# Aircraft Design Questions and Answers – Wing Geometry-2

This set of Aircraft Design Questions and Answers focuses on “Wing Geometry-2”.

1. For high aspect ratio strength of the wing tip vortex is low.
a) True
b) False
View Answer

Answer: a
Explanation: Wing tip of high aspect ratio wing is far from root as compared to low aspect ratio wing. The wing affected by higher ratio will be less and the strength of tip vortex will be less as well.

2. If aspect ratio of wing is 8 and S=0.1m2 then, what will be the span of wing?
a) 0.89m
b) 0.89cm
c) 0.89
d) 0.89inch
View Answer

Answer: a
Explanation: Given, wing Aspect ratio AR=8, S=0.1m2
Aspect ratio = span square/ reference area
8 = span square / 0.1
Span square = 8*0.1 = 0.8
Hence, span = 0.89m.

3. Which of the following is correct in accordance to diagram?

a) Aspect ratio of 1 is highest
b) Aspect ratio of 2 is maximum
c) Aspect ratio of 3 is maximum
d) Similar aspect ratio
View Answer

Answer: a
Explanation: High aspect ratio will give higher value of maximum lift coefficient. As shown in figure for -1, maximum lift coefficient is highest and hence, aspect ratio of 1 will be highest. Similarly for -3 it is lowest and hence, aspect ratio of 3 will be minimum.
advertisement
advertisement

4. Let’s consider an aircraft has statistically determined aspect ratio of 8.1. Aircraft has canard which gives contribution of 10% for total lift. Determine the aspect ratio of wing.
a) 9
b) 0.9
c) 10
d) 8.1
View Answer

Answer: a
Explanation: Given, Aspect ratio statistically ARst = 8.1
Canard contribution = 10%
Here, total lift is not produced by the wing only. Canard is also responsible for it as well.
Hence, wing contribution = total lift – lift by canard = 100% – 10% = 90% = 0.9.
Now, aspect ratio of the wing is given by,
ARw = ARst / wing contribution = 8.1 / 0.9 = 9.

5. An aircraft with elliptic wing planform has parasite drag coefficient as 0.6. Lift coefficient of wing is 0.25 and aspect ratio is 7.5. If induced drag co-efficient is 0.0235 then, find total drag coefficient for the wing.
a) 0.06235
b) 0.5235
c) 0.6
d) 0.0235
View Answer

Answer: a
Explanation: Given, parasite drag co-efficient = 0.6, induced drag coefficient = 0.0235
Total drag coefficient = Parasitic drag coefficient + induced drag coefficient = 0.6+0.0235 = 0.06235.

6. An aircraft with elliptic wing planform has parasite drag coefficient as 0.9. Lift coefficient of wing is 1.8 and aspect ratio is 8.5. Find total drag coefficient for the wing.
a) 1.021
b) 0.9
c) 0.121
d) 0.25
View Answer

Answer: a
Explanation: Given, elliptic wing, parasite drag coefficient CD0 = 0.9
Lift coefficient CL = 1.8, Aspect ratio AR=8.5
Now, Total drag coefficient = Parasitic drag coefficient (CD0) + induced drag coefficient (CDi)
CDi = CL*CL / (ᴨ*e*AR) = 1.8*1.8 / (ᴨ*1*8.5) = 0.121
Hence, Total drag coefficient = CD0 + CDi = 0.9 + 0.121 = 1.021.

7. Wing sweep is used to ____
a) increase critical mach number
b) decrease critical mach number
c) increase lofting
d) increase drafting
View Answer

Answer: a
Explanation: If wing is at some finite angle from fuselage reference line then it is called wing is sweep by that much degree. Main function of sweep is to increase critical mach number. Lofting is skin modelling and drafting is drawing phenomena.
advertisement

8. Canard pusher aircraft uses wing sweep to change location of aerodynamic centre.
a) True
b) False
View Answer

Answer: a
Explanation: Canard pusher aircrafts are heavier at rearward part. At tail weight is more. By sweeping the wing we can alter the location of aerodynamic center for balance.

9. The ratio of tip and root chord is called ____
a) taper ratio
b) sweep
c) aspect ratio
d) slope
View Answer

Answer: a
Explanation: Taper ratio is the ratio of tip chord of wing to root chord of the wing. Aspect ratio is square of span divided by area. Sweep is angle between wing and fuselage reference line.

advertisement

10. If root chord is 2m and tip chord is 0.9m then, find taper ratio.
a) 0.45
b) 0.55
c) 0.65
d) 0.25
View Answer

Answer: a
Explanation: Taper ratio is defined as,
Taper ratio = tip chord/root chord = 0.9/2 = 0.45.

11. What is the function of wing twist?
a) To improve stall characteristics at tip
b) To reduce lift by tail
c) To provide lofting
d) To increase engine thrust
View Answer

Answer: a
Explanation: Wing twist is used to delay the stall at tip typically. Wing twist can be used to rearrange the lift distribution of the wing. Lofting is skin modelling.

12. Excessive dihedral can produce _____
a) dutch roll
b) thrust
c) pitch
d) deflection at nose
View Answer

Answer: a
Explanation: Dihedral is upward deflection of wing. It is used to provide roll stability. If excessive dihedral is provided then, it will lead to dutch roll; continuous side to side motion involving yaw and roll.

13. Determine the corrections or otherwise of the following assertion [A] and reason [R]:
Assertion [A]: In general, wing twist should not be more than 6°.
Reason[R]: Wing twist is used to improve stall properties at tip.
a) Both [A] and [R] are true and [R] is the correct reason for [A]
b) Both [A] and [R] are true but [R] is not the correct reason for [A]
c) [A] is true but [R] is false
d) [A] is false but [R] is true
View Answer

Answer: b
Explanation: Wing twist can optimize the wing lift at a particular lift coefficient. At any different lift coefficient wing twist will not provide 100% accuracy. Wing twist is also used to improve stall at tip.

Sanfoundry Global Education & Learning Series – Aircraft Design.

To practice all areas of Aircraft Design for Interviews, here is complete set of 1000+ Multiple Choice Questions and Answers.

If you find a mistake in question / option / answer, kindly take a screenshot and email to [email protected]

advertisement
advertisement
Subscribe to our Newsletters (Subject-wise). Participate in the Sanfoundry Certification contest to get free Certificate of Merit. Join our social networks below and stay updated with latest contests, videos, internships and jobs!

Youtube | Telegram | LinkedIn | Instagram | Facebook | Twitter | Pinterest
Manish Bhojasia, a technology veteran with 20+ years @ Cisco & Wipro, is Founder and CTO at Sanfoundry. He lives in Bangalore, and focuses on development of Linux Kernel, SAN Technologies, Advanced C, Data Structures & Alogrithms. Stay connected with him at LinkedIn.

Subscribe to his free Masterclasses at Youtube & discussions at Telegram SanfoundryClasses.