本文選題：壁壓 + 洞壁干擾��； 參考：《空氣動(dòng)力學(xué)學(xué)報(bào)》2016年01期

【摘要】：為了滿足現(xiàn)代風(fēng)洞試驗(yàn)精細(xì)化要求,提高風(fēng)洞試驗(yàn)數(shù)據(jù)精準(zhǔn)度,開(kāi)展跨聲速開(kāi)孔壁洞壁干擾修正方法研究。本文利用實(shí)測(cè)壁壓信息構(gòu)造開(kāi)孔壁邊界條件,通過(guò)求解N-S方程,模擬試驗(yàn)?zāi)Ｐ驮陲L(fēng)洞中的繞流場(chǎng),建立基于壁壓信息的跨聲速洞壁干擾非線性修正方法。不同于線性修正方法,本方法可用于各種復(fù)雜外形飛行器的亞、跨聲速開(kāi)孔壁洞壁干擾修正,結(jié)合小展弦比飛翼標(biāo)模風(fēng)洞試驗(yàn)數(shù)據(jù),對(duì)其在FL-2風(fēng)洞試驗(yàn)數(shù)據(jù)開(kāi)展洞壁干擾特性研究。洞壁干擾修正結(jié)果表明,洞壁干擾量隨馬赫數(shù)變化呈增長(zhǎng)趨勢(shì),Ma=1.0左右達(dá)最大,經(jīng)過(guò)修正的FL-2風(fēng)洞的跨聲速試驗(yàn)結(jié)果,與FL-26風(fēng)洞近似無(wú)干擾試驗(yàn)結(jié)果吻合良好。
[Abstract]:In order to meet the requirements of modern wind tunnel test and improve the accuracy of wind tunnel test data, the transonic wall interference correction method was studied. In this paper, the boundary conditions of the open hole wall are constructed by using the measured wall pressure information. By solving the N-S equation and simulating the flow field around the wind tunnel, a nonlinear correction method of transonic wall interference based on the wall pressure information is established. Different from the linear correction method, this method can be used for the subsonic and transonic wall interference correction of aircraft with complex shapes, and combined with the wind tunnel test data of small aspect ratio flying wing. The wall interference characteristics of FL-2 wind tunnel test data are studied. The results of wall interference correction show that the volume of wall interference increases with Mach number to the maximum. The modified FL-2 wind tunnel transonic velocity test results are in good agreement with the FL-26 wind tunnel approximate non-interference test results.
【作者單位】： 中國(guó)航空工業(yè)空氣動(dòng)力研究院高速高雷諾數(shù)氣動(dòng)力航空科技重點(diǎn)實(shí)驗(yàn)室;
【分類號(hào)】：V211.74
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本文編號(hào)：1859860