Mary Reveley, of the Multidisciplinary Design, Analysis, and Optimization Branch, was recognized as one of eight key NASA members of Commercial Aviation Safety Team (CAST) at the Collier Trophy Presentation Banquet on May 28, in Arlington, VA.
The CAST, established in 1997, was chosen for the award for achieving an unprecedented safety level in U.S. commercial airline operations by reducing risk of a fatal airline accident by 83 percent, resulting in two consecutive years of no commercial airline fatalities. Also in attendance at the banquet were the present and former Aviation Safety Program Managers.
Author: Webmaster
| Other Categories: Awards, Honors & Patents
Mary Reveley of the Multidisciplinary Design, Analysis and Optimization (MDAO) Branch will be recognized as one of eight key NASA members of Commercial Aviation Safety Team (CAST) to be invited to the Collier Award Dinner on May 28, 2009, in Arlington, Virginia. The NASA Ames Research Center, NASA Langley Research Center, and the NASA Glenn Research Center will each receive a Collier Trophy.
Several members of the team including three researchers from the Icing Branch — Tom Ratvasky, Andy Reehorst, and Tom Bond (currently with FAA) — will also receive a certificate from NASA’s Aeronautics Research Mission Directorate (ARMD) Associate Administrator (AA).
Author: Webmaster
| Other Categories: Awards, Honors & Patents
A short note entitled “Multi-dimensional dissipation for cure of pathological behaviors of upwind scheme” authored by C. Loh (Multidisciplinary Design, Analysis & Optimization Branch) and P. Jorgenson (Turbomachinery & Heat Transfer Branch) was published in the March issue of the Journal of Computational Physics. The publication provides a technique to systematically suppress nonphysical (numerically generated) flow phenomena seen in steady and unsteady high Mach number computations such as the carbuncle phenomenon, expansion shock, slow moving shock oscillations, etc. in upwind schemes through a simple dissipation model while preserving the second order accuracy of the original scheme.
There have been many recommended fixes to these problems but none covered the complete range of known nonphysical behavior particularly on unstructured grids. This enhanced method has been applied successfully over a wide range of Mach numbers to the fields of computational fluid dynamics and computational aeroacoustics including flows that approach the incompressible limit without use of temporal preconditioning. This work is supported by Aeronautics Research Mission Directorate.
Author: Webmaster
| Other Categories: Awards, Honors & Patents, Turbomachinery & Heat Transfer
