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Comparison of Profile-drag and Boundary-layer Measurements Obtained in Flight and in the Full-scale Wind Tunnel (1939)
NASA Technical Reports Server (NTRS) · leaf 18
Figure 4.- Boundary-layer velocity distributions along upper Figure 5.- Boundary-layer velocity distributions along upper surface of N-22 airfoil; cL , 0.635. surface of N-22 airfoil-, ot , 0.580. _Reynolds 1.2 ~Number Height above + Flight 4.6 x 106 surface, in. -o Tunnel 4.3 u/U .20 .30 .20 .30…NASA Technical Reports Server (NTRS)
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