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Experimental study of nozzle wall boundary layers at Mach numbers 20 to 47 / by Joseph H. Kemp, Jr., and F. Kevin Owen.
- Format:
- Book
- Government document
- Author/Creator:
- Kemp, Joseph H.
- Series:
- NASA technical note ; D-6965.
- NASA technical note ; NASA TN D-6965
- Language:
- English
- Subjects (All):
- Wall pressure (Aerodynamics).
- Jet nozzles.
- Turbulent boundary layer.
- Aerodynamics, Hypersonic.
- Physical Description:
- 1 online resource (vii, 101 pages) : illustrations
- Place of Publication:
- Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va.] : [For sale by the National Technical Information Service], 1972.
- Summary:
- The nozzle wall boundary layer of an M-50 helium tunnel was investigated with pitot pressure, total temperature, skin friction, and wall heat transfer measurements at five stations and hot wire measurements at two stations. The results indicated that the boundary layer was turbulent with a thick viscous sublayer. Pressure gradients were observed across the boundary layer; the effect of these gradients on the equations of motion are discussed. The direct skin friction measurements were higher than expected from empirical predictions; the Reynolds analogy factors however were lower than expected. Hot wire measurements indicated mass flow fluctuations as large as 80 percent of the local mean mass flow at the edge of the viscous sublayer with a maximum value relative to the edge mass flow of about 15 percent at gamma about equal to 0.8.
- Notes:
- Cover title.
- Prepared at Ames Research Center.
- Includes bibliographical references (pages 17-21).
- Other Format:
- Online version: Kemp, Joseph H. Experimental study of nozzle wall boundary layers at Mach numbers 20 to 47.
- OCLC:
- 23014137
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