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Wind tunnel investigation of NACA 66(215)-216, 66,1-212, and 65(sub 1)-212 airfoils with 0.20-airfoil-chord split flaps

Felicien F Fullmer

Abstract

An. invest i~atim was carried out in the NACA twodii?lenS ional low-turbulence pres sure tunne 1 of the NACA f16(215 )-216, 66,1-212, and 651-212 airfoil.sections eql~ipped with split flaps having chord.s :?0percent o.f the airfoil.chord.The purpose was to determine the maxi~tum-l, j.ft characteristics of these low-drag airfoil Sections wit'h split flaps .All the present tests were mad e at & pLe y~olds ntlm'be~"

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Key concepts: Airfoil, NACA airfoil, Chord (peer-to-peer), Wind tunnel, Lift-to-drag ratio, Drag, Angle of attack, Lift (data mining)