TESTS OF ONE-THIRD-SCALE NASA HYPERSONIC RESEARCH ENGINE INLET AT MACH NUMBERS 6 AND 8
Abstract
An axisymmetric, variable geometry, hypersonic inlet was tested at Mach numbers 6 and 8 as a preliminary step in the development of the NASA hypersonic Research Engine (HRE). Surface pressure measurements on the inlet centerbody and inside the cowl and pitot pressure measurements at two stations along the internal passage were made. The measurements were obtained at various centerbody positions, free-stream Reynolds numbers from 970,000 to 2,500,000, based on the 6-in. cowl diameter, and over an angle-of-attack range from -6 to +6 deg. Selected results are presented to illustrate the effects of centerbody position, angle of attack, Mach number, and Reynolds number on the surface and pitot pressure distributions.
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 1968
- Accession Number
- AD0388036
Entities
People
- Frederick K. Hube
Organizations
- Arnold Engineering Development Complex