Applying and validating the RANS-3D flow-solver for evaluating a subsonic serpentine diffuser geometrySubsonic inlet ducts for advanced, high-performance aircraft are evolving towards complex three-dimensional shapes for reasons of overall integration and weight. These factors lead to diffuser geometries that may sacrifice inlet performance, unless careful attention to design details and boundary layer management techniques are employed. The ability of viscous computational fluid dynamic (CFD) analysis of such geometries to aid the aircraft configurator in this complex design problem is herein examined. The RANS-3D Reynolds-Averaged Navier-Stokes solver is applied to model the complex flowfield occurring in a representative diffuser geometry and the solutions are compared to experimental results from a static test of the inlet duct. The computational results are shown to compare very favorably with experimental results over a range of mass flow rates, including those involving large amounts of separation in the diffuser. In addition, a novel grid topology is presented, and two turbulence models are evaluated in this study as part of the RANS-3D code.
Document ID
19930065976
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Fletcher, Michael J. (NASA Ames Research Center Moffett Field, CA, United States)
Won, Mark J. (NASA Ames Research Center Moffett Field, CA, United States)
Cosentino, Gary B. (NASA Ames Research Center Moffett Field, CA, United States)
Te, Alexander (Sterling Federal Systems, Inc. Palo Alto, CA, United States)
Date Acquired
August 16, 2013
Publication Date
June 1, 1993
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 93-2157
Meeting Information
Meeting: AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference and Exhibit