Effects of compressibility on maximum lift coefficients for six propeller airfoils / by Harold E. Cleary.
An extension of previously reported data on the variation of lift coefficient with Mach number, camber, and thickness ratio is presented. The data were obtained from pressure-distribution tests in the Langley 8-foot high-speed tunnel of six propeller airfoils of 1-foot chord.
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| Corporate Authors: | , |
| Other title: | NACA Wartime Reports. Series L. Technical report archive and image library. |
| Format: | Government Document Book |
| Language: | English |
| Published: |
Washington, D.C. :
National Advisory Committee for Aeronautics,
[1945]
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| Series: | Wartime Reports (United States. National Advisory Committee for Aeronautics) ;
no. L514. |
| Subjects: |
| Summary: | An extension of previously reported data on the variation of lift coefficient with Mach number, camber, and thickness ratio is presented. The data were obtained from pressure-distribution tests in the Langley 8-foot high-speed tunnel of six propeller airfoils of 1-foot chord. |
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| Item Description: | NACA Wartime Report L-514. Originally issued as NACA as Advance Confidential Report L4L21a (January 1945) Prepared at the Langley Memorial Aeronautical Laboratory, Langley Field, Virginia. |
| Physical Description: | 11 pages, 7 unnumbered pages : illustrations ; 27 cm. |
| Bibliography: | Includes bibliographical references. |