High Altitude Maneuver Control Tests in the NSWC (Naval Surface Weapons Center) Hypervelocity Wind Tunnel
Abstract
Pressure tests were conducted in the NSWC Hypervelocity Wind Tunnel to obtain aerodynamic data on high-performance missile interceptor vehicles which are controlled by large jets issuing laterally from the vehicle. Reproduction of flight Reynolds number was of particular interest since for large lateral jets extensive separation can occur. The tests were conducted at nominal Reynolds numbers of 2.0, and 3.2 and 4.6 million per ft., and at Mach numbers of 10 and 14. Model orientations included angles of attack from -15 to +15 deg. and vehicle roll angles of 0, 45 and 90 deg. The tests provided surface pressure distributions over the 112 orifice locations and shock shapes and separation data from the Schlieren photographs. These results constitute an advancement over past tests and provide guidance in calculating jet penetration, jet spreading and separation on high-altitude maneuver control vehicles and in calculating 3-D effects of jets on surface pressure.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 01, 1983
- Accession Number
- ADA136105
Entities
People
- Benito D. Prats
- Jacques A. Hill
- Michael A. Metzger
Organizations
- Naval Ordnance Laboratory