Abstract
The optimization of 2D expansion lines and key parameters of three-dimensional configurations was carried out under simulated conditions of Mach 6.5 and a flight altitude of 25 km for an integrated configuration of the afterbody/nozzle of a hypersonic vehicle. First, the cubic B-spline method was applied to parameterize the expansion lines of the upper expansion ramp. The optimization procedure was established based on computational fluid dynamics and the sequential quadratic programming method. The local mesh reconstruction technique was applied to improve computational efficiency. A three-dimensional integrated configuration afterbody/nozzle was designed based on the two-dimensional optimized expansion lines. The influence rules incorporated certain key design parameters affecting the lift and thrust performance of the configuration, such as the ratio of the lengths of the lower expansion ramp to the afterbody (l/L), the dip angle of the lower expansion ramp ω, and the ratio of exit height to the length of afterbody (H/L). Under these conditions, we found that the integrated configuration has optimal performance when l/L=1/6, H/L=0.35 and ω=10°. We also showed that the presence of a side-board promotes lift and thrust performance, and effectively prevents the leakage of high pressure gas.
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References
Huang Z C. The aerodynamic design for aerospace plane (in Chinese). Aerodyn Exp Meas Control, 1991, 5: 1–11
Chen B, Xu X, Cai G B. Optimization design of two dimensional scramjet nozzle based on N-S equations (in Chinese). J Propul Tech, 2002, 23: 433–437
Rao G V R. Exhaust nozzle contour for optimum thrust. Jet Propul, 1958, 38: 377–382
Huang Z C. The aerodynamic design of nozzle for aerospace plane (in Chinese). Aerodyn Exp Meas Control, 1993, 7: 1–10
Berens T M. Experimental and numerical analysis of a two-duct nozzle/afterbody model at supersonic mach numbers. AIAA-1995-6085, 1995
Le Bozec A, Rostand P, Rouy F, et al. Afterbody testing and comparison to CFD simulations. AIAA-1998-1596, 1998
Zhao J X, Zhou L. Numerical investigation of internal and external supersonic flows of nozzle (in Chinese). J Propul Tech, 2001, 22: 295–298
Wang X F, Shang X S, Chen Y C, et al. Numerical simulation of internal flow field in the single expansion ramp nozzle for the hypersonic aero-engine (in Chinese). J Proj Rockets Missiles Guidance, 2007, 27: 187–189
Huang W, Liu J, Luo S B. Effect research of afterbody nozzle configuration on hypersonic vehicle performance (in Chinese). J Proj Rockets Missiles Guidance, 2008, 28: 161–164
Chen B, Xu X, Cai G B. Single- and multi-objective optimization of scramjet components using genetic algorithms based on a parabolized navier-stokes solver. AIAA-2006-4686, 2006
Marathe A G, Thiagarajan V. Effect of geometric parameters on the performance of single expansion ramp nozzle. AIAA-2005-4429, 2005
Damira S K, Marathe A G, Sudhakar K. Parametric optimization of single expansion ramp nozzle (SERN). AIAA-2006-5188, 2006
He X Z, Zhang Y, Wang G Y, et al. Automated design optimization of single expansion ramp nozzle for hypersonic vehicle (in Chinese). J Propul Tech, 2007, 28: 148–151
Che J, Tang S. The application of genetic algorithms to afterbody/nozzle integrated design of a hypersonic vehicle (in Chinese). Flight Dyn, 2006, 24: 74–77
Cao D Y, Lee C H. Optimal design of nozzle for hypersonic vehicle (in Chinese). J Beijing Uni Aeronaut Astronaut, 2007, 33: 1162–1165
Cui K, Yang G W. The effect of conical flowfields on the performance of waveriders at Mach 6. Chin Sci Bull, 2007, 52: 57–64
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Gao, T., Cui, K., Wang, X. et al. Aerodynamic optimization and evaluation for the three-dimensional afterbody/nozzle integrated configuration of hypersonic vehicles. Chin. Sci. Bull. 57, 849–857 (2012). https://doi.org/10.1007/s11434-011-4948-3
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DOI: https://doi.org/10.1007/s11434-011-4948-3