Computational Modeling of the CH-47 Helicopter in Hover

This paper describes installed rotor performance computations for the CH-47 Chinook tandem-rotor helicopter. The computations were performed with a Reynolds-Averaged Navier-Stokes flow solver using overset structured grids to resolve the flow around the rotors, the fuselage, and the resulting rotor wake system. The calculations model all six rotor blades discretely while resolving the rotor motions relative to the fuselage in a time-accurate manner. The computational performance predictions are compared to Boeing flight test data and show good agreement with the experimental measurements. In addition, the computational results provide a wealth of data on the interactions between the rotor wake system and the fuselage that cant be easily obtained in any other way. The original document contains color images. All DTIC reproductions will be in black and white. Presented at the DoD High Performance Computer Modernization Program (HPCMP) Users Group Conference (USG)(2007): A Bridge to Future Defense held in Pittsburgh, PA on 18-21 June 2007. Published in Proceedings of the DoD High Performance Computer Modernization Program (HPCMP) Users Group Conference (USG), p98-103, June 2007. Publisher: IEEE Computer Society, Conference Publishing Services (CPS). ISBN 0-7695-3088-5 and ISBN 978-0-7695-3088-8. Sponsored in part by the US Army Research, Development, and Engineering Command, contract NNA05BF35C. This article is from ADA488707 Proceedings of the HPCMP Users Group Conference 2007. High Performance Computing Modernization Program: A Bridge to Future Defense held 18-21 June 2007 in Pittsburgh, Pennsylvania