Transonic lateral departure motion characteristics of a low-aspect-ratio flying-wing model

被引：0
|
作者：
Zhang J. [1 ,2 ]
Li W. [1 ,2 ]
Wang Z. [1 ,2 ]
Pan J. [1 ,2 ]
Bu C. [1 ]
机构：
[1] AVIC Aerodynamic Research Institute, Shenyang
[2] Aeronautical Science and Technology Key Lab for High Speed and High Reynolds Numbers Aerodynamic Force Research, Shenyang
来源：
Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica | 2022年 / 43卷 / 11期
关键词：
flow principle; lateral departure motion; low-aspect-ratio flying-wing; transonic; wing drop; wing rock;
D O I：
10.7527/S1000-6893.2021.26340
中图分类号：
学科分类号：
摘要：
Adapted for high-speed, stealth and maneuvering flight, the low-aspect-ratio flying-wing aircraft adopts the large sweep delta wing profile to meet the uncommanded lateral motion caused by the asymmetric leading vortex breaking similar to delta wing. In order to research the motions and related control methods, aerodynamic/flow integration measurement test, free-to-roll test and numerical simulation are carried on a low-aspect-ratio flying-wing model with leading edge sweep 65° and aspect ratio 1.54, which successfully captured the commanded lateral motions including wing drop and wing rock at Mach number 0.8 and 0.9, angle of attack 15°-20° conditions in wind tunnel. The Figure of Merit in free-to-roll test show that the lateral flight quality has declined obviously. The frequency spectrum and phase plane portrait of free-to-roll trajectories confirm that the departure motion characteristics are chaos or multi-periodic broadband oscillation. The combined control surfaces including leading edge flap 10° and all aileron 10° are used to free-to-roll wind tunnel test. The results verify that the combined control surfaces can restrain the uncommanded lateral motion at Mach number 0.8, angle of attack 20° condition. The flow principle is also given by numerical simulation. The shock-wave/vortex interactions above the wings at transonic cause the flow breaking asymmetric. There are high and low frequencies in the roll moment, which finally bring out the self-excited oscillations of the low-aspect-ratio flying-wing mode. © 2022 AAAS Press of Chinese Society of Aeronautics and Astronautics. All rights reserved.
引用
收藏
相关论文
共 32 条
  • [11] VICROY D D, LOESER T D, SCHVTTE A., SACCON forced oscillation tests at DNW-NWB and NASA Langley 14×22-foot tunnel:AIAA-2010-4394, (2010)
  • [12] LI L, MA C, WANG L X., Stability features of low aspect-ratio flying wings[J], Acta Aeronautica et Astronautica Sinica, 28, 6, pp. 1312-1317, (2007)
  • [13] MA S H, WU C F, CHEN H M., Study on stability and manoeuvrability of flying wing aircraft, Flight Dynamics, 24, 3, pp. 17-21, (2006)
  • [14] HUANG X, HANFF E., Free-to-roll trajectory and related attractors of a 65° delta wing rolling at high incidence:AIAA-1999-4103, (1999)
  • [15] KONRATH R, SCHRODER A, KOMPENHANS J., Analysis of PIV results obtained for the VFE-265° delta wing configuration at sub-and transonic speeds:AIAA-2006-3003, (2006)
  • [16] DONOHOE S R, BANNINK W J., Surface reflective visualizations of shock-wave/vortex interactions above a delta wing, AIAA Journal, 35, 10, pp. 1568-1573, (1997)
  • [17] HUANG X Z., Comprehensive experimental studies on vortex dynamics over military wing configurations in IAR:AIAA-2003-3940, (2003)
  • [18] MITCHELL A, MORTON S, FORSYTHE J., Analysis of delta wing vortical substructures using detached-eddy simulation, AIAA Journal, 44, 5, (1997)
  • [19] BARBERIS D, MOLTON P, RENAC F, Et al., Vortex control on delta wings:AIAA-2004-2620, (2004)
  • [20] SU J C, HUANG Y, ZHONG S D, Et al., Research on flow characteristics of low-aspect-ratio flying-wing at transonic speed[J], Acta Aerodynamica Sinica, 33, 3, pp. 307-312, (2015)
1234