NASA's Hyper-X research program was developed primarily to flight demonstrate a supersonic combustion ramjet engine, fully integrated with a forebody designed to tailor inlet flow conditions and a free expansion nozzle/afterbody to produce positive thrust at design flight conditions. With a point-designed propulsion system, the vehicle must depend upon some other means for boost to its design flight condition. Clean separation from this initial propulsion system stage within less than a second is critical to the success of the flight. This paper discusses the early planning activity, background, and chronology that developed the series of wind tunnel tests to support multi degree of freedom simulation of the separation process. Representative results from each series of tests are presented and issues and concerns during the process and current status will be highlighted.
Hyper-X Stage Separation Wind Tunnel Test Program
2000
17 pages
Report
No indication
English
Aerodynamics , Supersonic combustion ramjet engines , Stage separation , Propulsion system configurations , Wind tunnel tests , Aircraft structures , Inlet flow , Hypersonic aircraft , Launch vehicle configurations , Research vehicles , Afterbodies , Degrees of freedom , Forebodies , Flight conditions , Aerodynamic characteristics
Hyper-X Stage Separation Wind-Tunnel Test Program
AIAA | 2001
|Hyper-X Stage Separation Wind Tunnel Test Program
NTRS | 2000
|Hyper-X Stage Separation Wind-Tunnel Test Program
NTRS | 2001
|SPECIAL SECTION: HYPER-X - Hyper-X Stage Separation Wind-Tunnel Test Program
Online Contents | 2001
|Hyper-X Storage Separation Wind Tunnel Test Program
NTRS | 2000
|