exist for all Right conditions. This conclusion marks a A mixing model representative of 3 dimensional HZ t -g Point in computational Ruid dynamics (CFD) fuel injection into a scramjet combustor has been in-in that a vehicle will be designed and Rown based pricorporated into the SAIC scramjet p r o p~i o n pro-marily on numerical computations. For these tools to gram package. The model conserves mass, momen-be they must resolve the important physics yet trim and energy and uses the urpe-entally gen-be computationally efficient to be of use in the design erated Hz mass fraction correlations due to Cohen, Process.Coulter and Egan for closure. Computations pre-A package of computer programs designed to comformed with this pachage have shown that fuel injec-pute the Row field about and through scramjet powtion can increase combustor pressures substantially. ered hypersonic vehicles has been assembled by Science Applications International Corporation (SAIC) Nomenclature and is summarized in references 171 and [SI. The pack-C P k age consists of running a series of 2-D/axisymmetric parabolic Navier Stokes codes about and through a M Mach number. desired hypersonic vehicle. Figure 1 shows the forem Masa Flux. body and inlet region of a typical hypersonic vehicle P Pressure. considered in this study. Note the nose region is com-B Gas Constant. pnted with the VSL code(& [I]), the forebody and T Gas temperature. external cowl region with the SCRAMP code and the U Axial Velocity. inlet region with the SCRINT code. The fuel injecv Normal Velocity. tion region, the combustion region and the nozzle re-Y Cell Normal Spacing. gion are shown in figure 2. The combustor and noz-4, E R Fuel equivalence ratio. ale Rowfields are computed with the SCORCH and P Density. SCHNOZ codes respectively. These codes can only simulate parallel and Z D slot injection. In reality Hz is injected through holes which cannot be realistically represented by slot injectors. Thus the fuel injection model is the weak link in the SAIC nose to tail analysis. The major contribution of this paper is in the development of a fuel injection model which can simulate 3-D Hz fuel injection and therefor better represent real scramjet propulsion system. The procedure for obtaining a complete nose to tail solution can be summarized with the Row chart shown in figure 3. ing problem due to the highly three dimensiond Bowfield created by the injection process. Obstruction of the airflow caused by fuel injection creates a -c/ Coe5cient of heat at constant p r e s sure for species k. Subscripts m Freestream coudition.
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