Aircraft Design Mock Test 9

10%

Question 1 of 10

1. Which of the following is correct for steady level flight?

T=D

D<T

T>D

L>W

Question 1 of 10

Question 2 of 10

2. Which of the following is not the type of aircraft dynamic mode?

Phugoid

Dutch roll

Lateral mode

Flap

Question 2 of 10

Question 3 of 10

3. An aircraft is designed to be in steady level flight with weight of 1500N and CL of 1.0. Determine at which speed we need to design this aircraft so that it can achieve this requirement. Consider density as 1.2 kg/m³ and reference area as 2m².

35.35m/s

56m/min

56m/s

70km/s

Question 3 of 10

Question 4 of 10

4. For pitching moment coefficient diagram shown below which one will have positive trim AOA?

Aircraft 3

Aircraft 3 and Curve 2 both

Aircraft 1

Aircraft 2

Question 4 of 10

Question 5 of 10

5. Stability about roll axis is called _____________

elevator control

directional stability

lateral stability

longitudinal stability

Question 5 of 10

Question 6 of 10

6. Canard will provide longitudinal static stability.

False

True

Question 6 of 10

Question 7 of 10

7. Elevator control power is given by _____

T = CD0 + K*CL

\(\frac{dCm}{d\delta e}\)

DCL/ɑ

Zero lift drag

Question 7 of 10

Question 8 of 10

8. Find the appropriate value of pitching moment coefficient derivative if lift curve slope is 0.032 per degree and Xcg is 0.3. Consider neutral point is located at 60 % of chord from leading edge.

0.1

-7 per degree

-0.0096 per degree

2.56 per degree

Question 8 of 10

Question 9 of 10

9. Aircraft can suffer from adverse yaw during rolling.

True

False

Question 9 of 10

Question 10 of 10

10. Which of the following is correct?

Thrust required is minimum if L/D is minimum for cruise

Thrust required is minimum if L/D is maximum during cruise

Power required is minimum if L/D is maximum

Thrust required is maximum if L/D is maximum during steady state

Question 10 of 10