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INDIGO AERODYNAMIC

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INDIGO AERODYNAMIC
INDIGO AERODYNAMIC
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#1. On a symmetrical aerofoil, the pitch moment for which Cl=0 is:

#2. Drag is in the direction of - and lift is perpendicular to the:

#3. The correct drag formula is:

#4. Lift and drag on an aerofoil are vertical respectively parallel to the

#5. The angle of attack (aerodynamic angle of incidence) of an aerofoil is the angle between the:

#6. The angle of attack of a two dimensional wing section is the angle between :

#7. The angle between the aeroplane longitudinal axis and the chord line is the:

#8. The term angle of attack in a two dimensional flow is defined as:

#9. Which statement is correct about the Cl and angle of attack?

#10. The relative thickness of an aerofoil is expressed in:

#11. ""A line connecting the leading- and trailing edge midway between the upper and lower surface of a aerofoil"". This definition is applicable for :

#12. The angle of attack of a wing profile is defined as the angle between :

#13. The Mean Aerodynamic Chord (MAC) for a given wing of any planform is

#14. The aspect ratio of the wing:

#15. Dihedral of the wing is:

#16. Consider an aerofoil with a certain camber and a positive angle of attack. At which location will the highest flow velocities occur ?

#17. With increasing angle of attack, the stagnation point will move (I) ...and the point of lowest pressure will move (II) ...Respectively (I) and (II) are:

#18. Which statement is correct?

#19. The point, where the aerodynamic lift acts on a wing is:

#20. The location of the centre of pressure of a positive cambered wing at increasing angle of attack will:

#21. Lift is generated when:

#22. The lift force, acting on an aerofoil :

#23. On an asymmetrical, single curve aerofoil, in subsonic airflow, at low angle of attack, when the angle of attack is increased, the centre of pressure will (assume a conventional transport aeroplane) :

#24. The Cl - alpha curve of a positive cambered aerofoil intersects with the vertical axis of the Cl - alpha graph:

#25. The lift formula is:

#26. The terms ""q"" and ""S"" in the lift formula are:

#27. The critical angle of attack:

#28. An aeroplane performs a straight and level horizontal flight at the same angle of attack at two different altitudes. (all other factors of importance being constant, assume ISA conditions and no compressibility effects)

#29. The aerodynamic drag of a body, placed in a certain airstream depends amongst others on:

#30. A body is placed in a certain airstream. The airstream velocity increases by a factor 4. The aerodynamic drag will increase with a factor :

#31. A body is placed in a certain airstream. The density of the airstream decreases to half of the original value. The aerodynamic drag will decrease with a factor :

#32. Comparing the lift coefficient and drag coefficient at normal angle of attack:

#33. The polar curve of an aerofoil is a graphic relation between :

#34. The lift- and drag forces, acting on a wing cross section:

#35. The aerofoil polar is:

#36. The frontal area of a body, placed in a certain airstream is increased by a factor 3. The shape will not alter. The aerodynamic drag will increase with a factor :

#37. Increasing dynamic (kinetic) pressure will have the following effect on the drag of an aeroplane (all other factors of importance remaining constant) :

#38. Increasing air pressure will have the following effect on the drag of an aeroplane (angle of attack, OAT and TAS are constant):

#39. Which statement is correct? The lift to drag ratio provides directly the

#40. The span-wise flow is caused by the difference between the air pressure on top and beneath the wing and its direction of movement goes from :

#41. Which statement about induced drag and tip vortices is correct?

#42. Which of the following wing planforms gives the highest local profile lift coefficient at the wingroot ?

#43. If flaps are deployed at constant IAS in straight and level flight, the magnitude of tip vortices will eventually : (flap span less than wing span)

#44. The value of the induced drag of an aeroplane in straight and level flight at constant weight varies linearly with:

#45. Induced drag at constant IAS is affected by:

#46. Which of the following will reduce induced drag?

#47. Induced drag is created by the:

#48. What is the effect of high aspect ratio of an aeroplane's wing on induced drag?

#49. Which of the following wing planforms produces the lowest induced drag? (all other relevant factors constant)

#50. Induced drag may be reduced by:

#51. The induced drag:

#52. The relationship between induced drag and the aspect ratio is:

#53. A high aspect ratio wing produces:

#54. Excluding constants, the coefficient of induced drag (CDi) is the ratio of :

#55. High Aspect Ratio, as compared with low Aspect Ratio, has the effect of :

#56. Winglets

#57. Which location on the aeroplane has the largest effect on the induced drag ?

#58. The induced angle of attack is the result of:

#59. The induced drag coefficient, CDi is proportional with:

#60. The interference drag is created as a result of

#61. The value of the parasite drag in straight and level flight at constant weight varies linearly with the:

#62. In what way do (1) induced drag and (2) parasite drag alter with increasing speed?

#63. An aeroplane accelerates from 80 kt to 160 kt at a load factor equal to 1. The induced drag coefficient (i) and the induced drag (ii) alter with the following factors:

#64. What is the effect on induced drag of weight and speed changes ?

#65. How does the total drag vary as speed is increased from stalling speed (VS) to maximum IAS (VNE) in a straight and level flight at constant weight?

#66. Which one of the following statements about the lift-to-drag ratio in straight and level flight is correct?

#67. At an aeroplane's minimum drag speed, what is the ratio between induced drag Di and profile drag Dp? Di/Dp=

#68. The aeroplane drag in straight and level flight is lowest when the:

#69. What will happen in ground effect ?What will happen in ground effect ?

#70. If an aeroplane flies in the ground effect

#71. Floating due to ground effect during an approach to land will occur :

#72. Ground effect has the following influence on the landing distance :

#73. An aeroplane maintains straight and level flight while the IAS is doubled. The change in lift coefficient will be:

#74. When an aeroplane is flying at an airspeed which is 1.3 times its basic stalling speed, the coefficient of lift as a percentage of the maximum lift coefficient (CLmax) would be:

#75. Which of the following statements about boundary layers is correct?

#76. Where on the surface of a typical aerofoil will flow separation normally start at high angles of attack?

#77. The boundary layer of a wing is caused by:

#78. A laminar boundary layer is a layer, in which:

#79. Compared with level flight prior to the stall, the lift (1) and drag (2) in the stall change as follows :

#80. Entering the stall the centre of pressure of a straight (1) wing and of a strongly swept back wing (2) will:

#81. Which of the following statements about the stall of a straight wing aeroplane is correct?

#82. Which statement is correct about the laminar and turbulent boundary layer :

#83. After the transition point between the laminar and turbulent boundary layer

#84. Which kind of boundary layer has the strongest change in velocity close to the surface?

#85. The stall speed in a 60° banked turn increases by the following factor:

#86. In a turn, the load factor n and the stalling speed VS will be:

#87. A jet aeroplane cruises buffet free at high constant altitude in significant turbulence. Which type of stall can occur if this aeroplane decelerates?

#88. Which of the following situations leads to a decreasing stall speed (IAS)?

#89. Two identical aeroplanes A and B are flying horizontal steady turns. Further data are:A:W= 1500 kgBank= 20°TAS= 130 ktB:W= 1500 kgBank= 20°TAS= 200 ktWhich of the following statements is correct?

#90. . Increase of wing loading will:

#91. The stall speed :

#92. When a pilot makes a turn in horizontal flight, the stall speed :

#93. An aeroplane has a stall speed of 78 KCAS at its gross weight of 6850 Ibs. What is the stall speed when the weight is 5000 Ibs ?

#94. An aeroplane has a stall speed of 100 kt at a load factor n=1. In a turn with a load factor of n=2, the stall speed is:

#95. The following factors increase stall speed :

#96. The wing of an aeroplane will never stall at low subsonic speeds as long as....

#97. The stall speed increases, when: (all other factors of importance being constant)

#98. By what approximate percentage will the stall speed increase in a horizontal coordinated turn with a bank angle of 45° ?

#99. An aeroplane has a stalling speed of 100 kt in a steady level flight. When the aeroplane is flying a level turn with a load factor of 1.5, the stalling speed is:

#100. The stalling speed in IAS will change according to the following factors:

#101. The stalling speed in IAS will change according to the following factors:

#102. The stalling speed in IAS will change according to the following factors:

#103. A boundary layer fence on a swept wing will:

#104. Which of the following are used as stall warning devices?

#105. The vane of a stall warning system with a flapper switch is activated by the change of the:

#106. The normal stall recovery procedure for a light single engined aeroplane is:

#107. Compared with stalling airspeed (VS) in a given configuration, the airspeed at which stick shaker will be triggered is:

#108. The sensor of a stall warning system can be activated by a change in the location of the

#109. On a swept wing aeroplane at low airspeed, the ""pitch up"" phenomenon:

#110. Low speed pitch up is caused by the:

#111. The most important problem of ice accretion on an aeroplane during flight is:

#112. The effects of very heavy rain (tropical rain) on the aerodynamic characteristics of an aeroplane are:

#113. Which of the following statements about stall speed is correct ?

#114. Which of the following statements about the spin is correct?

#115. During an erect spin recovery:

#116. Which combination of design features is known to be responsible for deep stall?

#117. A strongly swept back wing stalls. If the wake of the wing contacts the horizontal tail, the effect on the stall behaviour can be:

#118. The function of the stick pusher is:

#119. Stick pushers must be installed in aeroplanes with dangerous stall characteristics. Dangerous stall characteristics include:

#120. Which type of stall has the largest associated angle of attack?

#121. Which aeroplane design has the highest probability of a super stall?

#122. The pitch up effect of an aeroplane with swept wing in a stall is due to the

#123. One disadvantage of the swept back wing is it's stalling characteristics. At the stall :

#124. Trailing edge flap extension will:

#125. Which of the following series of configurations has an increasing critical angle of attack ?

#126. An aeroplane with swept back wings is equipped with slats and/or leading edge (L.E.) flaps. One possible efficient way to arrange the leading edge devices on the wings is:

#127. An aeroplane has the following flap settings : 0°, 15°, 30° and 45°. Slats can be selected too. Which of the above selections will produce the greatest negative influence on the CL/CD ratio?

#128. After take-off the slats (when installed) are always retracted later than the flaps. Why ?

#129. Which statement is correct?

#130. The trailing edge flaps when extended :

#131. When the trailing edge flaps are deflected in level flight, the change in pitch moment will be:

#132. Extension of FOWLER type trailing edge lift augmentation devices, will produce:

#133. On a wing fitted with a ""fowler"" type trailing edge flap, the ""Full extended"" position will produce:

#134. When flaps are extended in a straight and level flight at constant IAS, the lift coefficient will eventually :

#135. When flaps are deployed at constant angle of attack the lift coefficient will:

#136. What is the most effective flap system?

#137. Deploying a Fowler flap, the flap will:

#138. A slotted flap will increase the CLmax by:

#139. In order to maintain straight and level flight at a constant airspeed, whilst the flaps are being retracted, the angle of attack will:

#140. Flap selection at constant IAS in straight and level flight will increase the :

#141. -During flap down selection in a continuous straight and level flight at constant IAS and weight:

#142. A plain flap will increase CLmax by

#143. During the retraction of the flaps at a constant angle of attack the aeroplane starts to (all other factors of importance being constant)

#144. During the extension of the flaps at a constant angle of attack the aeroplane starts to (all other factors of importance being constant)

#145. Compared with the flap up configuration the maximum angle of attack for the flaps down configuration is

#146. Deflection of leading edge flaps will:

#147. Slat extension will:

#148. Which of the following statements about the difference between Krueger flaps and slats is correct?

#149. What is the purpose of an auto-slat system ?

#150. The function of the slot between an extended slat and the leading edge of the wing is to:

#151. A deployed slat will:

#152. What increases the stalling angle of attack ? Use of :

#153. The use of a slot in the leading edge of the wing enables the aeroplane to fly at a slower speed because :

#154. A slat will

#155. Vortex generators:

#156. Spoiler deflection causes :

#157. Upon extension of a spoiler on a wing:

#158. When ""spoilers"" are used as speed brakes:

#159. There are two types of boundary layer: laminar and turbulent. One important advantage the turbulent boundary layer has over the laminar type is that :

#160. In which phase of the take-off is the aerodynamic effect of ice located on the wing leading edge most critical?

#161. The formula for the Mach Number is:(a= speed of sound)

#162. The Mach number:

#163. Climbing at a constant Mach Number up to FL 350 the TAS will:

#164. The flight Mach number is 0.8 and the TAS is 400 kts. The speed of sound is:

#165. Which statement with respect to the speed of sound is correct ?

#166. If the altitude is increased and the TAS remains constant in the standard troposphere the Mach Number will

#167. The speed of sound is affected by the:

#168. An aeroplane is descending at a constant Mach number from FL 350. What is the effect on true airspeed ?

#169. To be able to predict compressibility effects you have to determine the:

#170. A normal shock wave:

#171. Which statement is correct about a normal shock wave ?

#172. Compared with an oblique shock wave at the same Mach number a normal shock wave has a

#173. Compared with an oblique shock wave at the same Mach number a normal shock wave has a

#174. The regime of flight from the critical Mach number up to M = 1.3 is called the

#175. Mcrit is the free stream Mach Number at which:

#176. When the Mach number is slowly increased in straight and level flight the first shockwaves will occur:

#177. The critical Mach Number of an aeroplane is the free stream Mach Number, which produces the first evidence of :

#178. Air passes a normal shock wave. Which of the following statements is correct?

#179. The critical Mach number for an aerofoil equals the free stream airfoil Mach number at which:

#180. When the air has passed through a normal shock wave the Mach number is

#181. When the air is passing through a shock wave the static temperature will

#182. When the air is passing through a shock wave the density will

#183. When air has passed through a shock wave the speed of sound is

#184. Just above the critical Mach number the first evidence of a shock wave will appear at the

#185. Critical Mach-number is the :

#186. The loss of total pressure in a shock wave is due to the fact that

#187. Which of the following (1) aerofoils and (2) angles of attack will produce the lowest Mcrit values?

#188. In the transonic range the aeroplane characteristics are strongly determined by:

#189. Which of the following flight phenomena can happen at Mach Numbers below the critical Mach Number?

#190. The critical Mach Number of an aeroplane can be increased by:

#191. In transonic flight the ailerons will be less effective than in subsonic flight because:

#192. Two methods to increase the critical Mach Number are:

#193. If an aeroplane is flying at transonic speed with increasing Mach number the shock wave on the upper side of the wing

#194. To increase the critical Mach number a conventional aerofoil should

#195. The critical Mach number can be increased by

#196. Some aeroplanes have a 'waist' or 'coke bottle' contoured fuselage. This is done to

#197. The application of the area rule on aeroplane design will decrease the

#198. When comparing a rectangular wing and a swept back wing of the same wing area and wing loading, the swept back wing has the advantage of :

#199. What is the influence of decreasing aeroplane weight on Mcrit at constant IAS ?

#200. What is the effect of a decreasing aeroplane weight on Mcrit at n=1, when flying at constant IAS ? The value of Mcrit:

#201. How does stalling speed (IAS) vary with altitude?

#202. Which kind of flow separation occurs at the smallest angle of attack?

#203. At higher altitudes, the stall speed (IAS):

#204. Shock stall is:

#205. Which of the following flight phenomena can only happen at Mach Numbers above the critical Mach Number?

#206. Shock induced separation results in

#207. In the transonic range lift will decrease at the shock stall due to the

#208. The high speed buffet is induced by

#209. ""Tuck under"" is caused by (i) which movement of the centre of pressure of the wing and (ii) which change of the downwash angle at the location of the stabilizer.

#210. The consequences of exceeding Mcrit in a swept-wing aeroplane may be : (assume no corrective devices, straight and level flight)

#211. The Mach trim system will:

#212. The Mach trim system will prevent:

#213. When an aeroplane is flying through the transonic range with increasing Mach Number the centre of the pressure of the wing will move aft. This requires:

#214. Tuck under will happen

#215. The Mach-trim function is installed on most commercial jets in order to minimize the adverse effects of :

#216. What data may be obtained from the Buffet Onset Boundary chart?

#217. The maximum acceptable cruising altitude is limited by a minimum acceptable loadfactor because exceeding that altitude:

#218. Should a transport aeroplane fly at a higher Mach number than the 'buffet-onset' Mach number?

#219. A jet aeroplane is cruising at high altitude with a Mach-number, that provides a buffet margin of 0.3g incremental. In order to increase the buffet margin to 0.4g incremental the pilot must :

#220. The buffet margin :

#221. Vortex generators on the upper side of the wing surface will:

#222. Vortex generators on the upper side of the wing:

#223. Vortex generators mounted on the upper wing surface will

#224. How will the density and temperature change in a supersonic flow from a position in front of a shock wave to behind it ?

#225. At what speed does the front of a shock wave move across the earth's surface?

#226. In supersonic flight, all disturbances produced by an aeroplane are:

#227. The bow wave will appear first at:

#228. If the Mach number of an aeroplane in supersonic flight is increased, the shock wave angles will

#229. When air has passed an expansion wave, the static pressure is:

#230. When the air is passing through an expansion wave the local speed of sound will

#231. When the air is passing through an expansion wave the Mach number will

#232. When the air is passing through an expansion wave the static temperature will

#233. In case of supersonic flow retarded by a normal shock wave a high efficiency (low loss in total pressure) can be obtained if the Mach number in front of the shock is

#234. Which statement is correct about an expansion wave in a supersonic flow ?1- The density in front of an expansion wave is higher than behind.2- The pressure in front of an expansion wave is higher than behind

#235. On a non swept wing, when the aerofoil is accelerated from subsonic to supersonic speeds, the aerodynamic centre :

#236. If an aeroplane is accelerated from subsonic to supersonic speeds, the centre of pressure will move:

#237. The aft movement of the centre of pressure during the acceleration through the transonic flight regime will:

#238. In supersonic flight aerofoil pressure distribution is:

#239. If a symmetrical aerofoil is accelerated from subsonic to supersonic speed the centre of lift will move

#240. The additional increase of drag at Mach Numbers above the critical Mach Number is due to:

#241. If the total sum of moments about one of its axis is not zero, an aeroplane:

#242. In which situation would the wing lift of an aeroplane in straight and level flight have the highest value ?

#243. If the sum of moments in flight is not zero, the aeroplane will rotate about:

#244. When an aeroplane with the centre of gravity forward of the centre of pressure of the combined wing / fuselage is in straight and level flight, the vertical load on the tailplane will be:

#245. An aeroplane, with a C.G. location behind the centre of pressure of the wing can only maintain a straight and level flight when the horizontal tail loading is:

#246. In a twin-engined jet powered aeroplane (engines mounted below the low wings) the thrust is suddenly increased. Which elevator deflection will be required to maintain the pitching moment zero ?

#247. Which of the following statements is correct?

#248. Positive static stability of an aeroplane means that once it has been displaced the :

#249. After a disturbance about the lateral axis, an aeroplane oscillates about the lateral axis at a constant amplitude. The aeroplane is:

#250. Which one of the following statements about the dynamic stability of a conventional aeroplane about the lateral axis is correct?

#251. The ""short period mode"" is an:

#252. An aeroplane that has positive static stability:

#253. A statically unstable aeroplane is:

#254. One of the requirements for dynamic stability is:

#255. The manoeuvrability of an aeroplane is best when the:

#256. Longitudinal static stability is created by the fact that the:

#257. The aerodynamic centre of the wing is the point, where:

#258. For a normal stable aeroplane, the centre of gravity is located:

#259. The max aft position of the centre of gravity is amongst others limited by the:

#260. A C.G location beyond the aft limit leads to:

#261. In what way is the longitudinal stability affected by the degree of positive camber of the aerofoil?

#262. Which part of an aeroplane provides the greatest positive contribution to the static longitudinal stability ?

#263. During landing of a low-winged jet aeroplane, the maximum elevator up deflection is normally required when the flaps are:

#264. The C.G. position of an aeroplane is forward of the neutral point in a fixed location. Speed changes cause a departure from the trimmed position. Which of the following statements about the stick force stability is correct?

#265. ""Tuck under"" is:

#266. ""Tuck under"" may happen at:

#267. Which of the following statements about a Mach trimmer is correct?

#268. In case the Mach trimmer fails:

#269. A Machtrimmer:

#270. The (1) stick force stability and the (2) manoeuvre stability are positively affected by:

#271. Which statement about stick force per g is correct?

#272. The value of the manoeuvre stability of an aeroplane is 150 N/g. The load factor in straight and level flight is 1. The increase of stick force necessary to achieve the load factor of 2.5 is:

#273. An aeroplane has static directional stability, in a side-slip to the right, initially the:

#274. The effect of a positive wing sweep on static directional stability is as follows:

#275. The effect of a high wing with zero dihedral is as follows:

#276. Which of the following lists aeroplane features that each increase static lateral stability ?

#277. Which type of wing arrangement decreases the static lateral stability of an aeroplane?

#278. The effect of a ventral fin on the static stability of an aeroplane is as follows : (1=longitudinal, 2=lateral, 3=directional)

#279. Dihedral of the wing:

#280. Which statement is correct for a side slip condition at constant speed and side slip angle, where the geometric dihedral of an aeroplane is increased ?

#281. Which of the following statements about dihedral is correct?

#282. Which of the following statements about static lateral and directional stability is correct?

#283. Sensitivity for spiral dive will occur when :

#284. Which one of the following systems suppresses the tendency to ""Dutch roll""?

#285. Which aeroplane behaviour will be corrected by a yaw damper ?

#286. What will increase the sensitivity to Dutch Roll?

#287. With increasing altitude and constant IAS the static lateral stability (1) and the dynamic lateral/directional stability (2) of an aeroplane with swept-back wing will:

#288. Rotation about the lateral axis is called :

#289. Rolling is the rotation of the aeroplane about the:

#290. What is the effect on the aeroplane's static longitudinal stability of a shift of the centre of gravity to a more aft location and on the required control deflection for a certain pitch up or down?

#291. The centre of gravity moving aft will:

#292. In a mechanically controlled aeroplane, the most forward allowable position of the centre of gravity could be limited by the:

#293. When the C.G. position is moved forward, the elevator deflection for a manoeuvre with a load factor greater than 1 will be:

#294. An advantage of locating the engines at the rear of the fuselage, in comparison to a location beneath the wing, is :

#295. What happens during an engine failure with two similar aeroplanes with wing mounted engines, one of them with jet engines, the other one with co-rotating propellers:

#296. A jet aeroplane equipped with inboard and outboard ailerons is cruising at its normal cruise Mach number. In this case

#297. Flaperons are controls which are used simultaneously as

#298. When are outboard ailerons (if present) de-activated ?

#299. During initiation of a turn with speedbrakes extended, the roll spoiler function induces a spoiler deflection:

#300. Differential aileron deflection:

#301. An example of differential aileron deflection during initiation of left turn is:

#302. How is adverse yaw compensated for during entry into and roll out from a turn ?

#303. One method to compensate adverse yaw is a

#304. Which of the following statements concerning control is correct?

#305. Which phenomenon is counteracted with differential aileron deflection?

#306. If the nose of an aeroplane yaws to port (left), this causes:

#307. Which moments or motions interact in a dutch roll?

#308. Which statement is correct about a spring tab ?

#309. Which kind of ''tab'' is commonly used in case of manual reversion of fully powered flight controls ?

#310. An aeroplane has a servo-tab controlled elevator. What will happen when only the elevator jams during flight ?

#311. A horn balance in a control system has the following purpose:

#312. Which statement about a primary control surface controlled by a servo tab, is correct ?

#313. Examples of aerodynamic balancing of control surfaces are:

#314. Examples of aerodynamic balancing of control surfaces are:

#315. elevator deflection, dynamic pressure

#316. When power assisted controls are used for pitch control, this:

#317. When flutter damping of control surfaces is obtained by mass balancing, these weights will be located with respect to the hinge of the control surface:

#318. What is the position of the elevator in relation to the trimmable horizontal stabilizer of a power assisted aeroplane, which is in trim ?

#319. How would the exterior appearance of an aeroplane change, when trimming for speed increase ?

#320. In general transport aeroplanes with power assisted flight controls are fitted with an adjustable stabilizer instead of trim tabs on the elevator. This is because :

#321. How does the exterior view of an aeroplane change, when the trim is used during a speed decrease ?

#322. If the elevator trim tab is deflected up, the cockpit trim indicator presents:

#323. One advantage of a movable-stabilizer system compared with a fixed stabilizer system is that:

#324. What should be usually done to perform a landing with the stabilizer jammed in the cruise flight position ?

#325. Which statement about a jet transport aeroplane is correct, during take-off at the maximum allowable forward centre of gravity limit, while the THS (Trimmable Horizontal Stabilizer) has been positioned at the maximum allowable AND (Aeroplane Noise Down) position

#326. Which statement about the trim position is true related to centre of gravity and adjustable stabiliser position ?

#327. ""Flutter"" may be caused by:

#328. A commercial jet aeroplane is performing a straight descent at a constant Mach Number with constant weight. The operational limit that may be exceeded is:

#329. VMO :

#330. A jet transport aeroplane is in a straight climb at a constant IAS and constant weight. The operational limit that may be exceeded is:

#331. Which statement with respect to the climb is correct ?

#332. The relationship between the stall speed VS and VA (EAS) for a large transport aeroplane can be expressed in the following formula:(SQRT= square root)

#333. By what percentage does VA (EAS) alter when the aeroplane's weight decreases by 19%?

#334. Which load factor determines VA?

#335. What can happen to the aeroplane structure flying at a speed just exceeding VA ?

#336. What is the limit load factor of a large transport aeroplane in the manoeuvring diagram?

#337. VA is:

#338. Load factor is :

#339. For an aeroplane with one fixed value of VA the following applies. VA is :

#340. The positive manoeuvring limit load factor for a large jet transport aeroplane with flaps extended is:

#341. The positive manoeuvring limit load factor for a light aeroplane in the utility category in the clean configuration is:

#342. Which statement regarding the gust load factor on an aeroplane is correct (all other factors of importance being constant) ?1. Increasing the aspect-ratio of the wing will increase the gust load factor.2. Increasing the speed will increase the gust load factor.

#343. Which of the following statements is true?

#344. The lift coefficient (CL) of an aeroplane in steady horizontal flight is 0.42, increase in angle of attack of 1 degree increases CL by is 0.1. A vertical up gust instantly changes the angle of attack by 3 degrees. The load factor will be :

#345. The lift coefficient (CL) of an aeroplane in steady horizontal flight is 0.4. Increase of angle of attack of 1 degree will increase CL by 0.09. A vertical up gust instantly changes the angle of attack by 5 degrees. The load factor will be :

#346. The shape of the gust load diagram is also determinated by the following three vertical speed in ft/s (clean configuration) :

#347. Which combination of speeds is applicable for structural strength in gust (clean configuration) ?

#348. The extreme right limitation for both V-n (gust and manoeuvre) diagrams is created by the speed:

#349. The lift coefficient (CL) of an aeroplane in steady horizontal flight is 0.35. Increase in angle of attack of 1 degree will increase CL by 0.079. A vertical up gust instantly changes the angle of attack by 2 degrees. The load factor will be :

#350. Which has the effect of increasing load factor ? (all other relevant factors being constant)

#351. What wing shape or wing characteristic is the least sensitive to turbulence :

#352. Which statement is correct about the gust load on an aeroplane (IAS and all other factors of importance remaining constant) ?1. the gust load increases, when the weight decreases.2. the gust load increases, when the altitude increases.

#353. The angle of attack for a propeller blade is the angle between blade chord line and:

#354. Which of these definitions of propeller parameters is correct?

#355. Why is a propeller blade twisted from root to tip?

#356. Constant-speed propellers provide a better performance than fixed-pitch propellers because they:

#357. If you push forward the RPM lever of a constant speed propeller during a glide with idle power and constant speed, the propeller pitch will:

#358. Does the pitch-angle of a constant-speed propeller alter in medium horizontal turbulence?

#359. Which of the following statements about a constant speed propeller is correct?

#360. The propeller blade angle of attack on a fixed pitch propeller is increased when :

#361. If you decrease the propeller pitch during a glide with idle-power at constant IAS the lift to drag ratio will

#362. If you increase the propeller pitch during a glide with idle-power at constant IAS the lift to drag ratio will

#363. For a fixed-pitch propeller designed for cruise, the angle of attack of each blade, measured at the reference section:

#364. Propeller efficiency may be defined as the ratio between:

#365. If you pull back the RPM lever of a constant speed propeller during a glide with idle power and constant speed, the propeller pitch will:

#366. An engine failure can result in a windmilling (1) propeller and a non rotating (2) propeller. Which statement about propeller drag is correct?

#367. When the blades of a propeller are in the feathered position:

#368. Increasing the number of propeller blades will:

#369. Which is one of the disadvantages of increasing the number of propeller blades ?

#370. A propeller turns to the right, seen from behind. The torque effect in the take-off will:

#371. Gyroscopic precession of the propeller is induced by:

#372. A propeller is turning to the right, seen from behind. The asymmetric thrust effect is mainly induced by:

#373. A propeller is turning to the right, seen from behind. The asymmetric thrust effect in the climb will:

#374. The lift of an aeroplane of weight W in a constant linear climb with a climb angle (gamma) is approximately:

#375. An aeroplane performs a continuous descent with 160 kts IAS and 1000 feet/min vertical speed. In this condition:

#376. What factors determine the distance travelled over the ground of an aeroplane in a glide ?

#377. What is the correct relation of the True Air Speed (TAS) for minimum sink rate (VR/Dmin) and best glide angle (VBest glide) at a given altitude?

#378. Which statement is correct at the speed for minimum drag (subsonic) ?

#379. Which of the following factors will lead to an increase of ground distance during a glide ?

#380. A jet aeroplane is rolled into a turn, while maintaining airspeed and holding altitude. In such a case, the pilot has to:

#381. An aeroplane is in a steady turn, at a constant TAS of 300 kt, and a bank angle of 45°. Its turning radius is equal to:(given: g= 10 m/s²)

#382. By what percentage does the lift increase in a steady level turn at 45° angle of bank, compared to straight and level flight?

#383. A light twin is in a turn at 20 degrees bank and 150 kt TAS. A more heavy aeroplane at the same bank and the same speed will:

#384. What is the approximate value of the lift of an aeroplane at a gross weight of 50 000 N, in a horizontal coordinated 45 degrees banked turn ?

#385. Which statement is correct about an aeroplane, that has experienced a left engine failure and continues afterwards in straight and level cruise flight with wings level ?

#386. Which of the following statements is correct ?I When the critical engine fails during take-off the speed VMCL can be limiting.II The speed VMCL is always limited by maximum rudder deflection

#387. I is incorrect, II is correct

#388. I is correct, II is correct

#389. Why is VMCG determined with the nosewheel steering disconnected?

#390. decreases, because the engine thrust decreases.

#391. From the polar diagram of the entire aeroplane one can read:

#392. (CL/CD)max

Finish
INDIGO AERODYNAMIC
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