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The NASA Langley Research Center plans to cany out realistic full-scale tests of supersonic combustion ramjet engines at its 8-Foot High Temperature Tunnel (HTT). Consisting mainly of a shower-head type fuel injector (spray bar), the burner and combustion chamber of the tunnel provides the energy needed to attain high-temperature air flows ranging from 1300 to 3000 K and Mach numbers of 4 to 7 at the test section. Required high-temperature fields are generated during the combustion process in a Liquid Oxygen (Lox) Mode environment where air is enriched to about 47 percent by mass in oxygen concentration. The main objectives of this paper are to determine the most important parameters to enable computation of thermal stresses, heat-transfer coefficients, and convective temperatures on the spray bar. In order to compute heattransfer coefficients, NASA will utilize the FLUENT computer code along with well-known empirical methods such as Churchill, Bernstein and Petukhov.