本文選題：壁壓 + 洞壁干擾��； 參考：《空氣動力學學報》2016年01期

【摘要】：為了滿足現(xiàn)代風洞試驗精細化要求,提高風洞試驗數(shù)據(jù)精準度,開展跨聲速開孔壁洞壁干擾修正方法研究。本文利用實測壁壓信息構造開孔壁邊界條件,通過求解N-S方程,模擬試驗模型在風洞中的繞流場,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雜外形飛行器的亞、跨聲速開孔壁洞壁干擾修正,結合小展弦比飛翼標模風洞試驗數(shù)據(jù),對其在FL-2風洞試驗數(shù)據(jù)開展洞壁干擾特性研究。洞壁干擾修正結果表明,洞壁干擾量隨馬赫數(shù)變化呈增長趨勢,Ma=1.0左右達最大,經(jīng)過修正的FL-2風洞的跨聲速試驗結果,與FL-26風洞近似無干擾試驗結果吻合良好。
[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】： 中國航空工業(yè)空氣動力研究院高速高雷諾數(shù)氣動力航空科技重點實驗室;
【分類號】：V211.74
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本文編號：1859860