对民用飞机静压孔布局规律进行了研究.确定相关条例中静压孔的安装使用要求,将其转换成具体的设计分析技术指标;利用数值模拟方法对翼身组合体构型进行气动计算,得到不同状态下机身表面压力分布;对机身表面压力分布均方根进行分析,得到机身表面静压随马赫数、攻角变化较小的区域,定义为稳压线;将机身等直段等效为圆柱体,将来流分解为轴向平直流动和圆柱周向绕流,通过圆柱绕流Cp分布理论分析,获得与计算结果一致的稳压线分布规律,表明稳压线分布规律的普适性.开展高低速测压风洞试验,对稳压线规律进行验证,结果表明稳压线上压力分布变化范围趋近于0,试验结果与CFD计算结果以及理论分析结果高度一致,证明了稳压线计算及分析方法合理、可行,静压孔布局规律的正确、普适.所得稳压线分布规律可为常规布局民用飞机静压孔布局提供直接参考.%Static pressure port orientation for civil aircraft was studied in this paper.Static port is one of the most important air data sensors.It is used to measure local static pressure to calculate airspeed and altitude by air data computer,and the measure performance depends on its installed location. In order to fulfill the static port orientation in HB regulations and airworthiness standards,the corresponding requirements were interpreted into analysis objects. The flow field around a wing-body configuration was simulated by computational fluid dynamics (CFD),and the pressure distributions were obtained in various conditions.The root mean square of the pressure coefficients for all the cases was analyzed,and the area where the pressure coefficient is not sensitive to the Mach number and angle of attack (AOA)was found.This area was defined as the Cp steady line.The forward fuselage was simplified as circular cylinder,and the free stream velocity was decomposed into normal and vertical components.The vertical velocity component around the circular cylinder was analyzed theoretically,and the Cp steady line was found as same as that from the simulation result.This behavior means that the Cp steady line is universality.High speed and low speed pressure measurement experiments were conducted to validate the Cp steady line rule.The variation of the pressure coefficient almost equals to zero on the Cp steady line with varying Mach numbers and AOAs.The results have good agreement with the CFD solutions and theoretical results,and it is indicated that the analysis methods and relevant static port installing rule are applicable and possess universality.Furthermore,the obtained method and rule have the potential of applying to other aircrafts with similar configuration.
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