The Challenge of Modeling High Speed Flows

Current and expected developments in space transportation have led to growing interest in new space vehicles. These new vehicles require essential improvements over current vehicles in order to ensure economic viability and to fullfill mission and safety constraints. The size and complexity of this problem has led to growing importance of numerical methods for design and optimization involving all disciplines as well as the optimal use of all technical potentialities is necessary. The material presented here reviews the growth and advances achieved at DLR in the last years. The Status of the physical modeling, code development issues such as algorithms, grid generation and validation strategy is provided. Viscous, high speed unsteady flows are still restricted to simple problems due to a strong demand in Computer resources. The short coming to obtain adequate data for code validation in high speed flow problems is discussed. It tums out that little progress has been realized in numerical modeling since past major difficulties to obtain reliable experimental data in the high enthalpy flow environments still remain. On the other side, CFD based multidisciplinary analysis is emerging as a key discipline in aerospace design. Supported by a continuous, almost linear, grows in computer capacity and performance, this new procedure to conduct configuration analysis is paying off its way. A number of selected applications of multidisciplinary problems with complex physics are presented.

[1]  Klaus Hannemann,et al.  High Enthalpy Flows in the HEG Shock Tunnel: Experiment and Numerical Rebuilding (Invited) , 2003 .

[2]  J.M.A. Longo,et al.  Aerothermodynamics of the ARD: Postflight Numerics and Shock-Tunnel Experiments , 2002 .

[3]  J.M.A. Longo,et al.  Aerodynamic optimization of re-entry capsules , 2001 .

[4]  Andreas Mack,et al.  Study of the heating of a hypersonic projectile through a multidisciplinary simulation , 2006 .

[5]  Erich Schülein,et al.  Simulation of streamwise vortices at the flaps of re-entry vehicles , 2004 .

[6]  Carl Dankert,et al.  Experimental Investigation and Numerical Simulation on a Missile Radome at Mach 6 , 2007 .

[7]  J.M.A. Longo.  Modelling of Hypersonic Flow Phenomena , 2004 .

[8]  Jose Maria Longo,et al.  Aerothermodynamik und Wiedereintritt , 2007 .

[9]  J.M.A. Longo,et al.  X-38 NASA/DLR/ESA-Dassault Aviation Integrated Aerodynamic and Aerothermodynamic Activities , 1999 .

[10]  Ali Gülhan,et al.  Mars entry simulation in the arc heated facility L2K , 2002 .

[11]  R. Adeli,et al.  Flow Field Study of a Supersonic Jet Exiting into a Supersonic Stream , 2006 .

[12]  Norbert Kroll,et al.  National CFD Project MEGAFLOW , 1997 .

[13]  Klaus Hannemann,et al.  Application of the DLR TAU-Code to the RCM-4 Test Case: Microcombustor Ignition , 2006 .

[14]  Andreas Mack,et al.  Comparison of supersonic combustion tests with shock tunnels, flight and CFD , 2006 .

[15]  O. Bozic,et al.  Aerothermodynamic Aspects of Railgun-Assisted Launches of Projectiles With Sub- and Low-Earth-Orbit Payloads , 2007, IEEE Transactions on Magnetics.

[16]  T. Eggers,et al.  The Effect of Catalycity on the Heating of the X-38 Shape , 1997 .

[17]  Jan Martinez Schramm,et al.  Numerical and Experimental Investigation of a Hypersonic Glider , 2007 .

[18]  M. Haupt,et al.  Waverider Aerodynamics and Preliminary Design for Two-Stage-to-Orbit Missions, Part 1 , 1998 .

[19]  Erich Schülein,et al.  Simulation of Missiles with Grid Fins Using an Actuator Disk , 2006 .

[20]  Ralf Heinrich,et al.  The DLR TAU-Code: Recent Applications in Research and Industry , 2006 .

[21]  Klaus Hannemann,et al.  Application of the DLR TAU-Code to the RCM-1 Test Case: Penn State Preburner Combustor , 2006 .

[22]  Kim Haugbølle,et al.  Proceedings of the 2nd International Symposium , 2003 .

[23]  J.M.A. Longo,et al.  High Enthalpy Testing and CFD Rebuilding of X-38 in HEG , 2001 .

[24]  A. Filimon,et al.  Fluid Structure Interaction at the ARIANE-5 Nozzle section by Advanced Turbulence Models , 2006 .

[25]  J.M.A. Longo,et al.  Considerations on CFD Modeling for the design of re-entry vehicles , 2000 .

[26]  Heinrich Lüdeke,et al.  Simulation of Magnetohydrodynamic Effects on an Ionised Hypersonic Flow by Using the TAU Code , 2007 .

[27]  Jose M. A. Longo,et al.  Shock-Wave-Boundary-Layer Interaction (SWBLI) around open Flaps of EXPERT Capsule and their Consideration on Heat and Mechanical Loads under critical Re-Entry Flow Conditions , 2006 .

[28]  O. Bozic,et al.  Aerodynamic Design and Analysis of an ARIANE 5 Liquid Fly-Back Booster , 2002 .

[29]  Ralf Stark,et al.  Joint European Effort Towards Advanced Rocket Thrust Chamber Technology , 2005 .

[30]  J.M.A. Longo,et al.  X-38: A Testbed for the CEVCATS-N Code , 1999 .

[31]  H. Lüdeke,et al.  Computation of Supersonic Base Flow Using Detached Eddy Simulation , 2007 .

[32]  R. Radespiel,et al.  Comparison of nonequilibrium flows past a simplified Space-Shuttle configuration , 1997 .

[33]  Klaus Hannemann,et al.  Computations of shock wave propagation with local mesh adaptation , 2009 .

[34]  Simon Prince,et al.  Turbulence Model Studies to Investigate the Aerodynamic Performance of a NASA Dual Control Missile at Supersonic Mach Numbers , 2005 .

[35]  Klaus Hannemann,et al.  High Enthalpy Cylinder Flow in HEG: A Basis for CFD Validation , 2003 .

[36]  J. Steelant,et al.  Impact of intake boundary layer turbulence on the combustion behavior in a scramjet , 2009 .

[37]  T. Magin,et al.  Assessment of Radiative Transport in an Argon Plasma Flow , 2002 .

[38]  J.M.A. Longo,et al.  Designing Flight Experiments for Hypersonic Flow Physics , 2005 .

[39]  O. Bozic,et al.  Flow field analysis of a future launcher configuration during start , 2004 .

[40]  Andreas Mack,et al.  Fluid Structure Interaction on a Generic Body-Flap Model in Hypersonic Flow , 2005 .

[41]  Andreas Mack,et al.  CFD Analysis of the HyShot Supersonic Combustion Flight Experiment Configuration , 2006 .

[42]  J.M.A. Longo,et al.  Efficient Numerical Simulation of Complex 3D Flows with Large Contrast , 1995 .

[43]  H. Lüdeke,et al.  Time Accurate Simulation of Turbulent Nozzle Flow by the DLR TAU-Code , 2006 .

[44]  J.M.A. Longo,et al.  Aerothermodynamics - A critical review at DLR , 2003 .

[45]  Th. Eggers,et al.  Design Studies of the JAPHAR Experimental Vehicle for Dual Mode Ramjet Demonstration , 2001 .

[46]  J.M.A. Longo,et al.  Aerothermodynamics for reusable launch systems , 2004 .

[47]  Andreas Mack,et al.  Validation of the Unstructured DLR-TAU-Code for Hypersonic Flows , 2002 .

[48]  Uwe Reisch,et al.  CFD-simulation of the flow through a fluidic element , 2000 .

[49]  Andreas Mack,et al.  Aerothermodynamic behaviour of a generic nosecap model including thermomechanical structural effects , 2007 .