This investigation is an extension of NACA report no. 75 for the purpose of studying the effect of various modifications in a given wing section, including changes in thickness, height of lower camber, taper in thickness, and taper in plan form with special reference to the development of thick, efficient airfoils. The method consisted in testing the wings in the NACA 5-foot wind tunnel at speeds up to 50 meters (164 feet) per second while they were being supported on a new type of wire balance. Some of the airfoils developed showed results of great promise. For example, one wing (no. 81) with a thickness in the center of 4.5 times that of the U. S. A. 16 showed both uniformly high efficiency and a higher maximum lift than this excellent section. These thick sections will be especially useful on airplanes with cantilever construction. (author)
Aerodynamic properties of thick airfoils II
1923-01-01
Miscellaneous
No indication
English
Aerodynamic Performance of Thick Blunt Trailing Edge Airfoils
British Library Conference Proceedings | 2010
|Aerodynamic characteristics of airfoils
Engineering Index Backfile | 1924
Aerodynamic characteristics of airfoils
Engineering Index Backfile | 1928
Aerodynamic and Aeroacoustic Properties of Flatback Airfoils
British Library Conference Proceedings | 2008
|