CFD Capabilities for Hypersonic Scramjet Propulsive Flowpath Design

This paper discusses the status of our CFD capabilities for scramjet flow path analysis and design, as well as key enabling technologies that enhance accuracy and efficiency. A scramjet engine flow path encompasses some of the most complex aero-propulsive physics including; laminar to turbulent flow transition, complex shock interactions, and multi-species reacting chemistry. Through the judicious use of advanced modeling and adaptive procedures to ensure adequate resolution, CFD can now predict the performance characteristics of proposed engine designs. Several enhancements to the baseline modeling approach are presented and their influence is demonstrated on unit problems representative of scramjet flow paths. Nomenclature Pr t = Turbulent Prandtl Number Sc t = Turbulent Schmidt Number Le = Lewis Number, Pr t /Sc t Re θ = Reynolds Number based on momentum boundary layer thickness M = Mach Number k,ε = Turbulent kinetic energy, turbulent dissipation rate T w = Temperature of wall PDE = Partial differential equation

[1]  D. C. Kenzakowski,et al.  Extensions Of A Rapid Engineering Approach To Modeling Hypersonic Laminar To Turbulent Transitional Flows , 2005 .

[2]  D. Kenzakowski,et al.  Progress in Practical Scalar Fluctuation Modeling for High- Speed Aeropropulsive Flows * , 2005 .

[3]  Peter A. Cavallo,et al.  PARALLEL UNSTRUCTURED MESH ADAPTATION FOR TRANSIENT MOVING BODY AND AEROPROPULSIVE APPLICATIONS , 2004 .

[4]  W. Calhoon,et al.  HEAT RELEASE AND COMPRESSIBILITY EFFECTS ON PLANAR SHEAR LAYER DEVELOPMENT , 2003 .

[5]  D. Kenzakowski,et al.  Calibration and validation of EASM turbulence model for jet flowfields , 2002 .

[6]  Ronald J. Ungewitter,et al.  High fidelity design oriented scramjet propulsive flowpath analysis , 2001 .

[7]  T. B. Gatski,et al.  Nonlinear eddy viscosity and algebraic stress models for solving complex turbulent flows , 2000 .

[8]  Ashvin Hosangadi,et al.  Design-oriented analysis of scramjet combustor flowfield using combined UNS/PNS procedure , 2000 .

[9]  Peter A. Cavallo,et al.  Missile flowfield modeling advances and data comparisons , 2000 .

[10]  D. Kenzakowski,et al.  Scalar Variance Transport in the Turbulence Modeling of Propulsive Jets , 1999 .

[11]  Scott D. Stouffer,et al.  Study of a Supersonic Combustor Employing Swept Ramp Fuel Injectors , 1997 .

[12]  Ashvin Hosangadi,et al.  Upwind unstructured scheme for three-dimensional combusting flows , 1996 .

[13]  R. M. C. So,et al.  A near-wall two-equation model for turbulent heat fluxes , 1992 .

[14]  Yasutaka Nagano,et al.  A Two-Equation Model for Heat Transport in Wall Turbulent Shear Flows , 1988 .

[15]  A. Martellucci,et al.  Boundary layer transition flight test observations , 1977 .

[16]  V. Ahuja,et al.  Shape Optimization of Multi-Element Airfoils Using Evolutionary Algorithms and Hybrid Unstructured Framework , 2004 .

[17]  Lance Jacobsen,et al.  Comparison of Planar and Axisymmetric Flowpaths for Hydrogen Fueled Space Access Vehicles (Invited) , 2003 .

[18]  R. M. C. So,et al.  Near-wall variable-Prandtl-number turbulence model for compressible flows , 1993 .