Computational fluid dynamic simulations have been used to study the combustion processes within an axisymmetric, RBCC flowpath. Two distinct operating modes have been analyzed to date, including the independent ramjet stream (IRS) cycle and the supersonic combustion ramjet (scramJet) cycle. The IRS cycle investigation examined the influence of fuel-air ratio, fuel distribution, and rocket chamber pressure upon the combustion physics and thermal choke characteristics. Results indicate that adjustment of the amount and radial distribution of fuel can control the thermal choke point. The secondary massflow rate was very sensitive to the fuel-air ratio and the rocket chamber pressure. The scramjet investigation examined the influence of fuel-air ratio and fuel injection schedule upon combustion performance estimates. An analysis of the mesh-dependence of these calculations was presented. Jet penetration data was extracted from the three-dimensional simulations and compared favorably with experimental correlations of similar flows. Results indicate that combustion efficiency was very sensitive to the fuel schedule.
Computational Analysis of the Combustion Processes in an Axisymmetric, RBCC Flowpath
25th Airbreathing Propulsion Subcommittee
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2000
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Monterey, CA, United States
19th Propulsion Systems Hazards Subcommittee Joint Meeting
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2000
;
Monterey, CA, United States
37th Combustion Subcommittee
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2000
;
Monterey, CA, United States
2001-02-01
Preprint
No indication
English
Performance Evaluation of the NASA GTX RBCC Flowpath
NTRS | 2001
|Performance Evaluation of the NASA GTX RBCC Flowpath
NTIS | 2001
|