Ordinates and theoretical pressure-distribution data for NACA 6- and 6A-series airfoil sections with thicknesses from 2 to 21 and from 2 to 15 percent chord, respectively
1961
86 S.
graph. Darst.
Supersedes NACA technical note 4322
Report
Englisch
Pressure distributions and force tests of NACA 65-120 airfoil section with 50-percent-chord flap
Engineering Index Backfile | 1947
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