Determination of the Profile Drag of an Airplane Wing in Flight at High Reynolds Numbers
Description:
"Flight tests were made to determine the profile-drag coefficients of a portion of the original wing surface of an all-metal airplane and of a portion of the wing made aerodynamically smooth and more nearly fair than the original section. The wing section was approximately the NACA 2414.5. The tests were carried out over a range of airplane speeds giving a maximum Reynolds number of 15,000,000. Tests were also carried out to locate the point of transition from laminar to turbulent boundary laye…
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Date:
January 6, 1939
Creator:
Bicknell, Joseph
Item Type:
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Report
Partner:
UNT Libraries Government Documents Department