Enhancement of the CAVE computer code [PDF]
The computer code CAVE (Conduction Analysis via Eigenvalues) is a convenient and efficient computer code for predicting two dimensional temperature histories within thermal protection systems for hypersonic vehicles.
Burk, H. O., Rathjen, K. A.
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Exploratory study of transient upstart phenomena in a three-dimensional fixed-geometry scramjet engine [PDF]
The structural and thermal design of a hydrogen fueled regeneratively cooled three dimensional fixed geometry scramjet was examined. An exploratory study was conducted at Mach 5.3 in the 7-inch Mach 7 pilot tunnel to investigate the unstart phenomena and
Wieting, A. R.
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Apollo Lightcraft project [PDF]
The detailed design of a beam-powered transatmospheric vehicle, the Apollo Lightcraft, was selected as the project for the design course. The principal goal is to reduce the LEO payload delivery cost by at least three orders of magnitude below the Space ...
Blandino, John S. +9 more
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Active cooling design for scramjet engines using optimization methods [PDF]
A methodology for using optimization in designing metallic cooling jackets for scramjet engines is presented. The optimal design minimizes the required coolant flow rate subject to temperature, mechanical-stress, and thermal-fatigue-life constraints on ...
Lucas, Stephen H. +2 more
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NASP X-30 Propulsion technology status [PDF]
The performance goals of the NASP program require an aero-propulsion system with a high effective specific impulse. In order to achieve these goals, the high potential performance of air-breathing engines must be achieved over a very wide Mach number ...
Powell, William E.
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Subsonic longitudinal aerodynamic characteristics and engine pressure distributions for an aircraft with an integrated scramjet designed for Mach 6 cruise [PDF]
A 1/10-scale model of a proposed hypersonic aircraft with an integrated scramjet was tested. The investigation took place over a Mach number range from 0.2 to 0.7 and an angle of attack range from 2 deg to approximately 17 deg at a sideslip angle of 0 ...
Fox, C. H., Jr. +2 more
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Numerical Analysis of Supersonic Film Cooling in Supersonic Flow in Hypersonic Inlet with Isolator
Advances in Mechanical Engineering, 2014 Supersonic film cooling is an efficient method to cool the engine with extremely high heat load. In order to study supersonic film cooling in a real advanced engine, a two-dimensional model of the hypersonic inlet in a scramjet engine with supersonic ...
Silong Zhang +3 more
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Influence of extruded injector nozzle on fuel mixing and mass diffusion of multi fuel jets in the supersonic cross flow: computational study. [PDF]
Sci Rep, 2023 Abdollahi SA +2 more
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Validation of scramjet exhaust simulation technique at Mach 6 [PDF]
Current design philosophy for hydrogen-fueled, scramjet-powered hypersonic aircraft results in configurations with strong couplings between the engine plume and vehicle aerodynamics.
Hopkins, H. B., Konopka, W., Leng, J.
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Usage of extruded diamond multi-injectors for improvement of fuel mixing inside the supersonic combustion chamber. [PDF]
Sci Rep, 2023 Seraj H +3 more
europepmc +1 more source