INVESTIGATION OF AN AXISYMMETRIC INTERNAL COMPRESSION INLET AT A MACH NUMBER OF ABOUT 3.8
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)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 1961
- Accession Number
- AD0257799
Entities
People
- John H. Lundell
- Lewis A. Anderson
- Richard Scherrer
Organizations
- National Aeronautics and Space Administration