6. Case Studies

• 6.1. NACA 0012 Low Speed Airfoil
  • 6.1.1. Introduction
  • 6.1.2. Mesh and Flow Configuration
  • 6.1.3. SA/SA-RC Model Results
  • 6.1.4. SST(m) Model Results
  • 6.1.5. Remarks
• 6.2. 2D NACA 4412 Airfoil Trailing Edge Separation
  • 6.2.1. Introduction
  • 6.2.2. Simulation setup
  • 6.2.3. Numerical Results
• 6.3. 2D Backward Facing Step
  • 6.3.1. Introduction
  • 6.3.2. Simulation setup
  • 6.3.3. Numerical Results
• 6.4. Transition Modeling
  • 6.4.1. Introduction
  • 6.4.2. Flat Plate Case
  • 6.4.3. NLF(1)-0416 Airfoil Case
  • 6.4.4. Conclusions
• 6.5. High Lift Common Research Model (HL-CRM)
  • 6.5.1. Introduction
  • 6.5.2. Problem Description
  • 6.5.3. Mesh
  • 6.5.4. Setup and Solution
  • 6.5.5. Grid Convergence
  • 6.5.6. Results
  • 6.5.7. Summary
• 6.6. Drag Prediction of Common Research Model
  • 6.6.1. Introduction
  • 6.6.2. Problem Description
  • 6.6.3. Mesh
  • 6.6.4. Setup and Solution
  • 6.6.5. Grid Convergence
  • 6.6.6. Results
  • 6.6.7. Summary
• 6.7. ONERA M6 Wing
  • 6.7.1. Introduction
  • 6.7.2. Setup and Solution
  • 6.7.3. Grid Convergence
  • 6.7.4. Results
  • 6.7.5. Summary
• 6.8. XV-15 Rotor Blade Analysis using the Blade Element Disk Method
  • 6.8.1. Highlights
  • 6.8.2. Introduction
  • 6.8.3. Helicopter Hovering Mode
  • 6.8.4. Airplane Mode
• 6.9. DTU 10MW Wind Turbine
  • 6.9.1. Introduction
  • 6.9.2. Rotor Geometry
  • 6.9.3. Automated Meshing
  • 6.9.4. Flow Configuration
  • 6.9.5. Residual Convergence
  • 6.9.6. Surface and Volumetric Results
  • 6.9.7. Sectional Loads on One of the Blades
  • 6.9.8. Integrated Loads on the Entire Rotor
  • 6.9.9. Off-Design Performance
• 6.10. Scale-Resolving Simulations Past a Circular Cylinder
  • 6.10.1. Introduction
  • 6.10.2. Simulation Setup
  • 6.10.3. Grid Refinement Study
  • 6.10.4. Time-Dependent Flow Field Results
  • 6.10.5. Time-Averaged Flow Field Results
  • 6.10.6. Conclusions