Experimental results are presented for separating flows over a NASA GA(W)-1 airfoil with 2-percent trailing-edge thickness, with emphasis on the mean velocity data that demonstrate flowfield similarity downstream of separation. The length scale presently employed was selected because it furnishes the requisite matching point between the outer, mixing region flow and the back-flow.
Separated flows developing under increasingly adverse pressure gradients
Journal of Aircraft ; 26
1989-01-01
Miscellaneous
No indication
English