Inhibition of flow separation at high speed.
Volume 3,
Experimental results for laminar boundary layers /
Jack N. Nielsen, Larry L. Lynes, Frederick K. Goodwin.
Description
- Language(s)
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English
- Published
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Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Systems Command, United States Air Force, 1969.
- Summary
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The report describes the results of a wind-tunnel test program on an ogive-cylinder-flare combination to determine the extent of laminar separation as a function of wall temperature for fixed free-stream Reynolds number per unit length at a free-stream Mach number of 8.0. The objective of the tests was to see if separation could be eliminated entirely by cooling the wall to a sufficiently low value. Pressure and temperature distributions spanning the separation region were made on a quick-insertion model, but the location of the separation point could not be obtained during the tests. Accordingly, a combined experimental-theoretical method was developed for determining the separation point location. Correlation of the separation length with model temperature ratio indicated that the separation distance was small and was rapidly approaching zero at the lowest wall temperature ratio achieved experimentally. The apparent critical wall temperature ratio so indicated by the data was lower than the theoretical ratio. It was not possible to achieve sufficiently low temperatures to see if separation could be entirely eliminated. Possible reasons for the difference between experiment and theory are discussed.
- Note
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"The work was carried out by Nielsen Engineering & Research, Inc., under Contract No. F33615-67-C-1096. The contract was initiated under Project 8219, Task 821902."
"Nielsen Engineering & Research, Inc."
"March 1968."
- Physical Description
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ix, 51 pages :
illustrations, figures, tables ;
28 cm.
Viewability