The primary objective of the workshop was to obtain a critical assessment of a concept for a large, advanced hypervelocity ballistic range test facility powered by an electromagnetic launcher, which was proposed by the Langley Research Center. It was concluded that the subject large-scale facility was feasible and would provide the required ground-based capability for performing tests at entry flight conditions (velocity and density) on large, complex, instrumented models. It was also concluded that advances in remote measurement techniques and particularly onboard model instrumentation, light-weight model construction techniques, and model electromagnetic launcher (EML) systems must be made before any commitment for the construction of suc...
On May 16, 1991, the NASA Headquarters Propulsion, Power, and Energy Division and the NASA Lewis Res...
Hypersonic vehicle development is an important problem of current national interest. Many of the key...
Aerodynamic effects on rocket and launch vehicle design, shock tunnel simulation, jet exhaust flow, ...
The discussion, started in Semiannual Status Report Number 1, on aerothermal problems of hyperveloci...
A four month feasibility study of a hypersonic real-gas free flight test facility for NASA Langley R...
A conceptual design of a very large aeroballistic range is presented, as are its operational charact...
Significant aircraft tests which were performed are highlighted. The broad range of the research and...
A review is presented of recent research, development, testing and evaluation activities related to ...
A study was performed to determine the feasibility of testing a large-scale High Speed Civil Transpo...
Description, capabilities, recent upgrades, and utilization of the NASA Langley Research Center (LaR...
Research activity in the aerothermodynamics branch at the NASA Ames Research Center is reviewed. Adv...
Papers presented at the First Annual High Speed Research Workshop held in Williamsburg, Viginia, on ...
This paper provides an overview of NASA's Hyper-X Program; a focused hypersonic technology effort de...
Information on the state of the art in space simulation, test technology, thermal simulation and pro...
Long-range hypervelocity vehicles are studied in terms of their motion in powered flight, and their ...
On May 16, 1991, the NASA Headquarters Propulsion, Power, and Energy Division and the NASA Lewis Res...
Hypersonic vehicle development is an important problem of current national interest. Many of the key...
Aerodynamic effects on rocket and launch vehicle design, shock tunnel simulation, jet exhaust flow, ...
The discussion, started in Semiannual Status Report Number 1, on aerothermal problems of hyperveloci...
A four month feasibility study of a hypersonic real-gas free flight test facility for NASA Langley R...
A conceptual design of a very large aeroballistic range is presented, as are its operational charact...
Significant aircraft tests which were performed are highlighted. The broad range of the research and...
A review is presented of recent research, development, testing and evaluation activities related to ...
A study was performed to determine the feasibility of testing a large-scale High Speed Civil Transpo...
Description, capabilities, recent upgrades, and utilization of the NASA Langley Research Center (LaR...
Research activity in the aerothermodynamics branch at the NASA Ames Research Center is reviewed. Adv...
Papers presented at the First Annual High Speed Research Workshop held in Williamsburg, Viginia, on ...
This paper provides an overview of NASA's Hyper-X Program; a focused hypersonic technology effort de...
Information on the state of the art in space simulation, test technology, thermal simulation and pro...
Long-range hypervelocity vehicles are studied in terms of their motion in powered flight, and their ...
On May 16, 1991, the NASA Headquarters Propulsion, Power, and Energy Division and the NASA Lewis Res...
Hypersonic vehicle development is an important problem of current national interest. Many of the key...
Aerodynamic effects on rocket and launch vehicle design, shock tunnel simulation, jet exhaust flow, ...