某型直升机机体气动特性风洞试验研究  

Investigation on the Airframe Aerodynamic Characteristics of One Helicopter in Wind Tunnel Test

作　　者：张青竹 张德平 林长亮 Zhang Qingzhu;Zhang Deping;Lin Changliang(AVIC Harbin Aircraft Industry Group,Harbin 150066,China)

机构地区：[1]航空工业哈尔滨飞机工业集团有限责任公司,黑龙江哈尔滨150066

出　　处：《气动研究与试验》2024年第2期97-102,共6页Aerodynamic Research & Experiment

摘　　要：本文介绍了某型直升机试验风洞、模型、支架、天平以及模型/支架和支架/天平的安装方式,研究了机体全向气动特性和各部件气动特性,定性评估了平尾气动环境、机体表面附近流场和机身下表面分离对直升机飞行特性的影响。试验研究表明,所使用的常规支架和专用支架适用于机体全向气动特性风洞试验;机身对平尾的气动干扰是可接受的;在侧滑角β=0°、迎角α=-72°附近的纵向气动特性突变是可以接受的,其产生的原因是机身下表面的突然分离;机体附近流场虽然有局部分离,但气流是稳定的。The paper introduces the wind tunnel,model,holder,aerodynamic balance and the installation of the model/holder and the holder/aerodynamic balance for one helicopter.By investigating the omnidirectional aerodynamic characteristics of the airframe and the aerodynamic characteristics of each aerodynamic component,qualitatively evaluates the airflow environment close to the horizontal tail and the flow field near the surface of the fuselage as well as the influence of flow field separation close to the lower surface on helicopter flight characteristics.Tests show that both ordinary holder and special holder used are suitable for the wind tunnel test to obtain the omnidirectional aerodynamic characteristics of the airframe;the aerodynamic interference of the fuselage on the horizontal tail is acceptable;the sudden change of the longitudinal aerodynamic characteristics is acceptable,which is caused by the suddenly separated flow around the bottom of the fuselage at sideslip angleβ=0°and angle of attackα=-72°;although the flow field around the airframe separated locality,the flow is stable.

关 键 词：直升机模型 机体 机身 平尾 风洞试验 风速 迎角 侧滑角 

分 类 号：V221.3[航空宇航科学与技术—飞行器设计]