Effectiveness at High Subsonic Mach Numbers of 20-Percent-Chord Plain Trailing-Edge Flap on NACA 65-210 Airfoil Section.
Effectiveness at high subsonic mach numbers of 20-percent-chord plain trailing-edge flap on NACA 65-210 airfoil section
NACA -- Tech Note
1954
15 pages
Report
Englisch
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Engineering Index Backfile | 1954
|Engineering Index Backfile | 1947
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