Accession Number:

AD0257799

Title:

INVESTIGATION OF AN AXISYMMETRIC INTERNAL COMPRESSION INLET AT A MACH NUMBER OF ABOUT 3.8

Descriptive Note:

Corporate Author:

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON D C

Report Date:

1961-06-01

Pagination or Media Count:

1.0

Abstract:

An idealized axisymmetric, all-internal compression inlet was designed for a Mach number of 3.75. The objective of the design was to obtain a steady, one-dimensional transonic flow and a high over-all total-pressure recovery. Boundary-layer removal was employed in the vicinity of the inflection point of the supersonic contour. Static- and total-pressure fluctuations were measured in the transonic flow region. A total-pressure recovery of about 90 percent was obtained with a boundary-layerremoval mass-flow rate of 15 percent of the inlet mass-flow rate. The accompanying root-meansquare total-pressure fluctuation in the throat region was only 1 percent of the free-stream total pressure. The test Mach number was 3.80 and the Reynolds number based on inlet diameter was 2.63 times 10 to the 6th power. Author

Subject Categories:

Distribution Statement:

APPROVED FOR PUBLIC RELEASE