本文選題：高超聲速飛機 + 吸氣式飛行器　； 參考：《力學學報》2016年02期

【摘要】：為探索前緣線變化對吸氣式高超聲速飛機氣動性能的影響,基于一種旁側進氣布局翼身融合體構型,在飛行馬赫數6,攻角4?和高度26 km的巡航飛行條件下,結合運用增量修正參數化設計方法、均勻實驗設計方法和計算流體力學模擬,分析了飛行器前緣型線與其升阻力系數及縱向壓心等性能參數間的關系.計算結果表明,前緣線形狀對飛行器升阻力系數明顯高于其對縱向壓心影響,設計空間范圍內升力系數變化約21.3%,阻力系數變化約31.8%,升阻比變化范圍約10.63%,但相對壓心變化范圍僅為3.87%.在此基礎上,通過對典型構型物面壓力分布進行分析,發(fā)現前緣線形狀適當彎曲可利用飛行器下表面?zhèn)缺趬嚎s產生的高壓氣流,利用二者的耦合效應使飛行器獲得額外的升力增量.
[Abstract]:In order to explore the effect of the change of leading edge line on the aerodynamic performance of hypersonic aspirated aircraft, based on a flanking intake configuration, the flight Mach number 6, attack angle 4? Combined with incremental modified parametric design method, uniform experimental design method and computational fluid dynamics simulation. The relationship between the leading edge profile of the aircraft and the performance parameters such as lift resistance coefficient and longitudinal pressure center is analyzed. The calculated results show that the influence of the shape of the leading edge line on the lift resistance coefficient of the aircraft is obviously higher than that on the longitudinal center of the vehicle. In the design space, the lift coefficient changes about 21.3g, the resistance coefficient about 31.8and the rise-to-drag ratio about 10.63, but the relative pressure center is only 3.87. On the basis of this, by analyzing the pressure distribution of the typical configuration, it is found that the high pressure airflow produced by the compression of the side wall of the lower surface of the aircraft can be used in the proper bending of the leading edge line. Using the coupling effect, the aircraft can obtain additional lift increment.
【作者單位】： 中國科學院力學研究所高溫氣體動力學國家重點實驗室;中國空氣動力研究與發(fā)展中心;中國航天科工集團31研究所;
【基金】：國家自然科學基金資助項目(11372324,11572333)
【分類號】：V221.3

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