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Low-speed Aerodynamic Characteristics of a 17-percent-thick Medium Speed Airfoil Designed for General Aviation Applications
Robert J. McGhee
出版National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1980
URLhttp://books.google.com.hk/books?id=tvUQAQAAIAAJ&hl=&source=gbs_api
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註釋Wind tunnel tests were conducted to determine the low speed two dimensional aerodynamic characteristics of a 17 percent thick medium speed airfoil (MS(1)-0317) designed for general aviation applications. The results were compared with data for the 17 percent thick low speed airfoil (LS(1)-0417) and the 13 percent thick medium speed airfoil (MS(1)-0313). Theoretical predictions of the drag rise characteristics of this airfoil are also provided. The tests were conducted in the Langley low turbulence pressure tunnel over a Mach number range from 0.10 to 0.32, a chord Reynolds number range from 2 million to 12 million, and an angle of attack range from about -8 to 20 deg.