Quiz
semana Carol segundo parcial
Questions in this quiz (32)
1Q1. Which was the first jet-powered aircraft?
- AA. Spitfire
- BB. Junkers Ju 87
- CC. Bell P-59
- DD. Heinkel He-178
2Q2. Why was the aircraft Gloster Meteor so popular?
- AA. It was the first jet-powered aircraft.
- BB. It was the first aircraft to break the sound barrier.
- CC. It was the first aircraft with sufficient speed to attack the German V1 flying bomb.
- DD. It was the first aircraft that could perform sustained inverted flight.
3Q3. The engine Jumbo 004B was a milestone in the turbojet engine because…
- AA. It had the first axial compressor in a turbojet engine.
- BB. It had the biggest change of pressure in one stage up until then.
- CC. It was the most produced engine in the WWII.
- DD. All the answers are false.
4Q4. Mark the right answer:
- AA. A turboprop produces more impulse than a turbojet.
- BB. A low-BPR turbofan has a bigger SFC than a high-BPR turbofan in low speeds.
- CC. A turboprop has a bigger SFC than a turbojet in low speeds.
- DD. A turboprop has the least SFC at any speed.
5Q5. Which statement is true?
D. None of the above- AA. Axial compressor is a compressor in which the gas or working fluid principally flows parallel to the axis of rotation
- BB. Centrifugal compressor is a compressor in which the gas or working fluid principally flows with a radial component through the compressor.
- CC. A and B are correct
- DD. None of the above
6Q6. In jet engines with greater impulse (I):
- AA. Large size.
- BB. Smaller size.
- CC. The division between thrust (E) and airflow (G) is lower
- DD. None of the above
7Q7. The specific fuel consumption (SFC) is:
- A(E (thrust) )/(G (airflow) )
- B(c (consumption) )/(E (thrust) )
- C(G (airflow) )/(E (thrust) )
- D(G (airflow) )/(c (consumption) )
8Q8. In turbofan the bypass ratio is:
- A(Secondary flow )/(Primary flow ) ; and primary flows through the combustion chamber.
- B(Secondary flow )/(Primary flow ) ; and secondary flows through the combustion chamber.
- C(Primary flow )/(Secondary flow ) ; and primary flows through the combustion chamber.
- D(Primary flow )/(Secondary flow ) ; and secondary flows through the combustion chamber.
9Q1. When it is produced stagnation pressure losses in the inlets:
- AA. Increase thrust
- BB. Increase Specific Fuel Consumption
- CC. Decrease thrust
- DD. A and B are correct
10Q2. Mark the wrong answer:
- AA. Generally, subsonic inlets are named “Pitot”
- BB. Typical parameters are NACA Serie 1 profiles
- CC. Drag is not due to inlet outer surface
- DD. The shape is aerodynamically smooth
11Q3. Supersonic inlets can be:
- AA. 2D or spike
- BB. 3D or wedge
- CC. 2D or wedge
- DD. A and B are correct
12Q4. Which are the functions of compressors?
- AA. Increase the pressure of the air mass received
- BB. Take the air to the combustion section
- CC. Provide bleed air for cabin pressure and other systems
- DD. All are correct
13Q5. Which are the types of compressors? Choose the wrong answer:
- AA. Bi-directional
- BB. Axial
- CC. Centrifugal
- DD. B and C are right
14Q6. Which are the elements of centrifugal compressors? Choose the incorrect answer:
- AA. Diffuser
- BB. Stabilizer
- CC. Front case
- DD. Impeller
15Q7. In centrifugal compressors, leaving the impeller the air passes into the diffuser section where the passages form
- AA. Divergent nozzles
- BB. Convergent nozzles
- CC. Divergent and convergent nozzles
- DD. None of them
16Q8. Mark the incorrect option:
- AA. Single-spool is a type of axial compressors
- BB. Multi-spool is a type of centrifugal compressors
- CC. Generally, in aviation are used single-spool and two spools
- DD. Multi-spool is a type of axial compressors
17Q1. If the angle of attack of the rotor blades is too large…
- AA. Boundary layer can stall
- BB. Will cause transonic zones
- CC. Can cause heating problem
- DD. Nothing can go wrong
18Q2. To ensure the working conditions for the compressor with different velocities via variable incident vanes… (Choose the wrong answer)
- AA. Variable IGV
- BB. Variable stator blades
- CC. They close when velocity reduces
- DD. None of the above
19Q3. A compression map…
- AA. Provides information of pressure ratio an equivalent flow for a throttle setting (IDLE-100%)
- BB. Does not give info relative to throttle settings
- CC. Gives info relative to weather conditions
- DBoth A and C are correct
20Q4. Combustion Chambers… (choose the wrong answer)
- AA. Ensure stable fuel burn with max. Thermal efficiency in large conditions ranges
- BB. Are not used for aviation engines
- CC. Max temperature (850-1700ºC) due to turbine materials
- DD. Combustion is initiated by an electric spark from an igniter plug
21Q5. Which is not a cooling method?
- AA. Corrugated strip cooling
- BB. Machined cooling ring
- CC. Splash cooling strip
- DD. Capsule icing allocation
22Q6. Types of combustion chambers…
- AA. Tubular
- BC. Annular
- CB. Tubo-annular
- DAll the above
23Q7. Fuel Nozzle types…
- AA. Vaporiser
- BB. Atomiser
- CC. Both A and B are correct
- DD. Both A and B are false
24Q8. Both impulse and reaction are energy transfer systems
- ATrue
- BFalse
25Q1. What are the different configuration of turbine?
A. Compressor
B. IMPULSE TURBINE
C. REACTIONTURBINE
D. B and C- AA. compressor
- BB. Impulse Turbine
- CC. Reaction Turbine
- DB and C
26Q2. What kind of engines are used nowadays in modern fighters?
- AA. Turbofan of low derivation
- BB. Turbofan of high derivation
- CC. Piston engines
- DD. Stratojet
27Q3. Why the afterburner is an inefficient method to increase the thrust
- AA. Because it implies more drag inside engine
- BB. Indeed, it is a really efficient method, especially in military aviation
- CBecause of increment in thrust, that is proportional to (√T_PC)/(√T_NoPC )
- DD. Because the increment in thrust follows a linear gradient, so that is not too much.
28Q4. Choose the correct answer
- AA. Afterburning provides the best method of thrust augmentation for short periods.
- BB. Afterburning provides the worst method of thrust augmentation for short periods.
- CC. Afterburning provides the best method of thrust augmentation for long periods.
- DD. Afterburning provides the worst method of thrust augmentation for long periods.
29Q5. Afterburning
- AA. It is a method of augmenting the basic thrust of an engine.
- BB. For military aircraft improve combat performance
- CC. It is the worst method of thrust augmentation for short periods.
- DD. A and B are correct
30Q6. how the use of afterburning affects the nozzle?
- AA. The nozzle expands
- BB. the nozzle contracts
- CC. the nozzle stays fixed
- DD. the nozzle opens and closes periodically
31Q7. What kind of Turbofans exist nowadays?
- AA. low derivation
- BB. high derivation
- CC. turboreactors
- DD. a and b are correct
32Q8. Turbofans of high derivation ratio are used in
- AA. Commercial planes
- BB. Fighters planes
- CC. None of the above
- DD. Helicopters
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- AVIÓNICA Quiz on semana Carol segundo parcial, created by Ismael Vázquez on 16/04/2018.
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- Ismael Vázquez
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- Español
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