翼形表面流动激励载荷特征试验研究  

Experimental study on characteristics of flow excitation load on airfoil surface

作　　者：杨洋 吕世金 吴光耀[1] 彭子龙 YANG Yang;LYU Shijin;WU Guangyao;PENG Zilong(School of Energy and Power,Jiangsu University of Science and Technology,Zhenjiang 212100,Jiangsu,China;Nation Key Laboratory on Ship Vibration and Noise,China Ship Science Research Center,Wuxi 214082,Jiangsu,China)

机构地区：[1]江苏科技大学能源与动力学院,江苏镇江212100 [2]中国船舶科学研究中心船舶振动噪声重点试验室,江苏无锡214082

出　　处：《声学技术》2024年第2期192-196,共5页Technical Acoustics

基　　金：国家自然科学基金(91952301,52201397);基础加强计划重点项目(2020-JCJQ-ZD-222)。

摘　　要：为了研究水下航行体翼形表面流动激励载荷特征,采用柔性基底微型传感器阵列,建立风洞中翼形结构表面流动激励载荷测试方法。分析了翼形表面层流、转捩、湍流发展过程中激励力试验特征,试验结果表明:翼形表面经过层流、转捩、湍流发展过程,随着来流速度的增大,翼形表面转捩区位置逐渐前移直至完全湍流。提出了转捩点预报修正方法,修正后预报值与试验值偏差在10%以内,为水下航行体翼形流动激励力相关研究提供试验基础。In order to explore the characteristics of the flow excitation load on the airfoil surface of an underwater vehicle,a method for the flow excitation load measurements on airfoil surface in a wind tunnel is established by using the micro sensor array on a flexible substrate.The characteristics of the flow excitation force in the developing process are analyzed.The experimental results show that through the developing process of laminar flow,transition and turbulence,the position of the transition zone on the airfoil surface gradually moves forward to complete turbulence with the increase of incoming flow velocity.And,the prediction and correction method of transition point is proposed.The deviation between the corrected prediction value and the experimental value is less than 10%,which provides an experimental basis for the research on the airfoil flow excitation force of underwater vehicles.

关 键 词：翼形 流动激励力 风洞试验 

分 类 号：U661.1[交通运输工程—船舶及航道工程]