CAJ | 학술논문

静压孔气动布局方案设计的首要工作是寻找合适的布置区域，使得静压孔的位置误差尽量降低并规律可控，以利于后期静压源误差修正曲线的试飞获取。首先分析得到静压孔的位置误差实际上主要受飞行马赫数和飞行迎角影响；然后利用商用 CFD 软件计算了某现代民机在不同飞行马赫数和迎角下的机身表面静压分布，对计算结果的统计处理显示机身表面规律性的存在静压恢复系数对迎角变化的不敏感区。根据结果，提出了该不敏感区宜于作为机身表面静压孔安装位置选取的参考基线，随后的风洞试验验证了基于上述原则选取的静压孔初步安装位置。全文提出并发展的基于静压场数值计算及结果统计后处理的方法为表面静压孔的气动布局定位提供了一种定量直观的新思路。
정압공기동포국방안설계적수요공작시심조합괄적포치구역，사득정압공적위치오차진량강저병규률가공，이리우후기정압원오차수정곡선적시비획취。수선분석득도정압공적위치오차실제상주요수비행마혁수화비행영각영향；연후이용상용 CFD 연건계산료모현대민궤재불동비행마혁수화영각하적궤신표면정압분포，대계산결과적통계처리현시궤신표면규률성적존재정압회복계수대영각변화적불민감구。근거결과，제출료해불민감구의우작위궤신표면정압공안장위치선취적삼고기선，수후적풍동시험험증료기우상술원칙선취적정압공초보안장위치。전문제출병발전적기우정압장수치계산급결과통계후처리적방법위표면정압공적기동포국정위제공료일충정량직관적신사로。
Flush-mounted static ports are widely used to sense ambient static pressure on modern subsonic commercial transport aircrafts.From aerodynamic perspectives,controlling the local position error mainly due to placement of static ports is the first step to obtain satisfied stat-ic pressure accuracy in practical design.It is found that position error at given location is mainly affected by flight Mach number and angle of attack.A comprehensive CFD study is consequently carried out to investigate the static pressure dependencies on Mach number and angle of attack for a typical commercial transport aircraft.A region insensitivity to angle of attack is discovered on the fuselage by some statistic post-processing of the CFD results.This insensitivity region is then identified as a baseline for placing the flush static ports.The thereout preliminary positions are verified by wind tunnel tests.Numerical simulation and associated statistical post-processing on the static pressure fields actually provide a novel and quantitative approach for determining static ports locations.