- Aeronautics and Astronautics
Top 3 Areas of Expertise:
Expected date of graduation:
The aerospace industry is considered an early-adopter regarding the use of computers as design tools, to the point where it can take a proactive role and be the driver for innovation in algorithms and hardware. The raise in computational power available in commodity clusters has increased the use of such numerical tools to the point where physical tests can be reduced to a minimum. In the case of aerodynamics, such heavy use of computers has reduced the amount of wind-tunnel testing required to iterate and validate a design, circumventing issues like physical similarity, e.g. Reynolds number or wall effects, along the way.
The increasing complexity of the cases run in industry, is mostly leveraged by the increasing capabilities of the hardware, rather than any substantial change in the algorithms. This has been identified by the CFD community as an undesirable situation. In particular, one would like to invert this trend and use the available computational power to run more complex algorithms that produce more accurate solutions with the same computational effort. For a while now, high order methods have been identified as a way to do this, and research into their application to CFD has grown significantly. Of particular importance to their success is the issue of robustness for: 1) compressible flows in which shock waves appear, and, 2) turbulence modeling using RANS. In this thesis, we propose independent ways to address these two issues.
In the case of turbulent flows, the prohibitive cost of simulating all the scales of the problem (DNS) or even part of them (LES) has made the cheaper RANS equations the de-facto approach in industry. As expected, there is a price to pay for this in that turbulence has to be modeled rather than directly computed. While there exists a variety of turbulence models to represent the Reynolds stresses, none of them can reliably account for the onset of turbulence. On the other hand, 50 years of work on the stability analysis of boundary layers has produced a significant amount of semi-empirical transition prediction methods suitable for engineering applications, most notably, the eN method. In this thesis we propose to develop a high order RANS solver with transition capabilities, based on the eN method.
Top 5 Awards and honors (name of award, date received):
5 Recent Papers:
Rus J., Moro D., Sillero J. A., Royuela J., Casado A., Estevez-Molinero F., and Fernandez de la Mora J. (2010), "IMS-MS Studies Based on Coupling a Differential Mobility Analyzer (DMA) to Commercial API-MS Systems", International Journal of Mass Spectrometry, 298:30-40 <a href="http://www.sciencedirect.com/science/article/pii/S138738061000134X" target="_blank"> link to ScienceDirect</a>
Moro D., Nguyen N.C., Peraire J., (2012) "A hybridized discontinuous PetrovGalerkin scheme for scalar con- servation laws", International Journal for Numerical Methods in Engineering, 91(9):950-970 <a href="http://onlinelibrary.wiley.com/doi/10.1002/nme.4300/full" target="_blank"> <img class="icon" src="./files/logos/link_icon.png" alt=""> link to Wiley</a>
Moro D., Nguyen N.C., Drela M, Peraire J., (2013), "A High-Order Self-Adaptive Monolithic Solver for Viscous-Inviscid Interacting Flows", 51st AIAA Aerospace Sciences Meeting, Grapevine, TX. (AIAA Paper 2013-857) <a href="http://arc.aiaa.org/doi/abs/10.2514/6.2013-857" target="_blank"> link to AIAA</a>
Moro D., Nguyen N.C., Peraire J., (2011), "Navier-Stokes Solution Using Hybridizable Discontinuous Galerkin methods", 20th AIAA Computational Fluid Dynamics Conference, Honolulu, HI, June 2011. (AIAA Paper 2011-3407) <a href="http://arc.aiaa.org/doi/abs/10.2514/6.2011-3407" target="_blank"> link to AIAA</a>
Nguyen N.C., Roca X., Moro D., Peraire J., (2013) "A Hybridized Multiscale Discontinuous Galerkin Method for Compressible Flows", 51st AIAA Aerospace Sciences Meeting, Grapevine, TX, January 2013. (AIAA Paper 2013-689) <a href="http://arc.aiaa.org/doi/abs/10.2514/6.2013-689" target="_blank"> link to AIAA </a>