空气动力学学报
空氣動力學學報
공기동역학학보
ACTA AERODYNAMICA SINICA
2010年
2期
197-202
,共6页
吴继飞%陶洋%范召林%罗新福
吳繼飛%陶洋%範召林%囉新福
오계비%도양%범소림%라신복
空腔%流场类型%压力梯度%空腔能量尖峰
空腔%流場類型%壓力梯度%空腔能量尖峰
공강%류장류형%압력제도%공강능량첨봉
cavity%flow type%pressure gradient%cavity tones
本文以风洞试验为手段,在高速风洞中对空腔流场特性进行了较为深入的研究,通过对空腔底部静态压力以及脉动压力的测量,分析后缘修型对腔底流场特性的影响.研究结果表明,后缘修型对空腔流场特性影响随修型半径增大而增强;当空腔流场类型为开式穴流动、过渡式穴流动和闭式穴流动,后缘修型对腔内静态压力分布的影响不大,而当空腔流场为过渡--开式穴流动时,后缘修型可能使空腔的流场类型发生转变并使静态压力梯度明显增大;研究结果还表明,后缘修型能有效降低腔内的噪声强度,但对空腔能量尖峰的抑制效果会因试验条件的改变而产生差异.
本文以風洞試驗為手段,在高速風洞中對空腔流場特性進行瞭較為深入的研究,通過對空腔底部靜態壓力以及脈動壓力的測量,分析後緣脩型對腔底流場特性的影響.研究結果錶明,後緣脩型對空腔流場特性影響隨脩型半徑增大而增彊;噹空腔流場類型為開式穴流動、過渡式穴流動和閉式穴流動,後緣脩型對腔內靜態壓力分佈的影響不大,而噹空腔流場為過渡--開式穴流動時,後緣脩型可能使空腔的流場類型髮生轉變併使靜態壓力梯度明顯增大;研究結果還錶明,後緣脩型能有效降低腔內的譟聲彊度,但對空腔能量尖峰的抑製效果會因試驗條件的改變而產生差異.
본문이풍동시험위수단,재고속풍동중대공강류장특성진행료교위심입적연구,통과대공강저부정태압력이급맥동압력적측량,분석후연수형대강저류장특성적영향.연구결과표명,후연수형대공강류장특성영향수수형반경증대이증강;당공강류장류형위개식혈류동、과도식혈류동화폐식혈류동,후연수형대강내정태압력분포적영향불대,이당공강류장위과도--개식혈류동시,후연수형가능사공강적류장류형발생전변병사정태압력제도명현증대;연구결과환표명,후연수형능유효강저강내적조성강도,단대공강능량첨봉적억제효과회인시험조건적개변이산생차이.
An experimental investigation was conducted in a high speed wind tunnel to explore cavity flow characteristics.Detailed static-pressure and fluctuating pressure measurements were obtained at the cavity floor to enable the effect of the modification at the trailing edge to be determined.Results indicate that the modification has no obvious effect on static pressure distributions if the cavity flow type is the open flow, transitional flow or closed flow.Bat the cavity flow type may be changed and the cavity static pressure gradi-ent may be increased remarkably by the modification if the cavity flow type is transitional/open flow.The study also indicates that the modification can reduce the intensity of noise markedly, but its effect on cavity tones depending on test conditions.