Mean camber lines identical for six airfoils and of such form that max mean camber is 2% of chord and is at position 0.4 of chord behind leading edge; airfoils differ in thickness only, max thickness per chord ratios being 0.06, 0.09, 0.12, 0.15, 0.18 and 0.21.
Tests of N.A.C.A. airfoils in variable-density wind tunnel, series 24
Nat Advisory Committee Aeronautics -- Tech Notes
1932
19 pages
14 Supp plates
Report
English
© Metadata Copyright Elsevier B. V. All rights reserved.
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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