Wind tunnel tests were conducted to determine the effects of airfoil thickness-ratio on the low speed aerodynamic characteristics of an initial family of airfoils. The results were compared with theoretical predictions obtained from a subsonic viscous method. The tests were conducted over a Mach number range from 0.10 to 0.28. Chord Reynolds numbers varied from about 2.0 x 1 million to 9.0 x 1 million.
Effects of Thickness on the Aerodynamic Characteristics of an Initial Low-Speed Family of Airfoils for General Aviation Applications
1976
51 pages
Report
Keine Angabe
Englisch
Studies of a new family of general aviation airfoils
AIAA | 1976
|Aerodynamic characteristics of airfoils
Engineering Index Backfile | 1929
Aerodynamic characteristics of airfoils
Engineering Index Backfile | 1926
Aerodynamic characteristics of airfoils
Engineering Index Backfile | 1924