Numerical Simulations of a Quiet SuperSonic Technology (QueSST) Aircraft Preliminary Design

Friedlander, David J ; Heath, Christopher M ; Castner, Raymond S

关键词: SUPERSONIC AIRCRAFT;    COMPUTATIONAL FLUID DYNAMICS;    GRID REFINEMENT (MATHEMATICS);    ADJOINTS;    REYNOLDS AVERAGING;    NAVIER-STOKES EQUATION;    COMPUTERIZED SIMULATION;   

RP-ID  :  NASA/TM-2018-219967,E-19577,GRC-E-DAA-TN59408

学科分类：航空航天科学

美国|英语

来源: NASA Technical Reports Server

【 摘 要 】

Reynolds Averaged Navier-Stokes (RANS) simulations were performed on the Lockheed Martin Quiet SuperSonic Technology (QueSST) aircraft preliminary design to assess inlet performance. The FUN3D flow solver and its adjoint-based grid refinement capability was used for the simulations in hopes of determining internal "best practices" for predicting inlet performance on top-aft-mounted inlets. Several parameters were explored including tetrahedral vs. pentahedral cells in/around the boundary-layer regions, an engine axis-aligned linear pressure sensor vs. a pressure box objective as the grid adaptation metric, and the number of grid adaptation cycles performed. Additional simulations were performed on manually refined grids for comparison with the adjoint-based adapted grids