velocity variation on engine performance. 10M
6. What are the types of loads acts on an aircraft and derive expression for total load factor for sharp edge gust. 15M
Unit – IV :
7. a) Explain the stability and control derivative of aircraft. 7M
b) Discuss the advantages and disadvantages of canard wing of airplane. 8M
8. Discuss the following:
i. RDT&E and production cost
ii. Operation and maintenance costs
iii. Crew salaries
iv. Matrix plot
v. Carpet plot 15M
Unit – V :
9. a) With neat sketch explain the development of DC-1 aircraft. 8M
b) With neat sketch explain double delta wing of aircraft. 7M
10. a) Draw the three views of the layout of a 60 seater high subsonic aircraft. 9M
b) Make a conceptual sketch of stealth bomber. 6M