INVESTIGATION ON THE HEAT FLUX REDUCTION CHARACTERISTICS OF THE LOCAL BULGES IN THE V-SHAPED BLUNT LEADING EDGE
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摘要:三维内转式进气道的唇口结构通常存在复杂的激波干扰及严酷的气动热载荷, 严重威胁高超声速飞行器的性能与安全. 在6.0马赫的高超声速流动中, 以V形钝前缘模型为研究对象, 设计了局部凸起的被动流动控制降热方案. 采用数值模拟手段, 首先研究了局部凸起方案的降热能力以及降热原理, 然后初步优化了局部凸起的位置、高度以及宽度等关键设计参数, 最后分析了优化后的局部凸起方案的攻角、侧滑角及马赫数的适用性. 研究结果表明: 上游凸起边缘形成的斜激波与主马赫反射结构形成的透射激波发生干扰, 能够减弱其冲击壁面的强度, 实现降热的目的; 驻点凸起通过改变超声速射流的对撞角度, 能够降低其对撞的强度, 实现降热的目的. 原始方案的降热能力约为37.75%, 在对局部凸起的关键设计参数进行初步优化后, 优化方案的降热能力将提升至44.60%. 设计工况下的优化方案具有良好的攻角适用性, 而高度可变的优化方案可以较好地适用于有侧滑角及高马赫数的流动. 在研究范围内, 高度可变的优化局部凸起方案的降热能力均高于20%.Abstract:Complex shock interaction structures and severe aerothermal heating loads are usually encountered on the lips of the three-dimensional inward-turning inlet, which seriously threatens the performance and safety of the hypersonic flight vehicle. The passive heat flux reduction scheme with the local bulge is designed based on the simplified model of the V-shaped lip, the V-shaped blunt leading edge. By performing numerical simulations, the heat flux reduction ability and the heat flux reduction principle of the local bulge scheme are researched at Mach number of 6.0. Then, the key design parameters of the scheme, which include the position, the height, and the width of the local bulge, are preliminarily optimized. Finally, the applicability of the optimized scheme in terms of attack angle, sideslip angle, and Mach number is analyzed. The oblique shocks formed at the edges of the upstream bulge interact with the transmitted shock formed by the primary Mach reflection structure, which can weaken the intensity of the transmitted shock impinging on the wall and achieve the purpose of heat flux reduction. By changing the collision angle of the supersonic jets, the stagnation bulge can reduce the collision intensity of the jets and achieve the purpose of heat flux reduction as well. The heat flux reduction ability of the original local bulge scheme is about 37.75%. After preliminarily optimizing the key design parameters of the local bulge scheme, the heat flux reduction ability of the optimized local bulge scheme can be increased to 44.60%. The optimized scheme under design condition has excellent applicability of attack angle. Meanwhile, the optimized scheme with changeable height can be well applied to the flow with sideslip angles or high freestream Mach numbers. Within the research scope of this work, the heat flux reduction ability of the optimized local bulge scheme with changeable height is higher than 20%.
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图 3Ma∞= 6.0时, V形钝前缘模型的流动特性分析
Figure 3.Analysis of flow field characteristics of V-shaped blunt leading edge atMa∞= 6.0
图 4局部凸起方案的几何模型及参数示意图
Figure 4.Schematics of geometric models and parameters of the local bulge schemes
图 5两个局部凸起方案的对称面数值纹影及壁面热流分布
Figure 5.Numerical schlieren in the symmetry plane and the surface heat flux distribution of the two local bulge schemes
图 6波系干扰区域的对称面流线及压力分布对比
Figure 6.Comparison of the streamline and pressure distribution in the shock interaction region
图 7倒圆区域各周向角站位的壁面截线上的热流最大值的分布
Figure 7.Distribution of the maximum surface heat flux values at each circumferential angle slice along the crotch
图 9改变局部凸起位置对LB方案降热能力的影响
Figure 9.Effect of changing the position of local bulges on the heat flux reduction ability of LB scheme
图 10改变局部凸起高度对LB方案降热能力的影响
Figure 10.Effect of changing the height of local bulges on the heat flux reduction ability of LB scheme
图 11最优局部凸起高度的LB方案的流场结构
Figure 11.Flow field structures of LB scheme with the optimal height of local bulges
图 12改变局部凸起宽度对LB方案降热能力的影响
Figure 12.Effect of changing the width of local bulges on the heat flux reduction ability of LB scheme
图 135°攻角时, LB(48-0.16-0.16)方案的降热能力
Figure 13.Heat flux reduction ability of the LB(48-0.16-0.16) scheme at attack angle of 5°
图 145°侧滑角时, 原始模型及不同LB方案的流场结构
Figure 14.Flow field structures of the original model and different LB schemes at sideslip angle of 5°
图 155°侧滑角时, 不同LB方案的降热能力
Figure 15.Heat flux reduction ability of different LB schemes at sideslip angle of 5°
图 1610.0马赫数时, 原始模型及不同LB方案的流场结构
Figure 16.Flow field structures of the original model and different LB schemes at Mach number of 10.0
图 1710.0马赫时, 不同LB方案的降热能力
Figure 17.Heat flux reduction ability of different LB schemes at Mach number of 10.0
图 18理想气体假设下, 原始模型及LB(48-0.20-0.09)方案的流场结构
Figure 18.Flow field structures of the original model and LB(48-0.20-0.09) schemes under ideal gas assumption
表 1V形钝前缘的几何参数
Table 1.Geometric parameters of V-shaped blunt leading edge
Name Symbol Value straight branch length L/mm 60 half-span angle β/(°) 24 regular curvature radius R/mm 6.5 leading edge bluntness radius r/mm 2 circumferential angle of crotch Φ/(°) 66 
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表 2网格无关性验证的网格设置
Table 2.Grid settings for grid independence verification
Case ξ×ζ×ψ Total cell number Surface cell
thickness/mmRec coarse grid 171 × 489 × 101 ~ 8.3 × 106 1.22 × 10−3 6.83 fine grid 221 × 545 × 110 ~ 1.3 × 107 9.16 × 10−4 5.13 dense grid 250 × 581 × 125 ~ 1.8 × 107 9.16 × 10−4 5.13 下载:
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表 3局部凸起方案的几何参数
Table 3.Geometric parameters of the local bulge schemes
Geometric parameters Scheme I Scheme II h1/mm 0.15 0.15 θ1/(°) 10.00 10.00 h2/mm 0.15 0.15 η/(°) 50.00 — θ2/(°) 10.00 — l/mm — 3.00 w/mm — 1.484 下载:
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