| [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
