Numerical Simulation Of Flat Plate Trajectory Using Coupled Cfd Rbd With Dynamic Meshing
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Numerical Simulation of Flat Plate Trajectory Using Coupled CFD-RBD with Dynamic Meshing
Foreign object debris including bird and/or drone strike debris upon impact, may cause critical secondary damage to downwind aircraft surfaces. This debris is simplified in geometry to a flat plate and represented as a rigid body for better comparison with experimental results. In this study, a coupled computational fluid dynamics (CFD)-rigid body dynamics (RBD) solver with dynamic meshing was used for numerical analysis of the flat plate trajectory in a uniform flow field. The computed trajectory of the rectangular flat plate was validated against available experimental data and compared with existing numerical results. Less than 10% difference was observed between the simulated trajectory and the experimental results. Furthermore, a parametric analysis and probability analysis were conducted to identify the sensitivity of plate trajectory to initial conditions and to obtain a probability distribution of the location of the center of gravity of the plate at a distance downstream of the release location. The studies depict the sensitivity of the path taken by the plate to initial release orientation and to initial angular velocities of the plate. Additionally, flow field interaction studies were conducted by simulating the release of multiple plates in the domain to observe the effect of distance and mass on the plate trajectories. Finally, a single plate was released in the vicinity of a wing for a qualitative analysis of the effect of change in aerodynamic forces on the plate trajectory due to the presence of the wing.
A 3-d Unstructured CFD Method for Maneuvering Vehicles
Numerical simulation of maneuvering vehicles is accomplished using a three dimensional (3-D) unstructured computational fluid dynamic (CFD) method. The equations of fluid motion used are either the inviscid Euler equations or the full viscous Navier Stokes equations cast in an Arbitrary Lagrangian- Eulerian (ALE) framework. A turbulence model developed by Spalart and Allmaras is used for viscous solutions. The system of fluid equations are solved implicitly using upwind, flux-splitting techniques for the convective fluxes of either Roe or Van Leer with up to second-order temporal and spatial accuracy for steady or unsteady computations. Innovative boundary conditions for a moving mesh to include inviscid, viscous, far-field and a solid rocket motor exhaust exit surface were developed. The temporal solution is found using an application of Newton's method. The computational field simulation (CFS) of two 3-D wings and a waisted-body of revolution are compared to experimental data for boundary condition validation. An unsteady CFS of a pitching wing is validated by comparison to experimental data. A number of unsteady missile maneuver trajectories coupled with a six degree of freedom model using Euler angles and the Flat-Earth model are presented.
Dynamic-Mesh CFD and Its Application to Flapping-Wing Micro-Air Vehicles
We are currently developing new numerical simulation methods and computational fluid dynamics (CFD) codes designed for advanced fluid-structure interaction (FSI) applications that have moving mechanical components and/or changing domain shapes. The method is called Dynamic-Mesh (DM) and is currently being implemented in parallel within our XFlow CFD simulation code. This method involves the tight coupling of automatic mesh generation (AMG) technology with more traditional parallel CFD methods designed for unstructured meshes. By coupling these two distinct technologies together, the mesh generation process never stops and continues throughout the entire simulation. By doing this, we can define a so-called "dynamic" mesh that has the ability to adjust, change, and modify its structure in response to any changes in geometry or other factors. DM-CFD technology of XFlow can be used to model the fluid flow around or within flapping-wing vehicles, rotorcraft, engines, turbines, pumps, airdrop systems, and has applicability to modeling free-surface flow, fluid-particle flow, energy/nuclear systems, and many bio-medical applications. Traditionally, these are some of the most difficult applications to simulate. We are currently demonstrating and testing the DM technique and the capabilities of XFlow through a series of complex FSI applications. These applications include the simulation of airdrop systems involving the deployment (i.e. opening) of parachutes, bio-medical applications, and the simulation of micro air vehicles (MAV) and biological systems. Results of the modeling of a flapping-wing MAV will be highlighted here to demonstrate the capabilities and potential of the DM method in XFlow, as well as providing some illustrative results for an interesting application.