THEORY OF FLIGHT 250 TO 315 QUE FOR EASA AND DGCA EXAM
251. Which condition is the actual amount of water vapour in a mixture of air and water?
a) Relative humidity b) Dew point # c) Absolute humidity
252. When the weight of an aircraft increases, the minimum drag speed
a) decreases # b) increases c) remains the same
253. Which statement concerning heat and/or temperature is true?
a) There is an inverse relationship between temperature and heat.
# b) Temperature is a measure of the kinetic energy of the molecules of any substance
c) Temperature is a measure of the potential energy of the molecules of any substance
254. Which is the ratio of the water vapour actually present in the atmosphere to the amount that would be present if the air were saturated at the prevailing temperature and pressure?
a) Absolute humidity # b) Relative humidity c) Dew point
255. When an aircraft experiences induced drag
# a) air flows under the wing spanwise towards the tip and on top of the wing spanwise towards the root
b) air flows under the wing spanwise towards the root and on top of the wing spanwise towards the tip
c) Neither a) or b) since induced drag does not cause spanwise flow
256. What is absolute humidity?
a) The temperature to which humid air must be cooled at constant pressure to become saturated.
# b) The actual amount of the water vapour in a mixture of air and water
c) The ratio of the water vapour actually present in the atmosphere to the amount that would be present if the air were saturated at the prevailing temperature and pressure
257. Which atmospheric conditions will cause the true landing speed of an aircraft to be the greatest?
a) Low temperature with low humidity b) High temperature with low humidity # c) High temperature with high humidity
258. If all, or a significant part of a stall strip is missing on an aeroplane wing, a likely result will be
a) increased lift in the area of installation on the opposite wing at high angles of attack
b) asymmetrical aileron control at low angles of attack
# c) asymmetrical aileron control at or near stall angles of attack
259. When a leading edge slat opens, there is a gap between the slat and the wing. This is
a) to allow it to retract back into the wing
# b) to allow air through to re-energize the boundary layer on top of the wing
c) to keep the area of the wing the same
260. An aeroplane wing is designed to produce lift resulting from relatively
a) positive air pressure below and above the wing's surface.
b) negative air pressure below the wing's surface and positive air pressure above the wing's surface.
# c) positive air pressure below the wing's surface and negative air pressure above the wing's surface
261. Aspect ratio of a wing is defined as the ratio of the
a) wingspan to the wing root b) square of the chord to the wingspan # c) wingspan to the mean chord
262. Which of the following is true?
a) Lift acts at right angles to the wing chord line and weight acts vertically down
# b) Lift acts at right angles to the relative airflow and weight acts vertically down
c) Lift acts at right angles to the relative air flow and weight acts at right angles to the aircraft centre line
263. The temperature to which humid air must be cooled at constant pressure to become saturated is called
# a) dewpoint b) absolute humidity c) relative humidity
264. The airflow over the upper surface of a cambered wing
a) increases in velocity and pressure # b) increases in velocity and reduces in pressure
c) reduces in velocity and increases in pressure
265. Which type of flap increases the area of the wing?
a) Plain Flap # b) Fowler Flap c) All flaps
266. If all, or a significant part of a stall strip is missing on an aeroplane wing, a likely result will be
a) increased lift in the area of installation on the opposite wing at high angles of attack
b) asymmetrical aileron control at low angles of attack # c) asymmetrical aileron control at or near stall angles of attack
267. With increased speed in level flight
a) induced drag increases # b) profile drag increases c) profile drag remains constant
268. Deployment of flaps will result in
# a) a decrease in stall angle b) an increase in stall angle c) a decrease in angle of attack
269. An aeroplane wing is designed to produce lift resulting from relatively
a) positive air pressure below and above the wing's surface.
b) negative air pressure below the wing's surface and positive air pressure above the wing's surface.
# c) positive air pressure below the wing's surface and negative air pressure above the wing's surface.
270. The angle of attack of an aerofoil section is the angle between the
# a) chord line and the relative airflow
b) underside of the wing surface and the mean airflow
c) chord line and the centre line of the fuselage
271. A swept wing tends to stall first at the
a) root # b) tip c) centre section
272. Kreuger Flaps are normally fitted to
a) the trailing edge of the wings b) the tips of the wings # c) the leading edge of the wings
273. Aspect ratio of a wing is defined as the ratio of the
a) wingspan to the wing root. b) square of the chord to the wingspan. # c) wingspan to the mean chord
274. The trailing vortex on a pointed wing (taper ratio = 0) is
a) at the root b) at the tip # c) equally all along the wing span
275. A high wing aircraft will be more
# a) laterally stable than a low wing aircraft b) longitudinally stable than a low wing aircraft
c) directionally stable than a low wing aircraft
276. A wing with a very high aspect ratio (in comparison with a low aspect ratio wing) will have
a) increased drag at high angles of attack. # b) a low stall speed. c) poor control qualities at low airspeeds.
277. The lift curve for a delta wing is
a) more steep than that of a high aspect ratio wing
# b) less steep than that of a high aspect ratio wing
c) the same as that of a high aspect ratio wing
278. after an aircraft has been disturbed from its straight and level flight, it returns to its original attitude with a small amount of decreasing oscillation. The aircraft is
a) statically stable but dynamically unstable
b) statically unstable but dynamically stable
# c) statically stable and dynamically stable
279. An increase in the speed at which an aerofoil passes through the air increases lift because
# a) the increased speed of the airflow creates a greater pressure differential between the upper and lower surfaces.
b) the increased speed of the airflow creates a lesser pressure differential between the upper and lower surfaces.
c) the increased velocity of the relative wind increases the angle of attack
280. A delta wing has
# a) a higher stall angle than a straight wing b) a lower stall angle than a straight wing c) the same stall angle than a straight wing
281. The Lift/Drag ratio of a wing at the stalling angle is
a) of a negative value # b) low c) high
282. The airflow over the upper surface of a cambered wing
a) increases in velocity and pressure # b) increases in velocity and reduces in pressure
c) reduces in velocity and increases in pressure
283. The speed of air over a swept wing which contributes to the lift is
a) less than the aircraft speed # b) more than the aircraft speed c) the same as the aircraft speed
284. For a given angle of attack induced drag is
a) greater on a high aspect ratio wing b) greater towards the wing root # c) greater on a low aspect ratio wing
285. In straight and level flight, the angle of attack of a swept wing is
a) the same as the aircraft angle to the horizontal # b) more than the aircraft angle to the horizontal
c) less than the aircraft angle to the horizontal
286. Induced drag
a) is never equal to the profile drag b) is equal to the profile drag at the stalling speed # c) is equal to the profile drag at Vmd
287. A delta wing aircraft flying at the same speed (subsonic) and angle of attack as a swept wing aircraft of similar wing area will produce
a) the same lift b) more lift # c) less lift
288. The stagnation point is
# a) static pressure plus dynamic pressure b) static pressure minus dynamic pressure c) dynamic pressure only
289. On a swept wing aircraft, due to the adverse pressure gradient, the boundary layer on the upper surface of the wing tends to flow
a) directly from leading edge to trailing edge # b) towards the tip c) towards the root
290. With increased speed in level flight
a) induced drag increases # b) profile drag increases c) profile drag remains constant
291. If a swept wing stalls at the tips first, the aircraft will
# a) pitch nose up b) pitch nose down c) roll
292. The thickness/chord ratio of the wing is also known as
a) aspect ratio b) mean chord ratio # c) fineness ratio
293. Flexure of a rearward swept wing will
a) increase the lift and hence increase the flexure # b) decrease the lift and hence decrease the flexure
c) increase the lift and hence decrease the flexure
294. A High Aspect Ratio wing is a wing with
a) long span, long chord # b) long span, short chord c) short span, long chord
295. Stall commencing at the root is preferred because
a) the ailerons become ineffective # b) it provides the pilot with a warning of complete loss of lift
c) it will cause the aircraft to pitch nose up
296. An aircraft flying in “ground effect” will produce
# a) more lift than a similar aircraft outside of ground effect
b) less lift than a similar aircraft outside of ground effect
c) the same lift as a similar aircraft outside of ground effect
297. If the angle of attack of a wing is increased in flight, the
# a) C of P will move forward b) C of G will move aft c) C of P will move aft
298. The Rams Horn Vortex on a forward swept wing will be
a) the same as a rearward swept wing b) more than a rearward swept wing # c less than a rearward swept wing
299. When maintaining level flight an increase in speed will
a) cause the C of P to move aft b) cause the C of P to move forward # c) have no affect on the position of the C of P
300. For a cambered wing section the zero lift angle of attack will be
a) zero b) 4 degrees # c) negative
301. Density changes with altitude at a rate
a) of 2kg/m3 per 1000ft # b) which changes with altitude c) which is constant until 11km
302. Airflow at subsonic speed is taken to be
a) compressible # b) incompressible c) either a or b depending on altitude
303. Bernoulli's equation shows that
# a) at constant velocity the kinetic energy of the air changes with a change of height
b) with a change in speed at constant height both kinetic and potential energies change
c) with a change in velocity at constant height the static pressure will change
304. If fluid flow through a venturi is said to be incompressible, the speed of the flow increases at the throat to
# a) maintain a constant volume flow rate b) allow for a reduction in static pressure c) allow for an increase in static pressure
305. to produce lift, an aerofoil must be
a) asymmetrical b) symmetrical # c) either a or b above
306. Lift is dependent on
# a) the area of the wing, the density of the fluid medium, and the square of the velocity
b) the net area of the wing ,the density of the fluid medium and the velocity
c) the frontal area of the wing, the density of the fluid medium and the velocity
307. The maximum lift/drag ratio of a wing occurs
a) at the angle of attack where the wing develops its maximum lift
b) during take off # c) at an angle below which the wing develops max lift
308. A wing develops 10,000N of lift at 100knots. Assuming the wing remains at the same angle of attack and remains at the same altitude, how much lift will it develop at 300knots?
a) 900,000 N # b) 90,000N c) 30,000N
9. The angle of attack is
a) related to angle of incidence b) always kept below 15 degrees # c) not related to the angle of incidence
310. The difference between the mean camber line and the chord line of an aero foil is
# a) one is always straight and the other may be straight b) neither are straight c) they both may be curved
311. If the C of G is calculated after loading as within limits for take off
a) no further calculation is required
# b) a further calculation is required prior to landing to allow for fuel and oil consumption
c) a further calculation is required prior to landing to allow for flap deployment
312. A stalled aero foil has a lift/drag ratio
a) more than the lift/drag ratio prior to stall b) Zero # c) Less than the lift/drag ratio prior to stall
313. At low forward speed
a) Increased downwash reduces tail plane effectiveness
# b) increased downwash increases tail plane effectiveness
c) Excessive rudder movement may cause fin to stall
314. Helicopter rotor blades create lift by
# a) creating low pressure above the blades
b) Pushing the air down c) Working like a screw
315. On some modern aircraft a stall warning will automatically
a) Increase thrust b) Extend outboard slats
# c) cause a pitch nose down movement
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