A supersonic 2D airfoil has Mach number of 1.5. Find Lift curve slope of the airfoil.

0.062 per degree

0.062 per rad

12.56 per degree

24 per degree

Correct Answer : 0.062 per degree

Explanation : Given, mach number M = 1.5
2D lift curve slope = 4 / (M² – 1)^0.5
= 4 / (1.5² – 1)^0.5 = 3.57 per rad = 3.57/57.3 = 0.062 per degree.

Recently Updated in Aircraft Design Questions

Find the approximate value of wetted area Swet for given reference area of Sref=20 unit and parasite drag coefficient of 0.0028. Consider equivalent skin friction coefficient Cf as 0.003.

12 unit

18.67 unit

20 unit

65 unit

Correct Answer : Option (B) : 18.67 unit

Explaination : Wetted area Swet = Parasite drag coefficient*Sref/Cf
= 0.0028*20/0.003 = 18.67 unit.

Consider equivalent skin friction coefficient as 0.0025 and Swet/Sref = 0.6. Evaluate parasite drag.

02.34

1.23

0.0015

0.000025

Correct Answer : Option (C) : 0.0015

Explanation : Parasite drag = equivalent skin friction coefficient*(Swet/Sref)
= 0.0025*0.6 = 0.0015.

Determine the initial estimation of parasite drag coefficient if, equivalent skin friction coefficient is 0.004 and ratio of wetted area to the reference area is 0.8.

0.0032

0.04

1.2

4.2

Correct Answer : Option (A) : 0.0032

Explaination : Parasite drag coefficient = equivalent skin friction coefficient*area ratio
= 0.004*0.8 = 0.0032.