Effect of Mach number on position error as applied to a pitot-static tube located 0.55 chord ahead of an airplane wing / by W.F. Lindsey.
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| Corporate Authors: | , |
| Other title: | NACA Wartime Reports. Series L. |
| Format: | Government Document Book |
| Language: | English |
| Published: |
Washington, D.C. :
National Advisory Committee for Aeronautics,
[1944]
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| Series: | Wartime Reports (United States. National Advisory Committee for Aeronautics) ;
no. L75. |
| Subjects: |
| Abstract: | The effect on static-pressure measurements of locating a pitot-static tube 0.55 chord ahead of an airfoil section has been investigated. The tests were conducted in the NACA 24-inch high-speed tunnel on airfoil sections of various thickness ratios over a large range of Mach number. The results show that for a wing having a thickness ratio of 0.15 the measured Mach number, determined from a pitot-static-tube reading, is approximately 0.01 too low at a stream Mach number of 0.4 and approximately 0.03 too low at a Mach number of 0.8. |
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| Item Description: | NACA Wartime Report L-75. Originally issued as NACA as Confidential Bulletin L4E29 (May 1944) Prepared at the Langley Memorial Aeronautical Laboratory, Langley Field, Virginia. |
| Physical Description: | 5 pages, 5 unnumbered pages : illustrations ; 27 cm. |
| Bibliography: | Includes bibliographical references. |