Results of tests of new wing section, N A C A 23012, at Reynolds numbers between 1,000,000 and 8,000,000; new airfoil develops reasonably high maximum lift and low profile drag, resulting in unusually high value of speed-range index; pitching-moment coefficient is very small. (Price 5¢)
Characteristics of N.A.C.A. 23012 airfoil from tests in full-scale and variable-density tunnels
Nat Advisory Committee Aeronautics -- Report
1935
10 pages
Bibliography
Report
Englisch
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Pressure distribution over N.A.C.A. 23012 airfoil with N.A.C.A. 23012 external-airfoil flap
Engineering Index Backfile | 1938
|Pressure distribution over N.A.C.A. 23012 airfoil with N.A.C.A. 23012 external-airfoil flap
Engineering Index Backfile | 1938
|Pressure distribution over N.A.C.A. 23012 airfoil with N.A.C.A. 23012 external-airfoil flap
Engineering Index Backfile | 1938
|