航空工程进展Issue(4)：448-454,7.
高雷诺数下机翼表面层流段长度对减阻量的影响
Effect of Laminar Flow Extent on Wing Surface on Drag Reduction at High Reynolds Numbers
马玉敏 1张彦军1
作者信息
- 1. 中国航空工业集团公司第一飞机设计研究院，西安 710089
- 折叠
摘要
Abstract
Effect of laminar flow extent on drag reduction characteristic based on engineering practice is of signi‐fance 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 × 107 and 1 .8 × 107 ,with the laminar flow extent being kept respec‐tively 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 .关键词
自然层流/层流减阻/层流段长度/摩擦阻力系数/升阻比/高雷诺数Key words
natural laminar flow/laminar drag reduction/laminar flow extent/frictional drag coefficient/lift-drag ratio/high Reynolds number分类
航空航天引用本文复制引用
马玉敏,张彦军..高雷诺数下机翼表面层流段长度对减阻量的影响[J].航空工程进展,2014,(4):448-454,7.
