Numerical simulation on the effect characteristics of belly temperature rise for short/vertical takeoff and landing aircraft proximity of ground
-
摘要:
通过计算流体力学方法和响应面法获得了机腹温升关于喷管落压比、来流速度及喷管出口离地高度的2阶响应曲面回归方程，以及显著影响飞机机腹温升的关键因素。分析了喷管落压比、来流速度和喷管出口离地高度对飞机机腹温升的交互影响作用，并得到了给定工况范围内机腹温升最大的工况。研究表明：仅考虑单因素影响时，机腹温升随落压比、来流速度和喷管出口离地高度的增大而减小；考虑两因素交互作用时，只有高度与落压比对机腹存在交互影响；考虑单因素2阶影响时，喷管出口离地高度、来流速度和喷管落压比均对机腹温升存在2阶效应。优化获得的机腹温升最大的工作点是尾喷管出口离地高度为3倍尾喷管出口直径、喷管落压比为2、来流速度为0 m/s，此时的机腹温度变化为13.92%。
-
关键词:
- 短距/垂直起降（S/VTOL） /
- 机腹温升 /
- 响应面 /
- 交互作用 /
- 2阶效应
Abstract:The two-order response surface regression functions of the belly temperature rise of the aircraft about the nozzle pressure ratio (NPR), inflow velocity and the height of the nozzle exit were obtained by CFD method and the response surface method, and the key factors significantly affecting the belly temperature rise were also acquired. The interaction effects of NPR, inflow velocity and height of nozzle exit above ground on aircraft belly temperature rise were analyzed, and the maximum belly temperature rise in certain range working state was obtained. The study showed that when considering single factor the belly temperature rise decreased with the increase NPR, inflow velocity and the height of nozzle exit above the ground. When considering the interaction of the two factors, only height and NPR had interaction effects on the belly. When considering the two-order influence of single factor, there were two order effects of height of nozzle exit, inflow velocity and NPR. According to the maximum belly temperature rise obtained by optimization, the height of rear nozzle exit above ground was treble the diameter of rear nozzle exit, the NPR was 2, and the inflow velocity was 0 m/s. In this case, the belly temperature change was 13.92%.
-
图 1 S/VTOL飞机缩比模型及边界条件
Figure 1. Scale model of S/VTOL aircraft and boundary conditions
图 2 不同湍流模型下冲击面中轴线压力分布
Figure 2. Pressure distribution on the central axis of impact surface under different turbulence models
图 6 不同落压比下计算域子午面速度及流线分布
Figure 6. Velocity and streamline distribution on meridian plane of computational domain under different nozzle pressure ratios
图 7 不同落压比下机腹无量纲温度分布
Figure 7. Non-dimensional temperature distribution of belly under different nozzle pressure ratios
图 8 不同流速下计算域子午面速度及流线分布
Figure 8. Velocity and streamline distribution on meridian plane of computational domain under different inflow velocities
图 9 不同流速下机腹无量纲温度分布
Figure 9. Non-dimensional temperature distribution of belly under different inflow velocities
图 10 H/D=9时计算域子午面速度及流线分布
Figure 10. Velocity an streamline distribution on meridian plane of computational domain when H/D=9
图 11 不同高度时机腹无量纲温度分布
Figure 11. Non-dimensional temperature distribution of belly under different heights
表 1 响应面法试验点
Table 1. Test point for respond surface method
参数 数值 H/D 3 6 9 U/（m/s） 0 7.5 15 π 2 2.5 3 
下载: 导出CSV
表 2 机腹温度变化模型方差及显著性表格
Table 2. Variance and significance of belly temperature variation
方差来源 方均根值/10−5 F P 结果 回归模型 422.1 19.8 0.0004 显著 A 652.5 30.61 0.0009 显著 B 1400 64.54 < 0.0001 显著 C 165.1 7.75 0.0272 显著 AB 0.269 0.013 0.9137 AC 171.6 8.05 0.0251 显著 BC 2.611 1.22 0.3050 A2 537.7 25.23 0.0015 显著 B2 144.4 6.77 0.0353 显著 C2 591.2 27.74 0.0012 显著 决定系数 0.9622
下载: 导出CSV
-
[1] 晨枫. F-35“闪电Ⅱ”战斗机[M]. 北京: 航空工业出版社,2014. CHEN Feng. F-35 lightning Ⅱ fighter jets[M]. Beijing: Aviation Industry Press,2014. (in ChineseCHEN Feng. F-35 lightning Ⅱ fighter jets[M]. Beijing: Aviation Industry Press, 2014. (in Chinese) [2] BEVILAQUA P. Inventing the F-35 joint strike fighter[R]. AIAA 2009-1650,2009. [3] MYERS L. Investigation of the flow-field of two parallel round jets impinging normal to a flat surface[R]. AIAA 2016-1776,2016. [4] 谭勇,袁颖. 垂直/短距起降战斗机动力系统发展浅析[J]. 现代军事,2015(12): 56-62. TAN Yong,YUAN Ying. Analysis on the development of power system of V/STOL fighter[J]. Conmilit,2015(12): 56-62. (in ChineseTAN Yong, YUAN Ying. Analysis on the development of power system of V/STOL fighter[J]. Conmilit, 2015(12): 56-62. (in Chinese) [5] 刘帅,王占学,周莉,等. 基于响应面法的短距/垂直起降飞机近地面升力损失[J]. 航空动力学报,2017,32(4): 874-881. LIU Shuai,WANG Zhanxue,ZHOU Li,et al. Lift loss of short/vertical takeoff and landing aircraft proximity of ground based on response surface method[J]. Journal of Aerospace Power,2017,32(4): 874-881. (in ChineseLIU Shuai, WANG Zhanxue, ZHOU Li, et al. Lift loss of short/vertical takeoff and landing aircraft proximity of ground based on response surface method[J]. Journal of Aerospace Power, 2017, 32(4): 874-881. (in Chinese) [6] SADDINGTON A,CABRITA P,KNOWLES K. Unsteady features of twin-jet STOVL ground effects[R]. AIAA 2002-6014,2002. [7] MYERS L M,KUO C W,MCLAUGHLIN D K. Experimental investigation of two impinging model scale jets[R]. AIAA 2014-0880 ,2014. [8] MCCARTHY K. The JSF STOVL performance process from small-scale database to flight test demonstration[R]. AIAA 2002-6002,2002. [9] WLEZIEN R W,FERRARO P J. Aeroacoustic environment of an advanced short takeoff and vertical landing aircraft in hover[J]. AIAA Journal,1992,30(11): 2606-2612. doi: 10.2514/3.11274 [10] SADDINGTON A,KNOWLES K,CABRITA P. Flow visualization and measurements in a short take-off,vertical landing fountain flow[R]. AIAA 2007-1402,2007. [11] MYERS L M,RUDENKO N,MCLAUGHLIN D K. Investigation on the flow-field of two parallel round jets impinging normal to a flat surface[R]. AIAA 2016-1776,2016. [12] NATARAJAN K,MEHTA Y,GUSTAVSSON J,et al. Effect of nozzle spacing on flow and acoustics characteristics of supersonic twin jets impinging on an inclined surface[R]. AIAA 2021-2220,2021. [13] HARMON M,BHARGAV V N,SELLAPPAN P,et al. Experimental study of impinging jet flow field involving converging and CD nozzle pair[R]. AIAA 2018-0261,2018. [14] 尤延铖,滕健,郑晓刚,等. 航空发动机进气温度畸变研究综述[J]. 南京航空航天大学学报,2017,49(3): 283-300. YOU Yancheng,TENG Jian,ZHENG Xiaogang,et al. Review of aero-engine temperature distortion research[J]. Journal of Nanjing University of Aeronautics & Astronautics,2017,49(3): 283-300. (in ChineseYOU Yancheng, TENG Jian, ZHENG Xiaogang, et al. Review of aero-engine temperature distortion research[J]. Journal of Nanjing University of Aeronautics & Astronautics, 2017, 49(3): 283-300. (in Chinese) [15] KUHN R,HANGE C,WARDWELL D. The hot gas environment of jet STOVL aircraft hovering in ground effect [R]. AIAA 1993-4888,1993. [16] MACLEAN R,SULLIVAN J P,MURTHY S. Hot gas environment around STOVL aircraft in ground proximity: Ⅰ experimental study[R]. AIAA 1990-2269,1990. [17] 杨帆,刘增文,刘帅,等. 三轴承旋转喷管型面设计与分析[J]. 航空计算技术,2014,44(2): 77-80. YANG Fan,LIU Zengwen,LIU Shuai,et al. Design and analisis of three bearing swivel nozzle inner contour[J]. Aeronautical Computing Technique,2014,44(2): 77-80. (in Chinese doi: 10.3969/j.issn.1671-654X.2014.02.019YANG Fan, LIU Zengwen, LIU Shuai, et al. Design and analisis of three bearing swivel nozzle inner contour[J]. Aeronautical Computing Technique, 2014, 44(2): 77-80. (in Chinese) doi: 10.3969/j.issn.1671-654X.2014.02.019 [18] HANGE C,WARDWELL D. Hot gas ingestion characteristics of a 5.3 percent scale model of the mixed-flow vectored-thrust (MFVT) ASTOVL aircraft concept[R]. AIAA 1993-4889,1993. [19] BHARGAV V N,SONG M,SELLAPPAN P,et al. Experimental characterization of supersonic single- and dual-impinging jets[J]. AIAA Journal,2021,59(6): 2282-2298. doi: 10.2514/1.J059687 [20] 申正. 圆喷嘴气体垂直冲击射流壁面压力规律研究[D]. 上海: 上海交通大学,2018. SHEN Zheng. Study of wall pressure distribution of vertical air impinging jet of round nozzles[D]. Shanghai: Shanghai Jiao Tong University,2018. (in ChineseSHEN Zheng. Study of wall pressure distribution of vertical air impinging jet of round nozzles[D]. Shanghai: Shanghai Jiao Tong University, 2018. (in Chinese) [21] 何为,薛卫东,唐斌. 优化试验设计方法及数据分析[M]. 北京: 化学工业出版社,2012. HE Wei,XUE Weidong,TANG Bin. Optimization experiment design method and date analysis[M]. Beijing: Chemical Industry Press,2012. (in ChineseHE Wei, XUE Weidong, TANG Bin. Optimization experiment design method and date analysis[M]. Beijing: Chemical Industry Press, 2012. (in Chinese) -
点击查看大图
计量
- 文章访问数: 332
- HTML浏览量: 351
- PDF量: 44
- 被引次数: 0