Wind-tunnel tests were conducted to determine the low-speed section characteristics of a 13-percent-thick airfoil designed for general aviation applications. The results are compared with NACA 12-percent-thick sections and with the 17-percent-thick NASA airfoil. The tests are conducted over a Mach number range from 0.10 to 0.35. Chord Reynolds numbers vary from about 2 million to 9 million. (Author)
Low-Speed Aerodynamic Characteristics of a 13-Percent Thick Airfoil Section Designed for General Aviation Applications
1975
57 pages
Report
Keine Angabe
Englisch