高雷诺数下机翼表面层流段长度对减阻量的影响

层流减阻技术是提高飞机经济性的重要手段,开展可应用于工程实践的层流减阻研究具有重要的意义。针对某民用飞机翼身组合体构型,采用数值模拟法分别研究雷诺数为1.0×107和1.8×107时全湍流以及机翼弦向保持7%、15%、20%、30%、40%层流段长度范围的减阻特性。结果表明:与全湍流情况相比,层流段长度的增加可以有效减小飞机阻力,增加升阻比;当层流段长度保持在40%时,飞机的减阻量可以达到11.0%左右,而升阻比可增加12.3%左右,且在较小雷诺数下有着更大的减阻收益;层流范围增加可有效减小摩擦阻力系数。

The Effect of Laminar Flow Extent on Wing Surface on Drag Reduction at high Reynolds numbers

Effect of laminar flow extent on drag reduction characteristic based on engineering practice is of signifance for some civil plane,which can be the important means to improve the economy.It is simulated for the wing-body model at Reynolds numbers 1.0×10^7 and 1.8×10^7,with the laminar flow extent being kept respectively 7%,15%,20%,30%,40% of the local chord of wing.Compared with the full turbulence state,the drag can be reduced by about 11.0% and the lift-drag ratio can be increased by about 12.3% when the laminar flow extent is kept with 40%,and drag reduction benefit can be obtained more at lower Reynolds number.The frictional drag coefficient is effectively decreased as the laminar flow extent is increased.