A hypersonic airbreathing missile using dual mode scramjet engines for propulsion is described. The fuselage is constructed of a material with a high heat sink capacity and is covered with a thermal protective shield and lined with an internal insulating blanket. The engine airframe integration uses the flat lower portion of the lower fuselage to precompress the air entering the scramjet engines. The precompression of air entering the scramjet inlets increases as the angles of attack. This feature results in a highly maneuverable missile which can accelerate as it banks into a turn
A supersonic combustion rocket is provided in which a small rocket motor is substituted for heavy tu...
A summary of the research activities is presented along with the design and analysis of an integrate...
Instrumentation developments are reported for thrust measurement, gas sampling, temperature measurem...
A conceptual design study of a scramjet engine was conducted for a hypersonic surface to air missile...
Recent interest in airbreathing hypersonic flight has centered around the need to develop advanced s...
Engine-nozzle airframe integration at hypersonic speeds was conducted by using a high-speed research...
This paper provides an overview of NASA's Hyper-X Program; a focused hypersonic technology effort de...
Results from an investigation of the effects of the operation of a combined turbojet/scramjet propul...
Hypersonic air-breathing propulsion utilizing scramjets can fundamentally change transatmospheric ac...
The conclusion evolved from the three phased study on the configuration development of the X-24C Hyp...
An inviscid technique for designing forebodies which produce uniformly precompressed flows at the in...
The goal of the Hyper-X research program, conducted jointly by the NASA Dryden Flight Research Cente...
This paper provides an overview of NASA's focused hypersonic technology program, called the Hyper-X ...
active supersonic combustion ramjet (scramjet) research program since the early days of the formatio...
Research programs at the NASA Langley Research Center on the development of airframe-integrated scra...
A supersonic combustion rocket is provided in which a small rocket motor is substituted for heavy tu...
A summary of the research activities is presented along with the design and analysis of an integrate...
Instrumentation developments are reported for thrust measurement, gas sampling, temperature measurem...
A conceptual design study of a scramjet engine was conducted for a hypersonic surface to air missile...
Recent interest in airbreathing hypersonic flight has centered around the need to develop advanced s...
Engine-nozzle airframe integration at hypersonic speeds was conducted by using a high-speed research...
This paper provides an overview of NASA's Hyper-X Program; a focused hypersonic technology effort de...
Results from an investigation of the effects of the operation of a combined turbojet/scramjet propul...
Hypersonic air-breathing propulsion utilizing scramjets can fundamentally change transatmospheric ac...
The conclusion evolved from the three phased study on the configuration development of the X-24C Hyp...
An inviscid technique for designing forebodies which produce uniformly precompressed flows at the in...
The goal of the Hyper-X research program, conducted jointly by the NASA Dryden Flight Research Cente...
This paper provides an overview of NASA's focused hypersonic technology program, called the Hyper-X ...
active supersonic combustion ramjet (scramjet) research program since the early days of the formatio...
Research programs at the NASA Langley Research Center on the development of airframe-integrated scra...
A supersonic combustion rocket is provided in which a small rocket motor is substituted for heavy tu...
A summary of the research activities is presented along with the design and analysis of an integrate...
Instrumentation developments are reported for thrust measurement, gas sampling, temperature measurem...