Aerodynamics Exam

BASIC AERODYNAMICS

SEMESTER-I

FLYTECH AVIATION ACADEMY  SEMESTER EXAMINATION EXAMINATION DECEMBER - 2014 SEMESTER-I SEMESTER-I (FW) SUBJECT: SUBJECT: BASIC AERODYNAMICS SUBJECT CODE:

TOTAL TOTAL MARKS:100 TIME: 2 1/2HRS DATE

NAME: NO:

ROLL

ART-A (OBJECTI!E) 1. On a swept wing aircraft if both wing tip sections lose lift simultaneously the aircraft will a) roll b) pitch nose up c) pitch nose down d) sideslip

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2. MTCS ( ) a) Density altitude is pressure pressure altitude corrected corrected for temperature. temperature.  b) !ressure increases with pressure altitude. c) The temperatutre temperatutre remains remains constant upto 11"### 11"### mtr. mtr. d) $nn%ironmental lapse rate refers to change change in temperature of a mass of air as it mo%es upwards. &. On a straight wing aircraft" stall commences at the a) root on a high thickness ratio wing  b) tip on a high thic'ness ratio wing c) tip on a low thic'ness ratio wing d) root on a low thic'ness ratio wing

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. On a high wing aircraft in a turn a) the upgoing wing loses lift causing a destabilising effect  b) the upgoing wing loses lift causing a stabilising effect c) the down-going wing gains lift causing a stabilising effect d) the downgoing wing loses lift causing a destabilising effect

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*. +or the same angle of attac'" the lift on a delta wing a) is greater than the lift on a high aspect ratio wing  b) is lower than the lift on a high aspect ratio wing c) is the same as the lift on a high aspect ratio wing d) none

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,. The -S a) is ta'en from the e/uator  b) is taken from 45 degrees latitude c) assumes a standard day d) either (a) or (b)

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BASIC AERODYNAMICS

SEMESTER-I

0. t higher altitudes as altitude increases" pressure a) decreases at constant rate  b) increases at constant rate c) increases eponentially d) decreases exponentially

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4. 3hen the pressure is half of that at sea le%el" what is the altitude5 a) 12"### ft  b) "### ft c) 1"### mtr. d) 18!!! ft

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1#. 6uring a turn" the stalling angle a) increases  b) decreases c) remains the same d) decreases and then remain the same

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. The thrustdrag couple o%ercomes the liftweight couple. 3hat direction of  force is re/uired to be produced by the tail of the aircraft to maintain straight and le%el flight a) upwards  b) downwards c) sideways d) none

11. -f gauge pressure on a standard day at sea le%el is 2* !S-" the absolute  pressure is a) 1#.& !S b) &. !Sc) 11.0 !Sd) "#.$# %&' 12. The C of 7 mo%es in flight. The most li'ely cause of this is a) mo%ement of passengers  b) mo%ement of the centre of pressure c) consumption of fuel and oils d) improper loading of aitcraft

BASIC AERODYNAMICS SEMESTER-I 1&. -n the diagram mentioned abo%e what does the air circulation in 8one 9: stand for  ( a) 6ownwash  b) (p wash c) ;oth downwash and bound %orte

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1. -n the diagram mentioned abo%e what does point 96: stand for a) entre of pressure b) Centre of gra%ity c) Centre of symmetry d)  >>>>>>> and increases with an increase in >>>>>>>> ( ) a) ?ow pressure and O  b) @igh pressure and O c) @igh pressure and camber  d) +ow pressure and camber 10. !ressure decreases a) proportionally with a decrease in temperature  b) in%ersely proportional to temperature c) !ressure and temperature are not related

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1. 3hat is sea le%el pressure5 a) 1!1"., mb c) 1#&2.2 mb

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 b) 1#12.& mb d) 1#1&.2 pa

14. 3hen the weight of an aircraft increases" the minimum drag speed a) decreases  b) increases c) remains the same

2#.  graph showing the angle of an attac' of an aircraft Aglider %ersus its liftcoefficient represents  a) &tall cur*e  ) b) !olar cur%e c) erodynamic efficiency d) >>>>>> for maimum effecti%eness . a) Supersonic ( ) b) subsonic c) transonic d) hypersonic *2. The tail rotor employed in helicopter is to pro%ide  a) /nti : tor;ue effect  b) 7eneration of lift c) ;oth 9a: G 9b: d) > for maimum effecti%eness . a) Supersonic ( b) subsonic c) transonic d) hypersonic *2. The tail rotor employed in helicopter is to pro%ide  a) /nti : tor;ue effect  b) 7eneration of lift c) ;oth 9a: G 9b: d) H 0/&' /@H>DGB/'& &@ @I/ C

1 2 " 4 # $ % &

B B D B B B A B

"1 "2 "" "4 "# "$ "% "&

C A B B B D A C

BASIC AERODYNAMICS

' 10 11 12 1" 14 1# 1$ 1% 1& 1' 20 21 22 2" 24 2# 2$ 2% 2& 2' "0

B C B D A B A D C B C D C D C B A D B A A D

SEMESTER-I

"' 40 41 42 4" 44 4# 4$ 4% 4& 4' #0 #1 #2 #" #4 ## #$ #% #& #' $0

B A B A B C A D B C B B B A C B A A A C C A