【摘要】：激波與邊界層干擾的非定常問題是高速飛行器氣動設(shè)計中基礎(chǔ)研究內(nèi)容之一.以往研究主要針對層流和湍流干擾,在分離激波低頻振蕩及其內(nèi)在機(jī)理方面存在著上游機(jī)制和下游機(jī)制兩類截然不同的理論解釋.分析激波與轉(zhuǎn)捩邊界層干擾下非定常運(yùn)動現(xiàn)象有助于進(jìn)一步加深理解邊界層狀態(tài)以及分離泡結(jié)構(gòu)對低頻振蕩特性的影響規(guī)律,為揭示其產(chǎn)生機(jī)理指出新的方向.采用直接數(shù)值模擬方法對來流馬赫數(shù)2.9,24?壓縮拐角內(nèi)激波與轉(zhuǎn)捩邊界層干擾下激波的非定常運(yùn)動特性進(jìn)行了數(shù)值分析.通過在拐角上游平板特定的流向位置添加吹吸擾動激發(fā)流動轉(zhuǎn)捩,使得進(jìn)入拐角的邊界層處于轉(zhuǎn)捩初期階段.在驗證了計算程序可靠性的基礎(chǔ)上,詳細(xì)分析了轉(zhuǎn)捩干擾下激波運(yùn)動的間歇性和振蕩特征,著重研究了分離泡展向三維結(jié)構(gòu)對激波振蕩特性的影響規(guī)律,最后還初步探索了轉(zhuǎn)捩干擾下激波低頻振蕩產(chǎn)生的物理機(jī)制.研究結(jié)果表明:分離激波的非定常運(yùn)動仍存在強(qiáng)間歇性和低頻振蕩特征,其時間尺度約為上游無干擾區(qū)內(nèi)脈動信號特征尺度的10倍量級;分離泡展向三維結(jié)構(gòu)不會對分離激波的低頻振蕩特征產(chǎn)生實質(zhì)影響.依據(jù)瞬態(tài)脈動流場的低通濾波結(jié)果,轉(zhuǎn)捩干擾下激波低頻振蕩的誘因來源于拐角干擾區(qū)下游,與流場中分離泡的收縮/膨脹運(yùn)動存在一定的關(guān)聯(lián).
[Abstract]:The unsteady problem of shock wave and boundary layer interaction is one of the basic research contents in aerodynamic design of high-speed aircraft. Previous studies have focused on laminar and turbulent interferences, and there are two distinct theoretical explanations, upstream mechanism and downstream mechanism, on the low-frequency oscillation and its internal mechanism of shock separation. The analysis of unsteady motion phenomenon under the interaction of shock wave and transition boundary layer is helpful to further understand the influence of boundary layer state and separation bubble structure on the low-frequency oscillation characteristics, and to point out a new direction for revealing the mechanism of its generation. By using the direct numerical simulation method, the Mach number of the incoming flow is 2.9, 24? The unsteady motion characteristics of shock wave under the interaction of shock wave in compression angle and transition boundary layer are numerically analyzed. The boundary layer entering the corner is in the initial stage of transition by adding blow-suction disturbance to stimulate the flow transition at the specific direction of the plate upstream of the corner. On the basis of verifying the reliability of the calculation program, the intermittent and oscillatory characteristics of shock wave motion under transition disturbance are analyzed in detail, and the effects of the three-dimensional structure of the separated bubble on the shock oscillation characteristics are emphatically studied. Finally, the physical mechanism of low-frequency oscillation of shock wave caused by transition interference is also discussed. The results show that the unsteady motion of the separated shock still has the characteristics of strong intermission and low frequency oscillation, and its time scale is about 10 times that of the characteristic scale of the pulsating signal in the upstream non-interference region. The three-dimensional structure of the separated bubble will not have a substantial effect on the characteristics of the low-frequency oscillation of the separated shock wave. According to the low-pass filtering results of transient pulsating flow field, the inducement of low-frequency oscillation of shock wave under transition interference comes from the downstream of corner interference region, which is related to the contraction / expansion motion of separated bubbles in the flow field.
【作者單位】： 中國空氣動力研究與發(fā)展中心計算空氣動力所;中國科學(xué)院力學(xué)研究所高溫氣體動力學(xué)國家重點實驗室;中國科學(xué)院大學(xué)工程科學(xué)學(xué)院;
【基金】：國家自然科學(xué)基金資助項目(91441103,11372330,11472278)
【分類號】：V211

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