模型大迎角高速动态特性与数据精度分析
收稿日期: 2016-01-13
修回日期: 2016-04-18
网络出版日期: 2016-05-11
基金资助
国家自然科学基金（91216203）
Analysis of dynamic performance and test data precision of models with high angle of attack
Received date: 2016-01-13
Revised date: 2016-04-18
Online published: 2016-05-11
Supported by
National Natural Science Foundation of China (91216203)
李其畅 , 赵忠良 , 杨海泳 , 马上 , 李玉平 , 刘维亮 , 史晓军 , 王晓冰 . 模型大迎角高速动态特性与数据精度分析[J]. 航空学报, 2016 , 37(8) : 2594 -2602 . DOI: 10.7527/S1000-6893.2016.0123
It is important to determine pitching dynamic aerodynamic performance and test data precision of models with high angle of attack in high speed wind tunnel to meet the needs of evaluating aerodynamic performance, designing control system with precision and achieving maneuverability fight of aircraft. The dynamic performance and repeated test data precision of 70° delta wing model, SDM and Su-27 fighter model with high angle of attack in the dynamic experimental system with large amplitude of FL-24 wind tunnel have been obtained, which can be used as a standard for investigations on dynamic test of models. The obtained results under the test conditions basically meet the standards of those with steady force test of models with high angle of attack in high speed wind tunnel.
[1] ERICKSON G E. High angle-of-attack aerodynamic[J]. Annual Review of Fluid Mechanics, 1995, 27:45-88.
[2] LAN C E. Experimental and analytical investigation of transonic limit-cycle oscillations of a flaperon[J]. Journal of Aircraft, 1995, 32(5):905-910.
[3] BRANDON J M. Dynamic stall effects and application to high performance aircraft:AGARD Report No.776[R]. Paris:AGARD, 1991.
[4] JARRAH M A. Low speech wind tunnel investigation of flow about delta wings, oscillating in pitch to very high angle of attack:AIAA-1989-0295[R]. Reston:AIAA, 1989.
[5] HANFF E S, JENKINS S B. Large-amplitude high-rate roll experiments on a delta and double wing:AIAA-1990-0224[R]. Reston:AIAA, 1990.
[6] ERCSSON L E. Control of forebody flow asymmetry a critical review:AIAA-1990-2833[R]. Reston:AIAA, 1990.
[7] CARR L W, MCCROSKEY W J. Fluid dynamics of high angle of attack[C]//IUTAM Symposium Tokyo/Japan, 1992.
[8] MCCROSKEY M J. Unsteady airfoils[J]. Annual Review of Fluid Mechanics, 1982, 14:285-311.
[9] 李其畅, 赵忠良. 边条翼和近距鸭翼布局模型动态特性分析[J]. 空气动力学学报, 2015, 33(2):178-182. LI Q C, ZHAO Z L. Dynamic characteristics of hinged strake-wing and close-coupled wing-canard configuration fighter models[J]. Acta Aerodynamic Sinica, 2015, 33(2):178-182(in Chinese).
[10] CHAMBERS J R, HALL R M. Historical review of uncommand lateral-directional motions at transonic condition[J]. Journal of Aircraft, 2004, 41(3):436-447.
[11] SOLTANI M R, BRAGG M B, BRANDON J M. Measurements on an oscillating 70-deg delta wing in subsonic flow[J]. Journal of Aircraft, 1990, 27(3):211-217.
[12] 李其畅, 赵忠良, 伍开元, 等. 1.2 m×1.2 m高速风洞大振幅动态试验系统及其初步应用[J]. 空气动力学学报, 2005, 23(3):378-382. LI Q C, ZHAO Z L, WU K Y, et al. Introduction of dynamic experimental system with large amplitude in the 1.2 m×1.2 m sub-transonic wind tunnel[J]. Acta Aerodynamica Sinica, 2005, 23(3):378-382(in Chinese).
[13] 方宝瑞. 飞机气动布局设计[M]. 北京:航空工业出版社, 1997. FANG B R. Design on aerodynamic configuration of fighter[M]. Beijing:Aviation Industry Press, 1997(in Chinese).
[14] 李其畅, 伍开元, 郑世华, 等. 高速风洞大振幅俯仰动态试验技术研究[J]. 流体力学实验与测量, 2004(4):67-71. LI Q C, WU K Y, ZHENG S H, et al. Experimental investigation dynamic stall characteristics on 70° delta wing with high angle-of-attack in high speed[J]. Experiments and Measurements in Fluid Mechanics, 2004(4):67-71(in Chinese).
[15] 国防科学技术工业委员会. 高速风洞和低速风洞测力实验精度指标:GJB 1061-91[S]. 北京:国防科学技术工业委员会, 1991. National Defense Science Technology Industry Committee. The force test data precision in high speed wind tunnel and low speed wind tunnel:GJB 1061-91[S]. Beijing:National Defense Science Technology Industry Committee, 1991(in Chinese).
[16] 贺中. 飞行器大攻角高速风洞测力试验方法[R]. 绵阳:中国空气动力研究与发展中心, 2005. HE Z. The test method on aircraft with high angle-of-attack in high speed wind tunnel[R]. Mianyang:China Aerodynamic Research and Development Center, 2005(in Chinese).
/
| 〈 |
|
〉 |
CJA