국내 최대 기계 및 로봇 연구정보

기술보고서

기술보고서 게시판 내용
타이틀	Status of Turbulence Modeling for Hypersonic Propulsion Flowpaths
저자	Georgiadis, Nicholas J.;; Yoder, Dennis A.;; Vyas, Manan A.;; Engblom, William A.;; FROM
Keyword	HYPERSONIC FLIGHT;; LARGE EDDY SIMULATION;; NAVIER-STOKES EQUATION;; REYNOLDS AVERAGING;; SCALARS;; SHOCK WAVES;; SIMULATION;; SUPERSONIC COMBUSTION RAMJET ENGINES;; TURBULENCE EFFECTS;; TURBULENCE MODELS;; TURBULENT BOUNDARY LAYER;; TURBULENT FLOW
URL	http://hdl.handle.net/2060/20120008521
보고서번호	NASA/TM-2012-217277
발행년도	2012
출처	NTRS (NASA Technical Report Server)
ABSTRACT	This report provides an assessment of current turbulent flow calculation methods for hypersonic propulsion flowpaths, particularly the scramjet engine. Emphasis is placed on Reynolds-averaged Navier-Stokes (RANS) methods, but some discussion of newer meth- ods such as Large Eddy Simulation (LES) is also provided. The report is organized by considering technical issues throughout the scramjet-powered vehicle flowpath including laminar-to-turbulent boundary layer transition, shock wave / turbulent boundary layer interactions, scalar transport modeling (specifically the significance of turbulent Prandtl and Schmidt numbers) and compressible mixing. Unit problems are primarily used to conduct the assessment. In the combustor, results from calculations of a direct connect supersonic combustion experiment are also used to address the effects of turbulence model selection and in particular settings for the turbulent Prandtl and Schmidt numbers. It is concluded that RANS turbulence modeling shortfalls are still a major limitation to the accuracy of hypersonic propulsion simulations, whether considering individual components or an overall system. Newer methods such as LES-based techniques may be promising, but are not yet at a maturity to be used routinely by the hypersonic propulsion community. The need for fundamental experiments to provide data for turbulence model development and validation is discussed.