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