Pressure Distribution Over a Thick, Tapered and Twisted Monoplane Wing Model-NACA 81-J (1932)
NASA Technical Reports Server (NTRS) · leaf 6
nother angle of attack. Check decrease in velocity. This was accomplished by in- records taken during the tests indicated an accuracy clining the leading edge of the plane, which consisted in measured pressure heads of within il.O per cent. of a hinged flap 5K inches wide, until vertical velocity… … Figure 2.—Airfoil and separation plane set-up in tunnel the tests the dynamic pressure was nudntained con- The model was set at the angle of attack of zero stant at 6.47 pounds per square foot, corresponding lift for these surveys, and it is fairly certain that the to an air speed of about 50.3 m.…
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