Toggle navigation sidebar
Toggle in-page Table of Contents
Table of Contents
1. Quick Start
1.1. Run CFD using Web UI: An example of ONERA M6 Wing
1.2. Run CFD using Python API: An example of ONERA M6 Wing
1.3. Run CFD using Automated Meshing and Web UI
1.4. Run CFD using Automated Meshing and Python API
1.5. Run CFD using Automated Meshing: An example of S809 Airfoil
1.6. Run CFD on a propeller: An example XV-15 rotor geometry
2. Capabilities
2.1. Overview
2.2. Feature Compatibility Matrix
2.3. Blade Element Theory Model
2.4. User Defined Dynamics
3. Preprocessing
3.1. Install Engineering Sketch Pad (ESP)
3.2. Manual Meshing
3.3. Automated Meshing
4. Solver Configuration
5. Postprocessing
6. Python API Reference
7. Frequently Asked Questions
8. Case Studies
8.1. NACA 0012 Low Speed Airfoil
8.2. 2D NACA 4412 Airfoil Trailing Edge Separation
8.3. 2D Backward Facing Step
8.4. High Lift Common Research Model (HL-CRM)
8.5. Drag Prediction of Common Research Model
8.6. ONERA M6 Wing
8.7. XV-15 Rotor Blade Analysis using the Blade Element Disk Method
9. Tutorials
9.1. Geometry Modeling and Preparation for Automated Meshing: An Example of the ONERA M6 Wing
9.2. Non-Dimensionalization and Integrated Loads Post-Processing in Flow360
9.3. RANS CFD on 2D High-Lift System Configuration Using the Flow360 Python Client
9.4. Time-accurate RANS CFD on a propeller using a rotation interface: the XV-15 rotor geometry
10. Conventions
11. Publications
11.1. Webinar
11.2. Papers
12. Release Notes
.rst
.pdf
Case Studies
8.
Case Studies
#
8.1. NACA 0012 Low Speed Airfoil
8.1.1. Introduction
8.1.2. Mesh and Flow Configuration
8.1.3. SA/SA-RC Model Results
8.1.4. SST(m) Model Results
8.1.5. Remarks
8.2. 2D NACA 4412 Airfoil Trailing Edge Separation
8.2.1. Introduction
8.2.2. Simulation setup
8.2.3. Numerical Results
8.3. 2D Backward Facing Step
8.3.1. Introduction
8.3.2. Simulation setup
8.3.3. Numerical Results
8.4. High Lift Common Research Model (HL-CRM)
8.4.1. Introduction
8.4.2. Problem Description
8.4.3. Mesh
8.4.4. Setup and Solution
8.4.5. Grid Convergence
8.4.6. Results
8.4.7. Summary
8.5. Drag Prediction of Common Research Model
8.5.1. Introduction
8.5.2. Problem Description
8.5.3. Mesh
8.5.4. Setup and Solution
8.5.5. Grid Convergence
8.5.6. Results
8.5.7. Summary
8.6. ONERA M6 Wing
8.6.1. Introduction
8.6.2. Setup and Solution
8.6.3. Grid Convergence
8.6.4. Results
8.6.5. Summary
8.7. XV-15 Rotor Blade Analysis using the Blade Element Disk Method
8.7.1. Highlights
8.7.2. Introduction
8.7.3. Helicopter Hovering Mode
8.7.4. Airplane Mode
