Доступ предоставлен для: Guest
TSFP DL Home Архив Исполнительный Комитет

DETAILED NUMERICAL SIMULATIONS OF A SUPERSONIC INLET-ISOLATOR

Heeseok Koo
Department of Aerospace Engineering and Engineering Mechanics, The University of Texas at Austin 210 E. 24th St. WRW 305A, Austin, Texas, 78712, USA; Sandia National Laboratories, Albuquerque, NM 87105, USA; Rolls Royce Indianapolis, IN, USA

Venkatramanan Raman
University of Texas at Austin, W. R. Woolrich Laboratories, 210 East 24th Street, Austin, Texas 78712-0235, USA

Аннотация

An isolator is an important component of dual-mode scramjet engines that separates the combustor from the engine inlet. This flow section contains a time-varying shock-train that adapts to external variations in order to provide a stable flow to the combustion chamber. The goal of this study is to understand the key modeling issues in computing the flow inside an isolator. We develop a large-eddy simulation (LES) based computational tool using a conservative finite difference method. This tool is validated using detailed measurements from an experimental isolator. Several different models, numerical schemes, and computational grids are tested. The shock structure inside the isolator is relatively stable and insensitive to the computational details. All the simulations overpredict the velocity fluctuations in the boundary layer. Further, simulations exhibit boundary layer separation due to shock impingement, a feature absent in the experiments. These studies indicate that current LES modeling practices are inadequate for describing isolator physics.