Low-speed aerodynamic characteristics of airfoil sections with rounded trailing edges in forward and reverse flow /
Low-speed wind-tunnel tests were conducted to determine the two-dimensional aerodynamic characteristics of 6-, 12-, and 18-percent-thick airfoil sections with rounded trailing edges in both forward and reverse flow. The shapes incorporated camber with both the leading and trailing edges rounded to p...
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| Format: | Government Document Book |
| Language: | English |
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Washington, D.C. : Springfield, Va. :
National Aeronautics and Space Administration ; For sale by the National Technical Information Service [distributor],
1974
Washington, D.C. : [Springfield, Va. : National Aeronautics and Space Administration ; For sale by the National Technical Information Service], 1974 |
| Series: | NASA technical memorandum ;
3060 NASA technical memorandum X-3060 |
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| Summary: | Low-speed wind-tunnel tests were conducted to determine the two-dimensional aerodynamic characteristics of 6-, 12-, and 18-percent-thick airfoil sections with rounded trailing edges in both forward and reverse flow. The shapes incorporated camber with both the leading and trailing edges rounded to provide reasonable aerodynamic performance with either edge directed toward the free-stream flow. The tests were conducted with the airfoils in both normal and reverse orientations relative to the free stream. The Mach number was varied from 0.16 to 0.36 and the angle of attack was varied from minus 10 to 24 million. Reynolds number, based on the airfoil chord, was varied from about 1.0 to 12.0 million |
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| Item Description: | Cover title Performing organization report no.: L-9327 Prepared at Langley Research Center This WorldCat-derived record is shareable under Open Data Commons ODC-BY, with attribution to OCLC "NASA TM X-3060." "September 1974." |
| Physical Description: | 102 p. : chiefly ill. ; 27 cm 102 p. : ill. ; 27 cm |
| Bibliography: | Includes bibliographical references (p. 16) |