A wing alone arrangement has wing lift curve slope of 2.65 per rad. Find slope of pitching moment coefficient. Given Xcg = 0.3.

0.0035 per degree

0.025 per degree

0.03 per rad

45 per rad

Correct Answer : 0.025 per degree

Explanation : Considering ideal location of aerodynamic centre i.e. Xac = 0.25
Slope of pitching moment curve = (wing lift curve slope*[Xcg-Xac])
= (2.56[0.3-0.25])
= 0.1325 per rad = 0.00253 per degree.

Recently Updated in Aircraft Design Questions

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

Phugoid

Flap

Dutch roll

Lateral mode

Correct Answer : Option (B) : Flap

Explanation : Flap is a high lift device. Flap is used to increase lift produced by the wing. Flaps are used to increase camber and overall surface area of the wing. This results in increased lift. Dutch roll, phugoid, lateral mode etc. are typical aircraft dynamic modes.

Which of the following is an example of longitudinal mode?

Dutch

Lateral

Phugoid

Aileron

Correct Answer : Option (C) : Phugoid

Explanation : Phugoid mode is an example of longitudinal mode. Dutch and lateral mode are not example of longitudinal mode. Aileron is known as primary control surface. Aileron is used to control the aircraft rolling moment.

Find critical damping coefficient if damping ratio is 0.5 and damping coefficient is 1.1.

2.2

4.1

4.9

5.2

Correct Answer : Option (A) : 2.2

Explanation : Critical damping coefficient damping coefficient/ damping ratio 1.1/0.5 = 2.2.