采用数值模拟方法开展小展弦比飞翼标模的雷诺数影响研究。使用自行研制的多块对接结构网格亚跨超声速流场解算器程序 Mbflow，计算了试验雷诺数、二倍试验雷诺数和飞行雷诺数等三种雷诺数情况下小展弦比飞翼标模的流场。通过对计算结果的分析研究，得到了不同马赫数（Ma＝0．2、0．8和1．5）和攻角情况下雷诺数对小展弦比飞翼标模的气动特性和流场特征的影响规律。小攻角情况下，雷诺数主要影响摩阻的大小；而大攻角时，雷诺数对压阻也有明显影响。在亚声速时，雷诺数主要影响分离涡的起始位置和强度；跨声速和超声速时，雷诺数还会影响到激波的位置和强度。进一步研究了小展弦比飞翼标模的自准区雷诺数问题，发现试验雷诺数接近于小展弦比飞翼标模的自准区雷诺数。%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,tran-sonic 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 and1.5)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 af-fected.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 ex-periment’s Reynolds number is approaching the prospective area of Reynolds number.
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