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
English
© Metadata Copyright Elsevier B. V. All rights reserved.