Determination of the profile drag of an airplane wing in flight at high Reynolds numbers (1939)
NASA Technical Reports Server (NTRS) · leaf 9
. The more forward position of the transi- probably slightly higher than it would have been for a tion point observed in the tests could easily account for true N. A. C. A. 2414.5 section in flight. This differ- the difference in profile-drag coefficient found in these ence can be attributed to… … O 10 20 30 40 50 60 Distance along the surface from stagnation point, Distance along the surface from stagnation point, percent chord percent chord Fir.uRE 8.—Boundary-layer surveys on upper surface of smooth wing at Cl—0M. Figure 7 — Boundary-layer surveys on upper surface of smooth wing at…
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