中国空气动力研究与发展中心 超高速空气动力研究所,绵阳,621000
吴岸平(1990—),男,湖南涟源人,研究方向:风洞试验技术. E-mail:wuanpingtech@163.com
许晓斌*,研究方向:风洞试验技术. E-mail: Scmy-xxb@163.com
纸质出版:2024
移动端阅览
吴岸平, 范孝华, 郭雷涛, 等. 高超声速喷管流场不均匀性分析与改进[J]. 空气动力学学报, 2024, 42(5): 38−44.
WU Anping, FAN Xiaohua, GUO Leitao, et al. Flow quality analysis and improvement of hypersonic nozzle[J]. 2024, 42(5): 38-44.
吴岸平, 范孝华, 郭雷涛, 等. 高超声速喷管流场不均匀性分析与改进[J]. 空气动力学学报, 2024, 42(5): 38−44. DOI: 10.7638/kqdlxxb-2023.0037
WU Anping, FAN Xiaohua, GUO Leitao, et al. Flow quality analysis and improvement of hypersonic nozzle[J]. 2024, 42(5): 38-44. DOI: 10.7638/kqdlxxb-2023.0037.
飞行器的发展,对风洞不同模拟条件下气动和操稳特性的准确预测提出了更高需求。风洞流场品质是影响试验数据精准度的主要因素之一,本文以某风洞马赫数5.5喷管为研究对象,开展喷管出口流场不均匀性研究。通过数值计算捕捉喷管内部微弱波系结构,分析喷管型面设计方法、型面加工精度和型面拼接处阶差等因素对喷管出口流场品质的影响,并与风洞流场校测结果进行对比分析,得出目前影响喷管出口流场品质的主要因素是拼接处阶差,并针对该因素提出了改进策略,通过对喷管合理分段减少波系对试验区域影响,以进一步提升风洞流场品质。
With the development of aircraft
higher requirements are put forward for the accurate prediction of aerodynamic and operating characteristics under different wind tunnel simulation conditions. The flow quality of wind tunnel is one of the main factors affecting the accuracy of wind tunnel test data. A Mach 5.5 nozzle used as the research object in this paper
the non-uniformity of nozzle outlet flow field is studied. The structure of weak waves in nozzle is captured by numerical simulation. The influence of different factors on the quality of nozzle outlet flow field is analyzed
including the profile design method
profile machining accuracy and step joint at profile splicing. Combined with the comparison and analysis of the wind tunnel calibration results
it is concluded that the main factor affecting the quality of nozzle outlet flow field is the step joint at profile splicing. An improvement strategy of segment the nozzle properly is proposed to improve the quality of flow field.
TANG Z G, XU X B, YANG Y G, et al . Research progress on hypersonic wind tunnel aerodynamic testing techniques[J ] . Acta Aeronautica et Astronautica Sinica, 2015 , 36 ( 1 ): 86 − 97 (in Chinese).
XU X B, SHU H F, XIE F, et al. Research progress on aerodynamic test technology of hypersonic wind tunnel for air-breathing aerocraft[J]. Journal of Experiments in Fluid Mechanics, 2018, 32(5): 29-40(in Chinese).
NAGAI S, IIJIMA H . Uncertainty identification of supersonic wind tunnel testing[J ] . Journal of Aircraft, 2010 , 48 : 567 − 577 .
MAUS J. Investigation of differences between measured and predicted pressures in AEDC/VKF Hypersonic Tunnel B[C]// 35th Aerospace Sciences Meeting and Exhibit, Reno, NV, USA. Reston, Virginia: AIAA, 1997: 566.
XIE F, GUO L T, XU X B, et al . Effects of non-uniformity of flow field on aerodynamic test in hypersonic wind tunnel[J ] . Journal of Propulsion Technology, 2022 , 43 ( 7 ): 368 − 376 (in Chinese).
WANG Y P, JIANG Z L . A review of theories and metho ds for hypersonic nozzle design[J ] . Advances in Mechanics, 2021 , 51 ( 2 ): 257 − 294 (in Chinese).
HUANG J, YANG Y N, LIU Q, et al . Developing and applying Mach 4.5 nozzle in hypersonic wind tunnel[J ] . Journal of Northwestern Polytechnical University, 2021 , 39 ( 5 ): 1064 − 1069 (in Chinese).
CHEN W N, XU L . Contour design of hypersonic wind tunnel nozzles[J ] . Applied Energy Technology, 2018 , 7 : 1 − 4 (in Chinese).
LACEY J, INOUE Y, HIGASHIDA A, et al. Improvement of flow quality in NAL Chofu Mach 10 nozzle[C]// 40th AIAA Aerospace Sciences Meeting Exhibit, Reno, NV, USA. Reston Virginia: AIAA, 2002: 440.
NORRIS J, LAFFERTY J, SMITH M, et al. Design and aerodynamic calibration of the new AEDC hypervelocity wind tunnel No. 9 Mach 8 nozzle[C]// 41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference Exhibit, Tucson, Arizona. Reston, Virginia: AIAA, 2005: 4278.
BOE K, CANDLER G. A novel simulation approach for the AEDC hypervelocity tunnel 9 Mach 14 nozzle[R]. Reston: AIAA, 2011.
ZHENG L M. ANSYS Fluent 15.0 fluid calculation: From beginner to proficient[M]. Beijing: Electronic Industry Press, 2015: 114-116(in Chinese).
LI N, ZHANG K Y, XU J L . Simulation and experiment validation of a two dimensional asymmetric ramp nozzle[J ] . Journal of Aerospace Power, 2004 , 19 ( 6 ): 802 − 805 (in Chinese).
CRESCI R J. Tabulation of coordinates for hypersonic axisymmetric nozzles: Part 1, analysis and coordinates for test section Mach number of 8, 12, 20[M]. Wright-Patterson Air Force Base, Ohio: 1958.
SIVELLS J C . Aerodynamic design of axisymmetric hypersonic wind-tunnel nozzles[J ] . Journal of Spacecraft and Rockets, 1970 , 7 ( 11 ): 1292 − 1299 .
ZHANG M L, YI S H, ZHAO Y X . The design and experimental investigations of supersonic length-shorted nozzle[J ] . Acta Aerodynamica Sinica, 2007 , 25 ( 4 ): 500 − 503 (in Chinese).
YI S H, ZHAO Y X, HE L. Supersonic and hypersonic nozzle design[M]. Beijing: National Defense Industry Press, 2013: 87-90(in Chinese).
0
浏览量
0
下载量
0
CSCD
关联资源
相关文章
相关作者
相关机构
京公网安备11010802024621