Advanced Hypersonic Test Facilities, Volume 198
Frank K. Lu, Dan E. Marren
American Institute of Aeronautics and Astronautics, Jan 1, 2002 - Science - 639 pages
The recent interest in hypersonics has energized researchers, engineers, and scientists working in the field, and has brought into focus once again the need for adequate ground test capabilities to aid in the understanding of the complex physical phenomenon that accompany high-speed flight. Over the past decade, there have been noteworthy improvements in the worldwide hypersonic ground testing infrastructure that will be important in furthering hypersonic technologies.
The current inventory of hypersonic testing facilities has been very successful, with few major failures or problems. Many of the enhancements highlighted have been driven by requirements for quiet tunnels for hypersonic boundary layer transition; long run times, high dynamic pressure, nearly clean air, true enthalpy, and larger sized facilities for hypersonic and hypervelocity air breathers; and longer run times, high dynamic pressure/enthalpy facilities for sensor and maneuverability issues associated with interceptors.
Timing is critical for new facility development, since one to two decades for research, design, development, construction, and calibration are needed. Experience shows that capability should be in place before a project that requires the new facility capability is started.
This book presents a number of new, innovative approaches to satisfying the enthalpy requirements for air-breathing hypersonic vehicles and planetary entry problems. It is divided into five parts: Introduction; Hypersonic Shock Tunnels; Long Duration Hypersonic Facilities; Ballistic Ranges, Sleds, and Tracks; and Advanced Technologies for Next Generation Facilities.
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AEDC aerodynamic aerothermal aerothermodynamic AIAA Paper approximately arc heater arc-heated boundary layer Boundary layer transition chemical combustion combustor compression computed configuration density detonation driver detonation wave diameter diaphragm dissociation driven section driver gas dynamic engine enthalpy experimental flight conditions flowfield ground test guideway heat flux heat transfer helium high-enthalpy high-pressure hydrogen hypersonic test Hypersonic Wind Tunnel hypervelocity HYPULSE increase initial inlet interaction ISBN km/s launch launcher Mach number measured NASA nitrogen nonequilibrium nozzle nozzle exit operation parameters performance piston Pitot pressure plasma propulsion real gas reentry Research reservoir Reynolds numbers SCIROCCO scramjet seekerhead settling chamber shock tube shock tunnel shockwave shown in Fig simulation stagnation point stagnation pressure supersonic surface techniques Technology temperature test article test capability test facilities test gas test section thermal thermocouple Tunnel 9 vehicle velocity wind tunnel