Numerical investigation of Reynolds number effects on a low-aspect-ratio flying-wing model

Reynolds number effect on a low-aspect-ratio flying-wing model is investigated using CFD. Numerical simulations are performed for three Reynolds numbers, i.e. Reynolds number of wind tunnel testing, doubled tunnel testing and fly testing by using software Mbflow developed in house, which is a multiblock structured grid slover aiming at solving subsonic, transonic and supersonic flow field. Then numerical results are presented and discussed, and the propertys of Reynolds number effects are investigated on different Mach numbers (0.2, 0.8 and 1.5) and different angles of attack. At small angle of attack, skin friction drag is affected by Reynolds number. At bigger angles of attack, both skin friction drag and pressure drag are affected. The initial location and strength of vortex are affected by Reynolds number at subsonic flow. At transonic and supersonic flow, the location and strength of shock wave are affected too. In addition, the prospective area of Reynolds number of this model is studied. It is found that experiment's Reynolds number is approaching the prospective area of Reynolds number.