CAJ | 학술논문

传统的叶型气动设计体系建立在高雷诺数基础上，UAV（无人飞行器）的发展对低雷诺数叶型气动设计和试验验证提出了新的要求。本文就降低叶型试验雷诺数的原理、实现的方法进行了分析，提出了在现有试验器基础上进行设备改造的方案和试验调节方法，并根据试验数据对改造后试验器的低雷诺数流场进行了初步分析，在国内首次通过试验手段获得了某高亚声速扩压叶型气动性能参数在低雷诺数条件下的特性。
전통적협형기동설계체계건립재고뢰낙수기출상，UAV（무인비행기）적발전대저뢰낙수협형기동설계화시험험증제출료신적요구。본문취강저협형시험뢰낙수적원리、실현적방법진행료분석，제출료재현유시험기기출상진행설비개조적방안화시험조절방법，병근거시험수거대개조후시험기적저뢰낙수류장진행료초보분석，재국내수차통과시험수단획득료모고아성속확압협형기동성능삼수재저뢰낙수조건하적특성。
The conventional airfoil design system is based on high Reynolds number, but the development of UAV （unmanned aerial vehicle） has offered the new demands on airfoil design and experimental verifi- cation under low Reynolds number condition. This paper analyses the theory and methods for low Reynolds number cascade aerodynamic performance. The reconstructive project and experiment adjusting methods of facility are given, and low Reynolds number flow field after the reconstruction based on test data is analyzed. In China, it is the first time that aerodynamic performance parameters change under low Reynolds number of a high subsonic speed diffused airfoil are got by means of test.