The drag of a simulated scramjet combustion module was measured at Mach 2, 2.5, and 3. The combustor was rectangular in cross section and incorporated six swept fuel injector struts. The effect of strut leading edge radius, position of maximum thickness, thickness ratio, sweep angle, and strut length on the drag was determined. Reduction in thickness ratio had the largest effect on drag reduction. Sweeping the struts upstream yielded the same drag as sweeping the struts downstream and potentially offers the advantages of increased mixing time for the fuel. Helium injection was used to simulate hydrogen fuel. The interstrut spacing required to achieve good distribution of fuel was was found to be about 10 jet diameters. The contribution of h...
© 2020 Hydrogen Energy Publications LLC The efficient fuel mixing in the combustion tank enhances th...
A summary of the research activities is presented along with the design and analysis of an integrate...
The scramjet engine has proven to be a viable means of powering a hypersonic vehicle, especially aft...
The aerodynamic drag and fuel distribution patterns of injectors designed for a supersonic combustio...
Results are presented of an experiment to investigate the behavior at Mach 4 flight conditions of th...
The results are presented of a cold-mixing investigation performed to supply combustor design inform...
Recent design studies have shown that airframe-integrated scramjets should include instream mounted,...
In the operation of a Scramjet engine, which operates at hypersonic velocities, one of the most impo...
An investigation of the combustion of hydrogen perpendicularly injected from step fuel injectors int...
A major problem in supersonic combustion is the short residence time of the fluid inside the combust...
Enhancing the fuel-air mixing is critical for scramjet combustor performance. The performance of fou...
It is desired to maintain supersonic flow through the combustor of supersonic airbreathing engines t...
The NASA Langley Research Center has conducted hypersonic propulsion research since the 1960s. A var...
Reports by the staff of the University of Queensland on various research studies related to the adva...
© 2020 Hydrogen Energy Publications LLC The efficient fuel mixing in the combustion tank enhances th...
© 2020 Hydrogen Energy Publications LLC The efficient fuel mixing in the combustion tank enhances th...
A summary of the research activities is presented along with the design and analysis of an integrate...
The scramjet engine has proven to be a viable means of powering a hypersonic vehicle, especially aft...
The aerodynamic drag and fuel distribution patterns of injectors designed for a supersonic combustio...
Results are presented of an experiment to investigate the behavior at Mach 4 flight conditions of th...
The results are presented of a cold-mixing investigation performed to supply combustor design inform...
Recent design studies have shown that airframe-integrated scramjets should include instream mounted,...
In the operation of a Scramjet engine, which operates at hypersonic velocities, one of the most impo...
An investigation of the combustion of hydrogen perpendicularly injected from step fuel injectors int...
A major problem in supersonic combustion is the short residence time of the fluid inside the combust...
Enhancing the fuel-air mixing is critical for scramjet combustor performance. The performance of fou...
It is desired to maintain supersonic flow through the combustor of supersonic airbreathing engines t...
The NASA Langley Research Center has conducted hypersonic propulsion research since the 1960s. A var...
Reports by the staff of the University of Queensland on various research studies related to the adva...
© 2020 Hydrogen Energy Publications LLC The efficient fuel mixing in the combustion tank enhances th...
© 2020 Hydrogen Energy Publications LLC The efficient fuel mixing in the combustion tank enhances th...
A summary of the research activities is presented along with the design and analysis of an integrate...
The scramjet engine has proven to be a viable means of powering a hypersonic vehicle, especially aft...