The results of tests of six airfoils having the N.A.C.A. 230 mean line and varying in thickness from 0.06c to 0.21c are presented. These results agree with previous findings in showing that aerodynamically the best section is one of moderate thickness. The data are of value mainly in connection with the design of tapered wings having sections based on the N.A.C.A. 230 mean line.
Tests of N.A.C.A. airfoils in the variable-density wind tunnel Series 230.
1936-05-01
Miscellaneous
No indication
English
Tests of N.A.C.A. airfoils in variable-density wind tunnel, series 24
Engineering Index Backfile | 1932
|Tests of N.A.C.A. Airfoils in variable-density wind tunnel
Engineering Index Backfile | 1936
|Tests of N.A.C.A. Airfoils in variable-density wind tunnel, series 4e and 63
Engineering Index Backfile | 1931
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