某民机着陆构型雷诺数效应风洞试验研究

摘要

By conducting a series of high Reynolds number wind- tunnel tests on a half civil aircraft model with a landing configuration, the influence of Reynolds number at different Mach numbers were obtained. The results showed that in the range of testing Reynolds numbers the maximum lift coefficient was sensitive to Re and its change tendency with Re was not monotone but tended to be steady. And it was also found that longitudinal static stability of the aircraft increase with the increment of Re.%通过对某民机增升装置着陆构型进行半模高雷诺数风洞试验,获得了不同马赫数下的雷诺数影响.结果表明:对于该民机的着陆构型,在试验雷诺数范围内,雷诺数对最大升力系数的影响存在敏感区域,最大升力系数随雷诺数增加的变化并不单调,但趋于平缓,纵向静稳定性随着雷诺数增加而增大.