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281.
282.
将矩阵预处理方法与多重网格方法结合,发展了适用于机翼及复杂外形气动数值优化设计的高效数值模拟方法和程序。在不改变定常流动解的前提下,对 Navier-Stokes 方程的时间导数项实施 Choi-Merkle 矩阵预处理,从而改善可压缩控制方程在低速情况下的系统刚性。Choi-Merkle 预处理最初用于二维低马赫数粘性流动数值模拟,本文将其推广应用到计算三维流动,并针对提高跨音速流动计算收敛性进行了相应的改进。预处理后控制方程采用中心格式有限体积进行空间离散,Runge-Kutta 混合多步方法进行显式时间推进求解,并应用 FAS 多重网格方法加速收敛。采用所发展的方法和程序数值模拟了绕 M6 机翼和 M100 机翼的低速和跨音速流动(马赫数从0.01 到 0.839)以及绕 F4 翼身组合体流动。计算结果与实验值吻合良好,验证了所发展的方法的正确性。算例研究表明所发展方法较大幅度地提高了三维流动数值模拟的效率,且同时适用于可压和不可压流动计算,在机翼及复杂外形气动优化设计方法具有应用前景 相似文献
283.
1.引言 在电磁散射计算问题中,过去研究较多的是高频情况,所用方法通常是几何绕射法、光学法等。用矩量法计基电磁散射问题,60年代提出了网格法。这种方法多用于尺寸较小的物体,如线天线、小平板等。l984年美国人用矩量法计算了飞机、导弹等的雷达截 相似文献
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《中国航空学报》2023,36(3):96-106
The interactions of oblique/bow shock waves are the key flow phenomena restricting the design and aerothermodynamic performance of high-speed vehicles. Type III and Type IV Shock/Shock Interactions(SSIs) have been extensively investigated, as such interactions can induce abnormal aerodynamic heating problems in hypersonic flows of vehicles. The transition process between these two distinct types of shock/shock interactions remains unclear. In the present study, a subclass of shock/shock interaction configuration is revealed and defined as Type IIIa. Type IIIa interaction can induce much more severe aerodynamic heating than a Type IV interaction which was ever reported to be the most serious in literature. The intense aerodynamic heating observed in this configuration highlights a new design point for the thermal protection system of hypersonic vehicles. A secondary Mach interaction between shock waves in the supersonic flow path of a Type III configuration is demonstrated to be the primary mechanism for such a subclass of shock/shock interaction configuration. 相似文献
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Yinxin ZHU Wenqiang PENG Zhenbing LUO Qiang LIU Wei XIE Pan CHENG Yan ZHOU 《中国航空学报》2023,36(7):366-377
To effectively reduce the loss of strong shock wave at the trailing edge of the supersonic cascade under high backpressure, a shock wave control method based on self-sustaining synthetic jet was proposed. The self-sustaining synthetic jet was applied on the pressure side of the blade with the blow slot and the bleed slot arranged upstream and downstream of the trailing-edge shock,respectively. The flow control mechanism and effects of parameters were investigated by numerical simulation. The res... 相似文献
289.
《中国航空学报》2023,36(8):24-31
Mach number effects on the near-wall turbulence in the absence of outer motions remain unclear so far. The present study extends the Minimal Flow Units (MFUs), a widely applied method to investigate near-wall turbulence free from the impact of large-scale motions in the outer region in incompressible channel flows, to compressible wall-bounded turbulence. The compressible near-wall turbulence in MFU proves accurate in replicating near-wall statistics, independent of Mach number and statistically equivalent to the universal signals extracted from the full-sized channel. It is further utilized as universal signals in the predictive models of compressible near-wall turbulence, which is capable of accurately predicting variances and joint probability density functions of velocity and temperature fluctuations. 相似文献
290.
《中国航空学报》2023,36(4):75-78
Symmetric Mach reflection in steady supersonic flow has been usually studied by solving a half-plane problem with the symmetric line treated as reflecting surface, thus losing the opportunity to discover antisymmetric flow structures. Here in this paper we treat this problem as an entire-plane problem. Using an unsteady numerical approach, we find that the two sliplines exhibit antisymmetric unsteadiness if the Mach stem height is small while the flow remains symmetric if the Mach stem height is large. The mechanism by which disturbance, generated in the downstream of the flow duct between the two sliplines, propagates upstream is identified and it is also shown that the interaction between the transmitted expansion waves and the sliplines increases the amplitude of the unstable modes. The present study suggests a new type of compressible jet that deserves further studies. 相似文献