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

摘要

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/Local-Reconnection (AFLR) was developed that significantly improves the state-of-the-art. 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.