Computational Simulation of Unsteady, Viscous, Hypersonic Flow about Flight Vehicles with Store Separation

Abstract

Public reporting burden for this collection of information n estimated to average 1 hour per response, including gathering and maintaining the data needed, and completing and reviewing the collection of information. «a »(«91 «aw ABSTRACT (Maximum 200 words)This project describes a research project to develop a computational capability to accurately and efficiently simulate unsteady, three-dimensional, hypersonic, viscous flow fields about realistic flight vehicle configurations with separating stores and/or components. Unstructured grid technology with an advanced implicit high-resolution flow field, solution algorithm is utilized as the basis for this computational capability. The solution algorithm uses an implicit Newton-relaxation scheme with approximate LU factorization and Roe flux-difference splitting. A new unstructured grid generation procedure labeled Advancing-Front/LocalReconnection (AFLR) was developed that significantly improves the state-of-theart. This procedure uses an iterative point placement scheme. New points are generated using advancing-front type point placement and the connectivity is optimized with iterative local-reconnection. The combined efficiency, quality, and robustness for AFLR are a substantial improvement over existing techniques. Unsteady and steady flow fields about complex flight vehicles with separating components were simulated to demonstrate, test, and validate the overall computational procedure. SUBJECT TERMScomputational fluid dynamics, unstructured grid generation