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The effect of rate of change of angle of attack on the maximum lift coefficient of a pursuit airplane
- Author / Creator
- Available as
- Online
- Summary
-
Flight tests have been made with a pursuit airplane to determine the effect of Mach and Reynolds numbers on the variation of the rate of change of maximum lift coefficient with rate of change of th...
Flight tests have been made with a pursuit airplane to determine the effect of Mach and Reynolds numbers on the variation of the rate of change of maximum lift coefficient with rate of change of the angle of attack. These tests have indicated that the rate of increase of maximum lift coefficient with increasing abruptness of the stall is significantly affected by Reynolds number as well as Mach number. Both parameters reduce this rate of increase over the lower ranges tested and increase it in the higher ranges.
Details
- Creator
- by Burnett L. Gadeberg
- Included Title
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- Technical Report Archive & Image Library (TRAIL)
- Format
- Books
- Language
- English
- Publication
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- Washington, D.C. : National Advisory Committee for Aeronautics, 1951
- Physical Details
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- 1 online resource (17 pages) : illustrations, photographs
- data file
- OCLC
- on1343851017
- "Ames Aeronautical Laboratory."
- Title from title screen (viewed August 31, 2022)
- Date of issue: October 1951.
- Report numbers NACA-TN-2525.
- Includes bibliographical references (page 7)
- Electronic reproduction. Denton, Texas : University of North Texas, 2011. Electronic reproduction from print master produced by University of North Texas.