[1] 蒙泽威. 高超声速飞行器前机身进气道参数化设计与优化[D]. 长沙: 国防科技大学, 2018.
[2] Waltrup P J, Billig F S. Structure of Shock Waves in Cylindrical Ducts[J]. AIAA Journal, 1973, 11(10): 1404-1408.
[3] Waltrup P J, Dugger G L, Billig F S, et al. Direct-Connect Tests of Hydrogen-Fueled Supersonic Combustors[J]. Symposium (International) on Combustion, 1977, 16(1): 1619-1629.
[4] Lin P, Rao G, O'connor G. Numerical Analysis of Normal Shock Train in a Constant Area Isolator[C]. Sacramento:27th Joint Propulsion Conference, 1991.
[5] 熊 冰, 范晓樯, 王振国. 中心线偏置隔离段内激波串迟滞特性研究[J]. 推进技术, 2016, 37(5): 864-870.
[6] 田旭昂, 王成鹏, 程克明. 变截面隔离段流场数值分析[J]. 推进技术, 2008, 29(6): 690-695.
[7] Billig F S, Kothari A P. Streamline Tracing: Technique for Designing Hypersonic Vehicles[J]. Journal of Propulsion and Power, 2000, 16(3): 465-471.
[8] Billig F, Baurle R, Tam C J, et al. Design and Analysis of Streamline Traced Hypersonic Inlets[C]. Norfolk: 9th International Space Planes and Hypersonic Systems and Technologies Conference, 1999.
[9] Smart M K. Design of Three-Dimensional Hypersonic Inlets with Rectangular-to-Elliptical Shape Transition[J]. Journal of Propulsion and Power, 1999, 15(3): 408-416.
[10] Smart M K. Experimental Testing of a Hypersonic Inlet with Rectangular-to-Elliptical Shape Transition[J]. Journal of Propulsion and Power, 2001, 17(2): 276-283.
[11] 黄河峡, 谭慧俊, 庄 逸, 等. 高超声速进气道/隔离段内流特性研究进展[J]. 推进技术, 2018, 39(10):98-119.
[12] Barger R L. A Procedure for Designing Forebodies with Constraints on Cross-Section Shape and Axial Area Distribution[R]. NASA TP 1881, L-14516.
[13] Meng Z, Fan X, Wang Y, et al. Optimization Design for Shape-Transition Curved Isolator with Controllable Cross-Sectional Area[J]. Acta Astronautica, 2018, 152: 335-341.
[14] Meng Z, Fan X, Wang Y, et al. Parameterization and Optimization for Shape-Transition Curved Isolator[J]. Acta Astronautica, 2018, 151: 563-571.
[15] Lee C C, Boedicker C. Subsonic Diffuser Design and Performance for Advanced Fighter Aircraft[R]. AIAA 85-3073.
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