階層型直交格子流体ソルバを用いたデルタ翼の低速性能に関する考察

抄録

Delta wings used for supersonic aircraft have to take a large angle of attack at takeoff and landing due to their low aerodynamic performance at low speed, which causes leading-edge vortices over the wing's upper surface. The previous paper used a hierarchical Cartesian grid flow solver to conduct steady flow analyses based on Navier-Stokes equations (NS) around flat-plate delta wing. This research uses steady flow analyses based on Reynolds-averaged Navier-Stokes equations (RANS) with two turbulence models (SA-noft2 and SA-noft2-R). This study examines the difference in the vortex phenomena between the results with different turbulence models and the suitable governing equations comparing the results of NS and RANS. The SA-noft2-R model shows better results than the SA-noft2 regarding the reproducibility of vortex flow pattern, but SA-noft2 predicts the primary vortex core location better than SA-noft2-R. Also, it is interesting to note that NS results are better than the RANS result compared to the experimental results. From these results, the analysis using NS is appropriate for estimating the vortex position around the delta wing under the flow field conditions conducted in this study.