Accession Number : ADA263905
Title : Solution of Euler Equations for Forebody-Inlet Ensemble of Aircraft at High Angle of Attack,
Corporate Author : FOREIGN AEROSPACE SCIENCE AND TECHNOLOGY CENTER WRIGHT-PATTERSON AFB OH
Personal Author(s) : Xiaoqing, Zheng ; Huili, Shen
Report Date : 27 APR 1993
Pagination or Media Count : 19
Abstract : A computational procedure was developed to simulate inviscid flows over integrated forebody-inlet ensemble of an aircraft model. The analysis, which includes the effect of Mach number, angle of attack and engine mass flow, is based on the solution of three-dimensional Euler equations. A finite-volume spatial discretization and a Runge-Kutta time stepping scheme are employed in solving the equations. To achieve the required geometric flexibility, a multizone mesh is used. The entire computational domain is divided into three zones. The mesh of each zone is generated by interpolating the fluxes across the interface between adjacent zones during iterations. A new type of treatment of inlet exit boundary conditions was developed and tested. The procedure was applied to forebody-inlet analysis for a range of flight conditions including subsonic, transonic and supersonic flight with various engine mass flows and angles of attack. In addition, the steady states of supersonic flight up to 15 degrees of angle of attack for the subcritical engine regime were obtained. The results are in good agreement with the experimental data.... Inlet, Euler equations, High angle of attack.
Descriptors : *BOUNDARY LAYER FLOW, *WING BODY CONFIGURATIONS, *JET ENGINE INLETS, AIRCRAFT MODELS, ANGLE OF ATTACK, EULER EQUATIONS, EXITS, EXPERIMENTAL DATA, FLIGHT, HIGH ANGLES, INTERFACES, ITERATIONS, MACH NUMBER, MASS FLOW, MESH, REGIONS, SUPERSONIC FLIGHT, THREE DIMENSIONAL, TRANSLATIONS, CHINA, CHINESE LANGUAGE, RUNGE KUTTA METHOD.
Subject Categories : Aircraft
Distribution Statement : APPROVED FOR PUBLIC RELEASE