Aeroelastic simulations of a delta wing with a Chimera approach for deflected control surfaces

Author:

Reinbold ChristopherORCID,Sørensen Kaare,Breitsamter Christian

Abstract

AbstractA numerical tool for the computation of aircraft control surface aerodynamics with flexibility effects is presented. The solution is based on coupled Computational Fluid Dynamics (CFD) and Computational Structural Mechanics (CSM) simulations embedded in the multidisciplinary simulation environment SimServer. In SimServer, the DLR-TAU Code is utilized to obtain the CFD solution by solving the Reynolds-Averaged Navier–Stokes (RANS) equations. Structural displacements are computed with a modal solver. The Chimera implementation of SimServer, suited for hybrid grids, is applied to model the control surfaces. Numerical simulations with the flexible Chimera method are performed for the Model53 wing configuration, which is a generic delta wing with a deployed slat as well as an inboard and outboard trailing edge flap. Aerodynamic and aeroelastic simulations at high dynamic pressure $$q=45$$ q = 45  kPa and transonic speed $${\text {Ma}} = 0.8$$ Ma = 0.8 are performed for several angles of attack $$10^\circ \le \alpha \le 25^\circ$$ 10 α 25 and flap deflection angles $$-30^\circ \le \delta \le 30^\circ$$ - 30 δ 30 . The effect of structural deformations on the flow field and control surface effectiveness are analyzed and compared to computations of components treated fully rigid. At the targeted freestream condition $$M=0.8$$ M = 0.8 and $${\text {Re}}=15.1 \times 10^7$$ Re = 15.1 × 10 7 , the flow field around the Model53 configuration is characterized by the interaction of vortices and shock waves. The results of the lift and pitching moment coefficient for the rigid and flexible configuration revealed the importance of taking the structural flexibility into account in order to obtain more accurate results for the considered range of flap deflections. Furthermore, the computational effort of the aerodynamic and aeroelastic simulations are evaluated. The increase in computational effort is shown to be adequate for the given increase in accuracy.

Funder

Technische Universität München

Publisher

Springer Science and Business Media LLC

Subject

Aerospace Engineering,Transportation

Reference24 articles.

1. Breitsamter, C.: Aerodynamic efficiency of high maneuverable aircraft applying adaptive wing trailing edge section. In: 24th International Congress of the Aeronautical Sciences, pp. 1–10 (2004)

2. Hövelmann, A., Pfnür, S., Breitsamter, C.: Flap efficiency analysis for the SAGITTA diamond wing demonstrator configuration. CEAS Aeronaut. J. 6(4), 497–514 (2015)

3. Pfnür, S., Oppelt, S., Breitsamter, C.: Yaw-control efficiency analysis for a diamond wing configuration with outboard split flaps. CEAS Aeronaut. J. 10(2), 645–663 (2019)

4. Helm, S., Haupt, M., Stickan, B., Bleecke, H.: Advancements of CFD–CSM coupling by means of multibody simulation. In: Deutscher Luft- und Raumfahrtkongress. Deutsche Gesellschaft für Luft- und Raumfahrt-Lilienthal-Oberth e.V. (2015)

5. Capsada, L.A., Heinrich, R.: Development of the DLR TAU code for modelling of control surfaces. In: Deutscher Luft- und Raumfahrtkongress. Deutsche Gesellschaft für Luft- und Raumfahrt-Lilienthal-Oberth e.V. (2019). https://elib.dlr.de/126777/

Cited by 5 articles. 订阅此论文施引文献 订阅此论文施引文献,注册后可以免费订阅5篇论文的施引文献,订阅后可以查看论文全部施引文献

同舟云学术

1.学者识别学者识别

2.学术分析学术分析

3.人才评估人才评估

"同舟云学术"是以全球学者为主线,采集、加工和组织学术论文而形成的新型学术文献查询和分析系统,可以对全球学者进行文献检索和人才价值评估。用户可以通过关注某些学科领域的顶尖人物而持续追踪该领域的学科进展和研究前沿。经过近期的数据扩容,当前同舟云学术共收录了国内外主流学术期刊6万余种,收集的期刊论文及会议论文总量共计约1.5亿篇,并以每天添加12000余篇中外论文的速度递增。我们也可以为用户提供个性化、定制化的学者数据。欢迎来电咨询!咨询电话:010-8811{复制后删除}0370

www.globalauthorid.com

TOP

Copyright © 2019-2024 北京同舟云网络信息技术有限公司
京公网安备11010802033243号  京ICP备18003416号-3