The data obtained from the wind tunnel test of a rectangular thin wing of = 3

The data obtained from the wind tunnel test of a rectangular thin wing of λ = 3 are as follows: On the basis of the above experimental data, try to calculate the lift line slope value of the rectangular wing of λ = 4 with the same airfoil at Ma∞ = 0.80.

Transcribed Image Text:

Max CL/rad da 0.40 0.0600 0.70 0.0660 0.80 0.0690 0.90 0.0750 0.95 0.0825