Consider a finite wing with an aspect ratio of 8 and an induced drag factor 8...

 

Transcribed Image Text:

Consider a finite wing with an aspect ratio of 8 and an induced drag factor 8 = 0.055. The airfoil section is assumed to be thin and symmetric. Calculate the lift coefficient and induced drag coefficient for this finite wing when it is at an angle of attack of 5 degrees. Assume 8 = T ao and slope a = Note that ao is the lift curve slope of an infinite wing obtained 1+(AR)(1+T) from thin airfoil theory. 2.0 1.6 1.2 0.8 0.4 0 -0.4 -0.8 -1.2 T T T T 1 NACA 2412 airfoil Gopr000000 0.00 O -8 0 Lift coefficient Moment coefficient 8 a, degrees - Eq. (4.57) Eq. (4.64) Re 3.1 X 106 Re = 8.9 X 106 16 24 0 -0.1 -0.2 -0.3 -0.4 Cm, c/4 Consider a finite wing with an aspect ratio of 8 and an induced drag factor 8 = 0.055. The airfoil section is assumed to be thin and symmetric. Calculate the lift coefficient and induced drag coefficient for this finite wing when it is at an angle of attack of 5 degrees. Assume 8 = T ao and slope a = Note that ao is the lift curve slope of an infinite wing obtained 1+(AR)(1+T) from thin airfoil theory. 2.0 1.6 1.2 0.8 0.4 0 -0.4 -0.8 -1.2 T T T T 1 NACA 2412 airfoil Gopr000000 0.00 O -8 0 Lift coefficient Moment coefficient 8 a, degrees - Eq. (4.57) Eq. (4.64) Re 3.1 X 106 Re = 8.9 X 106 16 24 0 -0.1 -0.2 -0.3 -0.4 Cm, c/4

Answer rating: 100% (QA)

The first step in solving this problem is to compute the lift coefficient CL for the finite wing at an angle of attack of 5 degrees and then calculate ... View the full answer