Section data for thin, highly cambered airfoils in incompressible flow, Volume 1767
Jerome H. Milgram, United States. National Aeronautics and Space Administration, Massachusetts Institute of Technology, Langley Research Center
National Aeronautics and Space Administration, 1971 - Technology & Engineering - 72 pages
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0.8 mean line 2ïï/radian for angles 65 mean line 65-12 SECTION NORMAL aft portion angle of attack angles of incidence attached flow attack less camber ratios causes trailing edge Chordwise Position inches clamped side DATA FOR THIN degrees drag coefficient dynamometer effects of flow forward portion friction drag HIGHLY CAMBERED AIRFOILS highly cambered sections ideal angle inches from leading INCOMPRESSIBLE FLOW laminar flow less camber lift coefficient lift-drag ratio lines with camber load cells Lower Surface Inches measured value meters NACA 65 mean Naval Architecture NORMAL REVERSED UPSIDEDOWN Parawings pinned side pitot tube PLANFORM predicted by thin pressure side Quarter chord pitching Reynolds Number section characteristics section data SECTION NORMAL REVERSED SECTION Station Chordwise shown in Fig special mean line Station Chordwise Position suction side test section theoretical value thicker sections thickness effects thickness form thin airfoil theory THREE ORIENTATIONS Tunnel Wall types of mean Upper Surface Inches values of angle