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in creator/contributor: "Little, B. H., Jr."  
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Performance and Boundary-Layer Data From 12 Degree and 23 Degree Conical Diffusers of Area Ratio 2.0 at Mach Numbers Up to Choking and Reynolds Numbers Up to 7.5 X 10(6)

Description: "For each of two inlet-boundary-layer thicknesses, performance and boundary-layer characteristics have been determined for a 12 degree, 10-inch-inlet-diameter diffuser, a 12 degree, 21-inch-inlet-diameter diffuser, and a 23 degree, 21-inch-inlet-diameter diffuser. The investigation covered an inlet Mach number range from about 0.10 to coking. The corresponding inlet Reynolds number, based on inlet diameter, varied from about 0.5 x 10(6) to 7.5 x 10(6)" (p. 1013).
Date: November 15, 1954
Creator: Little, B. H., Jr. & Wilbur, Stafford W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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High-Subsonic Performance Characteristics and Boundary-Layer Investigations of a 12 10-Inch-Inlet-Diameter Conical Diffuser

Description: Performance and boundary-layer data were taken in a 12 degree 10-inch inlet-diameter conical diffuser of 2:1 exit- to inlet-area ratio. These data were taken for two inlet-boundary-layer conditions. The first condition was that of a thinner inlet boundary later (boundary-layer displacement thickness, delta* approximately equal to 0.034) produced by an inlet section approximately 1 inlet diameter in length between the entrance bell and the diffuser. The second condition was a thicker inlet bound… more
Date: May 11, 1950
Creator: Little, B. H., Jr. & Wilbur, Stafford W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effects of Combining Auxiliary Bleed With Ejector Pumping on the Power Requirements and Test-Section Flow of an 8-Inch by 8-Inch Slotted Tunnel

Description: Report discussing an investigation to determine the effects of combining auxiliary bleed with ejector pumping on the power requirements and test-section flow of an 8-inch by 8-inch slotted tunnel. Two ejector configurations were used and tests were performed at Mach number range of 0.9 to 1.3. Information about the region of supersonic-flow deceleration, diffuser-inlet Mach numbers, total-power requirements, and which ejector characteristics were preferred is provided .
Date: July 19, 1955
Creator: Little, B. H., Jr. & Cubbage, James M., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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