7.5.1 Inner block enclosing the XV-15 3-bladed prop #įig. The interface between those two volumes needs to be a solid of revolution (i.e., sphere, cylinder, etc.).įig. In order to run a rotating geometry we need to set up a mesh with two blocks, an inner “rotational volume” and an outer “stationary volume”. Here we will go more in depth into how to get a sliding interface case setup. This same geometry and case was already used in a Quick Start example. Rotor5: Rotor analysis under 5 hours using ultra-fast and high-fidelity CFD simulation and automatic meshingĪssessment of Detached Eddy Simulation and Sliding Mesh Interface in Predicting Tiltrotor Performance in Helicopter and Airplane Modes We will now use it to show you how to analyze a propeller-type geometry using a sliding mesh interface. As you can see from the following papers, we have done extensive validation work on this geometry. The XV-15 tiltotor aircraft is a commonly used test bed for propeller validation work. Time-accurate RANS CFD on a propeller using a sliding interface: the XV-15 rotor geometry # CGNS Mesh Format and Multizone Interface Connectivityħ.5. TU Berlin TurboLab Stator simulation using periodic boundary conditionsĨ.1.6. Conjugate Heat Transfer for Cooling Finsħ.9. Calculating Dynamic Derivatives using Sliding Interfacesħ.8. Time-accurate RANS CFD on a propeller using a sliding interface: the XV-15 rotor geometryħ.6. Blade Element Theory using the XV-15 rotorħ.5. RANS CFD on 2D High-Lift System Configuration Using the Flow360 Python Clientħ.4. ![]() Non-Dimensionalization and Integrated Loads Post-Processing in Flow360ħ.3. Geometry Modeling and Preparation for Automated Meshing: An Example of the ONERA M6 Wingħ.2. Scale-Resolving Simulations Past a Circular Cylinderħ.1. XV-15 Rotor Blade Analysis using the Blade Element Disk MethodĦ.11. Drag Prediction of Common Research ModelĦ.9. High Lift Common Research Model (HL-CRM)Ħ.7. 2D NACA 4412 Airfoil Trailing Edge SeparationĦ.6. ![]() ![]() Propeller Models and Rotational Volume ZonesĦ.2.
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