本文選題：高超聲速進(jìn)氣道　切入點(diǎn)：邊界層人工轉(zhuǎn)捩　出處：《實(shí)驗(yàn)流體力學(xué)》2016年02期 　論文類型：期刊論文

【摘要】：為確保高超聲速進(jìn)氣道的安全工作,其壓縮面邊界層在進(jìn)入其內(nèi)流道前必須完成轉(zhuǎn)捩。針對(duì)高超聲速進(jìn)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(jī)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(fēng)洞中開展了試驗(yàn)驗(yàn)證。試驗(yàn)中首先通過(guò)進(jìn)氣道對(duì)稱面壓力分布和激波紋影獲得進(jìn)氣道的自起動(dòng)情況,進(jìn)而推斷進(jìn)氣道入口前的邊界層轉(zhuǎn)捩情況。試驗(yàn)包括進(jìn)氣道前體邊界層自然轉(zhuǎn)捩和人工轉(zhuǎn)捩,試驗(yàn)結(jié)果表明在Ma=5、6,迎角α=0°來(lái)流條件下,使用同一波長(zhǎng)的人工轉(zhuǎn)捩帶可以成功實(shí)現(xiàn)進(jìn)氣道邊界層轉(zhuǎn)捩,驗(yàn)證了基于線性穩(wěn)定性理論設(shè)計(jì)的人工轉(zhuǎn)捩帶在寬?cǎi)R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(guó)航天空氣動(dòng)力技術(shù)研究院;
【基金】：航天技術(shù)自主研發(fā)基金
【分類號(hào)】：V211.48

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本文編號(hào)：1594875