| Preface | 6 |
|---|
| Contents | 8 |
|---|
| Part I Reduction of SimulationTime | 11 |
|---|
| Recent Developments of TAU Adaptation Capability | 12 |
| Introduction | 12 |
| TAU-Code Adaptation Overview | 13 |
| Grid Refinement Algorithm | 14 |
| Edge-Indicator Sensor Functions | 14 |
| Target Point Number Iteration | 15 |
| Recent Algorithmic Devolpments | 16 |
| Results | 16 |
| Target Functional-Based Mesh Adaption | 18 |
| Mathematical Background | 18 |
| Implementation in the DLR TAU Code | 21 |
| Results | 23 |
| Conclusion | 26 |
| References | 27 |
| Adaptive Wall Function for the Prediction of Turbulent Flows | 29 |
| Motivation | 29 |
| Formulation and Implementation | 30 |
| High-Reynolds Boundary Condition | 31 |
| Hybrid Adaptive Boundary Condition | 32 |
| Validation | 33 |
| Transonic Airfoil Flow: RAE 2822 Case 9 | 33 |
| Transonic Wing Flow: ONERA M6 | 35 |
| Industrial Conditions | 36 |
| Conclusion | 40 |
| References | 41 |
| Acceleration of CFD Processes for Transport Aircraft | 42 |
| Introduction | 42 |
| Overview | 42 |
| Utilization of Improved Code Features | 43 |
| Automatization of Numerical Process Chain | 45 |
| Simultaneous Approach | 46 |
| Summary/Conclusions | 47 |
| References | 47 |
| Efficient Combat Aircraft Simulations with the TAU RANS Code | 48 |
| Background | 48 |
| Objectives | 50 |
| TAU Code Efficiency Improvements | 50 |
| Polar Simulations for High Angle-of-Attack Cases | 54 |
| Conclusions | 59 |
| References | 59 |
| Part II Improvement of Simulation Quality | 60 |
|---|
| Universal Wall Functions for Aerodynamic Flows: Turbulence Model Consistent Design, Potential and Limitations | 61 |
| Introduction | 61 |
| Compressible RANS Equations | 62 |
| Turbulence Model Consistent Universal Wall Functions | 63 |
| Wall Function Formulation | 64 |
| Boundary-Layer Approximation for Universal Wall Functions | 65 |
| Model-Consistency of Universal Wall Functions and Grid-Independent Predictions | 65 |
| Flat Plate Turbulent Boundary Layer at Zero Pressure Gradient | 67 |
| Near-Wall Behaviour of RANS Models in Situations of Non-equilibrium Flow | 68 |
| NumericalMethod | 69 |
| Validation for Aerodynamic Flows | 70 |
| Transonic Airfoil Flows RAE-2822 Cases 9 and 10 | 70 |
| Subsonic A-Airfoil in Highlift Configuration | 72 |
| Application to 3D Testcases | 73 |
| Combination of Wall-Functions and y+-Adaptation | 74 |
| Best Practice Guidelines | 75 |
| Conclusions | 75 |
| References | 76 |
| Computational Modelling of Transonic Aerodynamic Flows Using Near-Wall, Reynolds Stress Transport Models | 78 |
| Introduction | 78 |
| Computational Method | 80 |
| Turbulence Modelling | 81 |
| Numerical Method | 86 |
| Results and Discussion | 87 |
| RAE2822 | 88 |
| ONERA M6 Wing | 90 |
| DLR-ALVAST | 93 |
| Numerical Issues | 95 |
| Results and Discussion | 95 |
| References | 96 |
| Transition Prediction for Three-Dimensional Configurations | 98 |
| Introduction | 98 |
| Description of Methods | 99 |
| Linear Stability Theory | 99 |
| Numerical Methods | 99 |
| Implementation and Parallelization Issues | 103 |
| Results | 104 |
| Parallelization Performance | 104 |
| Code Validation | 105 |
| Feasibility Study | 107 |
| Conclusions | 109 |
| References | 110 |
| Application of Transition Prediction | 112 |
| Introduction | 112 |
| Transition Prediction Coupling | 114 |
| Computational Results | 116 |
| Conclusion | 124 |
| References | 125 |
| Numerical Simulation Quality Assessment for Transport Aircraft | 126 |
| Introduction | 126 |
| Aspects of Accuracy | 126 |
| Status on Accuracy | 127 |
| Cruise Configuration Analysis | 127 |
| High Lift Configuration Analysis | 130 |
| Means to Improve Accuracy | 133 |
| Conclusions | 136 |
| References | 136 |
| Part III Fluid Structure Coupling | 137 |
|---|
| Computational Methods for Aero-Structural Analysis and Optimisation of Aircrafts Based on Reduced-Order Structural Models | 138 |
<
