本文選題：BLI進(jìn)氣道 + 流動(dòng)特性��； 參考：《南京航空航天大學(xué)》2016年碩士論文

【摘要】：BLI進(jìn)氣道是一類不采用邊界層隔道、與機(jī)體結(jié)構(gòu)融合的進(jìn)氣道,特別適用于翼身融合體飛行器。本文設(shè)計(jì)了一種BLI進(jìn)氣道,并對(duì)其展開了模擬外流條件下的仿真研究,獲得了其流動(dòng)特性。在此基礎(chǔ)上,設(shè)計(jì)并搭建了BLI進(jìn)氣道雙流路地面抽吸實(shí)驗(yàn)臺(tái),通過(guò)仿真驗(yàn)證了實(shí)驗(yàn)臺(tái)流動(dòng)與待模擬流動(dòng)的一致性。另外,本文還對(duì)BLI進(jìn)氣道進(jìn)行了初步的實(shí)驗(yàn)研究,所獲結(jié)果和仿真結(jié)果基本一致。仿真和實(shí)驗(yàn)研究表明,由于吸入了大量的來(lái)流邊界層,BLI進(jìn)氣道內(nèi)形成了不同于無(wú)邊界層吸入的常規(guī)S彎進(jìn)氣道的特殊流動(dòng)結(jié)構(gòu):BLI進(jìn)氣道的進(jìn)口段流場(chǎng)主要受鈍體繞流與邊界層相互干擾作用,流場(chǎng)中鞍點(diǎn)和分離線的數(shù)目、位置均隨出口馬赫數(shù)的變化而變化;在內(nèi)通道中,吸入的邊界層在下壁面附近堆積,在第二彎段后半段,邊界層內(nèi)的二次流逐漸發(fā)展成對(duì)渦,并將低能流卷向截面中間,最終在出口截面的中下半部形成了低總壓區(qū);并且,出口馬赫數(shù)越低、來(lái)流馬赫數(shù)越高、吸入的來(lái)流邊界層越厚,出口截面上的低能流堆積就越嚴(yán)重,對(duì)渦影響范圍越大,總壓恢復(fù)系數(shù)ζ也越低。在不同工況下,BLI進(jìn)氣道的性能參數(shù)隨出口馬赫數(shù)的變化規(guī)律基本一致:隨著出口馬赫數(shù)的升高,BLI進(jìn)氣道總壓恢復(fù)系數(shù)ζ先升高后降低,而常規(guī)S彎進(jìn)氣道的ζ則隨之單調(diào)下降。另外,實(shí)驗(yàn)臺(tái)的仿真校驗(yàn)和初步實(shí)驗(yàn)均表明,其可較為真實(shí)地模擬帶外流條件下BLI進(jìn)氣道的流動(dòng)特性,并可獲得不同的來(lái)流馬赫數(shù)、出口馬赫數(shù)、來(lái)流邊界層厚度等流動(dòng)條件,因此該實(shí)驗(yàn)臺(tái)的設(shè)計(jì)是成功的。
[Abstract]:The BLI inlet is a kind of inlet which does not use the boundary layer septum and is fused with the airframe structure. It is especially suitable for the wing body fusion vehicle. In this paper, a BLI inlet is designed, and its flow characteristics are obtained. On this basis, a two-way ground suction test bench for BLI inlet is designed and built, and the consistency between the experimental bed and the simulated flow is verified by simulation. In addition, a preliminary experimental study of the BLI inlet is carried out, and the results obtained are in good agreement with the simulation results. Simulation and experimental studies show that, The inlet flow field of the inlet is mainly affected by the interaction between the blunt body and the boundary layer due to the formation of a special flow structure in the inlet of the BLI inlet which is different from the conventional S-bend inlet without boundary layer inhalation. The flow field in the inlet section of the inlet is mainly affected by the interaction between the blunt body and the boundary layer. The number and position of saddle points and separation lines in the flow field vary with the Mach number at the exit. In the inner channel, the inhaled boundary layer accumulates near the lower wall, and in the second half of the second bend, the secondary flow in the boundary layer gradually develops into a pair of vortices. The lower the Mach number is, the higher the Mach number is, and the thicker the boundary layer of incoming flow is. The more serious the accumulation of low energy flow on the exit section is, the greater the range of influence on the vortex is, and the lower the recovery coefficient 味 of the total pressure is. Under different operating conditions, the performance parameters of the BLI inlet vary with the outlet Mach number. With the increase of the outlet Mach number, the total pressure recovery coefficient 味 of the BLI inlet increases first and then decreases, while that of the conventional S-curved inlet decreases monotonously. In addition, the simulation and preliminary experiments of the test bench show that the flow characteristics of the BLI inlet can be simulated more truthfully under the condition of the outflow, and the flow conditions such as the Mach number of the incoming flow, the Mach number of the outlet, the thickness of the boundary layer of the incoming flow can be obtained. Therefore, the design of the experimental platform is successful.
【學(xué)位授予單位】：南京航空航天大學(xué)
【學(xué)位級(jí)別】：碩士
【學(xué)位授予年份】：2016
【分類號(hào)】：V211.48

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1 寧樂(lè);BLI進(jìn)氣道流動(dòng)特性的地面模擬方法和初步實(shí)驗(yàn)研究[D];南京航空航天大學(xué);2016年

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本文編號(hào)：1860236