PRESSURE DISTRIBUTION OVER THICK TAPERED AIRFOILS, N. h C. A..

M the request of the United States Army Air Service, the tests reported herein were con-ducted in the 5-foot atmospheric wind tunnel of the LangIey MemoriaI A~nauticsl Laboratory. The object was the measurement of prassures over three representative thick, tapered airfoils which are being used on existing or forthcoming Army airphmes. The results me presented in the form of pressure maps, cross-span Ioad and normal forw coefficient curves and load contours. The pressure distribution along the chord waa found very sirdar to that for thin wings, but with a tendency tc)ward greater negative p~es. The characterist.imof the Ioading across the span of the U. S. A. 27 C moditied are inferior to those of the other two wings; in the Iatte.ij the distribution is almost exactly elliptical throughout the usual range of flying angles. The form of tip incorporated in these models is not completely satisfactory end a modifica-tion is recommended