Wind Tunnel Tests of a Two-Thirds Scale NASA HRE Inlet at Mach Numbers 4, 5, 6, and 8
Abstract
An axisymmetric, variable geometry, two-thirds scale model of a NASA Hypersonic Research Engine (HRE) inlet was tested at Mach numbers 4, 5, 6, and 8. Surface pressures and temperatures were measured on the inlet centerbody and inside the cowl. Pitot pressure measurements were made at four stations along the internal passage. The measurements were obtained for various cowl positions at free-stream Reynolds numbers from 1.08 to 5.76 million (based on a 12-in. cowl diameter) and over an angle-of-attack range from -5 to +5 deg. The model walls were internally cooled and maintained at a minimum frost-free condition at each test condition. Selected results are presented to illustrate the effects of cowl position, angle of attack, Mach number, and Reynolds number on the surface and rake station measurements. Inlet performance data at design operating conditions are also presented.
Document Details
- Document Type
- Technical Report
- Publication Date
- Feb 01, 1969
- Accession Number
- AD0395666
Entities
People
- Frederick K. Hube
- Paul J. Bontrager
Organizations
- Arnold Engineering Development Complex