Toward Supersonic Retropropulsion CFD Validation

This paper begins the process of verifying and validating computational fluid dynamics (CFD) codes for supersonic retropropulsive flows. Four CFD codes (DPLR, FUN3D, OVERFLOW, and US3D) are used to perform various numerical and physical modeling studies toward the goal of comparing predictions with a wind tunnel experiment specifically designed to support CFD validation. Numerical studies run the gamut in rigor from code-to-code comparisons to observed order-of-accuracy tests. Results indicate that this complex flowfield, involving time-dependent shocks and vortex shedding, design order of accuracy is not clearly evident. Also explored is the extent of physical modeling necessary to predict the salient flowfield features found in high-speed Schlieren images and surface pressure measurements taken during the validation experiment. Physical modeling studies include geometric items such as wind tunnel wall and sting mount interference, as well as turbulence modeling that ranges from a RANS (Reynolds-Averaged Navier-Stokes) 2-equation model to DES (Detached Eddy Simulation) models. These studies indicate that tunnel wall interference is minimal for the cases investigated; model mounting hardware effects are confined to the aft end of the model; and sparse grid resolution and turbulence modeling can damp or entirely dissipate the unsteadiness of this self-excited flow.

[1]  Jack R. Edwards,et al.  A low-diffusion flux-splitting scheme for Navier-Stokes calculations , 1995 .

[2]  David J. Kinney,et al.  Overview of the NASA Entry, Descent and Landing Systems Analysis Study , 2010 .

[3]  P. O. Jarvinen,et al.  The aerodynamic characteristics of large angled cones with retrorockets , 1970 .

[4]  Yildirim Suzen,et al.  Investigation of Supersonic Jet Exhaust Flow by One-and Two-Equation Turbulence Models , 1998 .

[5]  J.R. Cruz,et al.  A Survey of Supersonic Retropropulsion Technology for Mars Entry, Descent, and Landing , 2008, 2008 IEEE Aerospace Conference.

[6]  B. V. Leer,et al.  Towards the ultimate conservative difference scheme V. A second-order sequel to Godunov's method , 1979 .

[7]  Ten-See Wang,et al.  Dynamics of Shock Dispersion and Interactions in Supersonic Freestreams with Counterflowing Jets , 2009 .

[8]  Boris Diskin,et al.  Towards Verification of Unstructured-Grid Solvers , 2008 .

[9]  P. Spalart,et al.  A New Version of Detached-eddy Simulation, Resistant to Ambiguous Grid Densities , 2006 .

[10]  Robert H. Nichols,et al.  Addition of Improved Shock-Capturing Schemes to OVERFLOW 2.1 , 2009 .

[11]  David P. Lockard,et al.  Re-evaluation of an Optimized Second Order Backward Difference (BDF2OPT) Scheme for Unsteady Flow Applications , 2010 .

[12]  P. Spalart.  A One-Equation Turbulence Model for Aerodynamic Flows , 1992 .

[13]  G. D. van Albada,et al.  A comparative study of computational methods in cosmic gas dynamics , 1982 .

[14]  D. Wilcox.  Formulation of the k-w Turbulence Model Revisited , 2008 .

[15]  R. Manning,et al.  Mars exploration entry, descent and landing challenges , 2006, 2006 IEEE Aerospace Conference.

[16]  Karl T. Edquist,et al.  Analysis of Navier-Stokes codes applied to Supersonic Retro-Propulsion wind tunnel test , 2011, 2011 Aerospace Conference.

[17]  H. C. Yee,et al.  A class of high resolution explicit and implicit shock-capturing methods , 1989 .

[18]  Michael J. Aftosmis,et al.  Parametric Study of Peripheral Nozzle Configurations for Supersonic Retropropulsion , 2010 .

[19]  Christopher J. Roy,et al.  Review of code and solution verification procedures for computational simulation , 2005 .

[20]  W. J. Monta,et al.  Description and calibration of the Langley unitary plan wind tunnel , 1981 .

[21]  Graham V. Candler,et al.  Development of a hybrid unstructured implicit solver for the simulation of reacting flows over complex geometries , 2004 .

[22]  Christopher J. Roy,et al.  Verification and Validation in Scientific Computing: Design and execution of validation experiments , 2010 .

[23]  Robert D. Braun,et al.  High Mass Mars Entry, Descent, and Landing Architecture Assessment , 2009 .

[24]  Suresh Menon,et al.  The compressible hybrid RANS/LES formulation using an additive operator , 2009, J. Comput. Phys..

[25]  Robert D. Braun,et al.  Comparison of Inviscid and Viscous Aerodynamic Predictions of Supersonic Retropropulsion Flowfields , 2010 .

[26]  Leslie A. Yates.  Interferograms, Schlieren, and Shadowgraphs Constructed from Real- and Ideal-Gas, Two- and Three-Dimensional Computed Flowfields , 1992 .

[27]  Robert H. Nichols,et al.  Solver and Turbulence Model Upgrades to OVERFLOW 2 for Unsteady and High-Speed Applications , 2006 .

[28]  William L. Oberkampf,et al.  Experimental methodology for computational fluid dynamics code validation , 1997 .

[29]  Robert D. Braun,et al.  CFD verification of supersonic retropropulsion for a central and peripheral configuration , 2011, 2011 Aerospace Conference.

[30]  W. K. Anderson,et al.  Implicit/Multigrid Algorithms for Incompressible Turbulent Flows on Unstructured Grids , 1995 .

[31]  Florian,et al.  Improved Two-Equation k- Turbulence Models for Aerodynamic Flows , 2022 .

[32]  Graham V. Candler,et al.  A parallel unstructured implicit solver for hypersonic reacting flow simulation , 2005 .

[33]  W. K. Anderson,et al.  An implicit upwind algorithm for computing turbulent flows on unstructured grids , 1994 .

[34]  F. Menter.  Two-equation eddy-viscosity turbulence models for engineering applications , 1994 .

[35]  Christopher J. Roy,et al.  Grid Convergence Error Analysis for Mixed-Order Numerical Schemes , 2001 .

[36]  P. Spalart.  Comments on the feasibility of LES for wings, and on a hybrid RANS/LES approach , 1997 .

[37]  Ten-See Wang,et al.  Numerical Study of Flow Augmented Thermal Management for Entry and Re-Entry Environments , 2007 .

[38]  Scott A. Berry,et al.  Supersonic Retropropulsion Experimental Results from the NASA Langley Unitary Plan Wind Tunnel , 2011 .

[39]  D. L. Young,et al.  A novel immersed boundary procedure for flow and heat simulations with moving boundary , 2009 .

[40]  Graham V. Candler,et al.  The solution of the Navier-Stokes equations using Gauss-Seidel line relaxation , 1989 .

[41]  David P. Lockard,et al.  Assessment of Hybrid RANS/LES Turbulence Models for Aeroacoustics Applications , 2010 .

[42]  Scott A. Berry,et al.  Supersonic retro-propulsion experimental design for computational fluid dynamics model validation , 2011, 2011 Aerospace Conference.

[43]  Michael J. Aftosmis,et al.  Analysis of Inviscid Simulations for the Study of Supersonic Retropropulsion , 2011 .

[44]  Kerry Trumble.  An Initial Assessment of Navier-Stokes Codes Applied to Supersonic Retro-Propulsion , 2010 .

[45]  Boris Diskin,et al.  Towards Verification of Unstructured-Grid Solvers , 2008 .

[46]  Ravi Prakash,et al.  Development of Supersonic Retro-Propulsion for Future Mars Entry, Descent, and Landing Systems , 2010 .