1) Find the approximate value of velocity of best climb. Consider Thrust loading as 1.08, wing loading as 377 unit, CD0 as 0.025, K as 0.0075 and sea level density as 1.225 unit. a. 98.46 b. 37.45 c. 12.1 d. 189.982
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2) Which of the following is correct value for rate of climb if an aircraft has free stream velocity of 125 m/s? Consider steady climb at climb angle of 10°. a. 21.70 m/s b. 12 m c. 35 m/min d. 1.302 min/m
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3) To operate at R/C of 7.08 m/s, determine the value of excess power. Consider weight of the aircraft as 13127.5 N. a. 92.942 kW b. 1000W c. 13127 N d. 1.312KN
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4) Consider steady climb from an altitude of 10km to 15km. If rate of climb is 20 m/s then, determine the time to climb. a. 250s b. 25 min c. 4.16 hr d. 0.07 min
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5) Corner speed is defined as __________ a. velocity for maximum instantaneous turn b. maximum lift velocity c. maximum aerodynamic efficiency d. minimum instantaneous turn speed
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6) During level turning flight, lift of wing is canted. a. True b. False
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7) If load factor of level turning flight is found to be 1.2 and flight speed is 120m/s then, determine turn rate. a. 3.107 degree/s b. 1.2 rad/s c. 0.03 rad per second d. 1.2
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8) Let’s consider we are designing an aircraft which can have 0.075 rad/s as its turn rate during level turning operation. If load factor is set to be 1.1 then, at which velocity we should fly our aircraft to obtain mentioned requirement. a. 59.8unit b. 590unit c. 5980unit d. 0894unit
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9) During level turning operation my aircraft has load factor of 2. Find the required bank angle for this level turning operation. a. 60° b. 60rad c. 120rad d. 2.1rad
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10) What will be the turn radius if flight speed is 50unit and load factor is 2? Consider Level turn. a. 147.13unit b. 180unit c. 50unit d. 20unit
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11) If an aircraft can slow down during turn then, it is termed as __________ a. instantaneous turn b. non instantaneous turn c. straight flight d. cruise segment
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12) The aircraft _____________ during a sustained turn. a. cannot be slowed down b. can be slowed down c. can lower its velocity d. can increase lofting process effort
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13) An aircraft is in sustained turn with thrust loading of 0.8 and aerodynamic efficiency of 6. Determine the approximate value of maximum load factor. a. 4.8 b. 3 c. 1 d. 12
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14) An aircraft weighing 200kg is in level turning operation. Find the value of vertical component of lift. a. 1.962 KN b. 200N c. 2KN d. 0.2KN
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15) Turn rate is defined as _______ a. ratio of radial acceleration and the velocity b. ratio of lift to drag c. product of thrust and velocity d. drag
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16) For a typical gliding flight, thrust will be ________ a. zero b. equal to the lift c. always same as drag d. always same as weight
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17) The tangent of glide angle is ________ a. equal to drag to lift ratio b. lift to drag ratio c. inverse of thrust d. equal to thrust
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18) If aerodynamic efficiency of the glider is 20 then, found the value of corresponding glide angle. a. 2.86 unit b. 3.8 c. 5.6 d. 12.12
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19) A typical glider has weight of 150N and has glide angle of 2.5°. Find Lift produced by the glider. a. 149.85N b. 150kN c. 322N d. 120Kn
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20) Glider with glide angle of 4.2° is gliding with gliding ratio of _____ a. 13.6 b. 12.9 c. 15 d. 25.4
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21) Typically, a high performance unpowered aircraft is called ________ a. sailplane b. glider c. jet d. twin engine
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22) Find the velocity required for maximum range. Consider a sailplane has wing loading of 110N/m2 and K/CD0 of 0.35. a. 10.3m/s b. 10.3mph c. 12.5mph d. 9.2mph
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23) If a glider needs to be flown at maximum range then, at which value of CL we should fly this glider? Consider CD0/K is 2.8. a. 1.67 b. 3.2 c. 5.6 d. 2.5
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24) Which of the following is correct for a typical glider? a. Drag D = W*cos (gamma) b. Drag D = W*arcsine (gamma) c. Drag D = W d. Drag D = Thrust T
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25) If my glider has lift coefficient at maximum lift to drag as 1.5 and induced drag factor K is 0.007 then, find parasite drag coefficient. a. 0.01575 b. 0.01 N c. 0.02N d. 0.0157N
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26) All the gliders are unpowered. a. True b. False
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27) If a sailplane has glide ratio of 45 then, find horizontal distance travelled by this sailplane. Consider altitude loss of 1000ft. a. 45000ft b. 1000ft c. 3456ft d. 987ft
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28) Sink rate can be used to ____________ a. determine the time a glider may remain in the air b. determine and estimate takeoff gross weight c. estimate only wing loading d. calculate weight to thrust ratio
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29) A glider has aspect ratio of 20 and CD0 of 0.02. In order to attain maximum range, determine the value required aerodynamic efficiency. Take e as 1. a. 28.02 b. 20 c. 30 d. 43
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30) Determine the value of sink rate of glider which is operating with 4.2° of glide angle and has speed of 120m/s. a. 8.78m/s b. 9.8ms c. 56.5ms d. 8.7ms
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31) Graphical representation of sink rate of sailplane is called ____________ a. typical speed polar b. drag polar wing c. lift curve of wing d. propulsion systems
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32) Velocity for the best glide ratio is 100ft/s. Determine velocity for minimum sink rate. a. 76ft/s b. 124m/s c. 23fts d. 45 fts2
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33) Variometer is used for _____________ a. informing pilot when glider is in lift b. increase lift c. thrust reversal d. increase thrust produced
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34) Consider turning glide operation with bank angle of 1.5 and Weight of 125 unit. Find lift. a. 125.042 b. 56 c. 120 d. 345
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35) Determine the value of turn rate. Consider glider has centripetal acceleration of 10 and velocity of 9.5. a. 1.052 b. 9.5 c. 10 d. 2.8
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36) Determine the value of best glide ratio velocity. Consider velocity for minimum sink rate is 10 fps. a. 13.15 fps b. 20 fps c. 11 fps d. 34 fps
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37) Consider turning gliding flight. Turn rate is given as 0.2 unit and velocity of flight is 10 unit. Find the value of turn radius. a. 50 b. 100 c. 2 d. 8
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38) Find the range of glider which has L/D of 13.6 and is descending from 5km. a. 68km b. 12 m c. 12 inch d. 68 m
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39) If KCD0 is 0.014 then, find lift to drag ratio for minimum sink. a. 3.66 b. 36.6 c. 1.4 d. 24
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40) Consider a glider is descending from 2km altitude. If it covers range of 30km then, at which aerodynamic efficiency the glider was flying? a. 15 b. 60 c. 12 d. 21
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