摘要
该洞壁干扰修正方法以实测的洞壁附近的压力分布作为边界条件；要求来流和洞壁附近的Ｍａｃｈ数都小于１；但允许模型附近出现局部超音速区和激波。它适用于各种透气壁或实壁实验段。应用该方法对国外三个模型的实验数据进行了洞壁干扰修正计算，修正结果与ＮＡＳＡ非线性洞壁干扰修正方法的结果十分接近或完全吻合。该方法已用于Ｂ７３７模型在１．２ｍ风洞中实验数据的洞壁干扰修正，其结果显示该方法适用于大展弦比飞机的跨音速风洞实验数据修正。
The correction method uses the static pressures measured near the tunnel walls during modeI tests as boundary conditions.It is required that the flow near the walls is subsonic and the freestream Mach number is less than 1.It is still valid when there are shock waves and supersonic pockets near the model as long as shock waves do not extend to walls and applicable to various ventilated wall or solid wall test sections. Corrections for three models tested abroad are in quite good agreement with NASA’s resuIts,which are obtained by a non一linear correction method.The present method has been applied to B737 model tested in CARDC 1.2m wind tunnel.The results show that this method is applicable to transonic wall interference correction for highaspect一ratio airplane tests.
出处
《航空学报》
EI
CAS
CSCD
北大核心
1994年第2期129-135,共7页
Acta Aeronautica et Astronautica Sinica
关键词
气动力干扰
跨音速
风洞
壁面压力
aerodynamic interference,transonic wind tunnels,wall pressure,data reduction
