1. For high aspect ratio strength of the wing tip vortex is low.
a) True
b) False
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
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. 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
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.
4. 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
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.
5. 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
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.
6. Wing sweep is used to ____
a) increase critical mach number
b) decrease critical mach number
c) increase lofting
d) increase drafting
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.
7. The ratio of tip and root chord is called ____
a) taper ratio
b) sweep
c) aspect ratio
d) slope
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.
8. 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
Explanation: Taper ratio is defined as,
Taper ratio = tip chord/root chord = 0.9/2 = 0.45.
9. 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
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.
10. Excessive dihedral can produce _____
a) dutch roll
b) thrust
c) pitch
d) deflection at nose
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.