Systematic Airfoil Tests in the Large Wind Tunnel of the DVL (1938)
NASA Technical Reports Server (NTRS) · leaf 13
N.A.C.A. Technical Memorandum Ho. 852 Figs. 1,6,7,8,9 Figure 6.- Dimensions of experimental split flap. Airfoil of < Figure 1, : m span and in the 5x 7 m 0.8 m chord L. tunnel of the D.V, wind (L t-H CD O 03 ^ F … Wing chord for 100 km/h , landing speed. Figure 8.- ca^x of N.A.C.A. airfoil series 0009 to 0021 with split flap. Figure 9.- Camax of N.A.C.A. airfoil Beriee 23009 to 23018 with split , r / J m ? Wing chord for 100 km/h , landing speed. flap.
NASA Technical Reports Server (NTRS)
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