發(fā)布時間：2018-03-10 20:08

  本文選題：高超聲速進氣道　切入點：邊界層人工轉(zhuǎn)捩　出處：《實驗流體力學》2016年02期 　論文類型：期刊論文

【摘要】：為確保高超聲速進氣道的安全工作,其壓縮面邊界層在進入其內(nèi)流道前必須完成轉(zhuǎn)捩。針對高超聲速進氣道邊界層轉(zhuǎn)捩需要,依據(jù)二維高超聲速邊界層轉(zhuǎn)捩機理,嘗試了一種新型低阻高效的邊界層人工轉(zhuǎn)捩方法,在FD-07風洞中開展了試驗驗證。試驗中首先通過進氣道對稱面壓力分布和激波紋影獲得進氣道的自起動情況,進而推斷進氣道入口前的邊界層轉(zhuǎn)捩情況。試驗包括進氣道前體邊界層自然轉(zhuǎn)捩和人工轉(zhuǎn)捩,試驗結(jié)果表明在Ma=5、6,迎角α=0°來流條件下,使用同一波長的人工轉(zhuǎn)捩帶可以成功實現(xiàn)進氣道邊界層轉(zhuǎn)捩,驗證了基于線性穩(wěn)定性理論設計的人工轉(zhuǎn)捩帶在寬馬赫數(shù)范圍的適用性。
[Abstract]:In order to ensure the safe operation of hypersonic inlet, the boundary layer of hypersonic inlet must complete the transition before entering its inner channel. According to the mechanism of two-dimensional hypersonic boundary layer transition, the hypersonic inlet boundary layer transition needs to be met. A new method of artificial boundary layer transition with low resistance and high efficiency was tried and tested in FD-07 wind tunnel. The self-starting of the inlet was obtained by the symmetrical plane pressure distribution of the inlet and the ripple shadow of the inlet. Furthermore, the boundary layer transition before inlet inlet is inferred. The experiment includes natural transition and artificial transition of inlet precursor boundary layer. The experimental results show that under the condition of Maxi 5, 0 擄angle of attack, The artificial transition band of the same wavelength can successfully realize the boundary layer transition of the inlet, which verifies the applicability of the artificial transition band designed based on the linear stability theory in the wide Mach number range.
【作者單位】： 中國航天空氣動力技術(shù)研究院;
【基金】：航天技術(shù)自主研發(fā)基金
【分類號】：V211.48

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本文編號：1594875