DESIGN AND NUMERICAL SIMULATION OF SINGLE EXPANSION RAMP NOZZLE FOR SCRAMJET
Basing on the theory of characteristics, the design method of Single Expansion Ramp Nozzle (SERN) is presented in this paper. By changing the geometric parameter F and Alfa, a series of two-dimensional, length-optimized configurations can be obtained. Computational investigation ofdifferent nozzle performance was performed by FLUENT software. At first, the inviscid two-dimensional nozzle flow field was numerically simulated in order to verify the design method. The inviscid result indicates that Mach number contour at nozzle internal flowfield agrees with characteristics theory perfectly. Then the viscous two-dimensional flow fields of baseline configurations and reduced configurations were studied under different free stream conditions. The baseline configurations with F equal to 0, 0.1, 0.5, 0.9, and 1.0 were simulated in order to study the effects of parameter F on nozzle performance. Then the reduced model was investigated to find out the reduction effects on the nozzle performance. For the baseline models, the effect of parameter F on thrust is slight under the design condition. While it has noticeable effect on the lift and pitch moment. Under the severely over-expanded condition, the effect of parameter F on the thrust is notable. For the reduced case, thrust decreases a little, while the lift and pitch moment decrease greatly.
Single Expansion Ramp Nozzle (SERN) Method of Characteristics numerical simulation hypersonic SCRANMJET
ZHANG Yan-hui XU Jing-lei ZhANG Kun-yuan
Coll.of Energy and Power Engineering Nanjing Univ.of Aeronautics and Astronautics Jiangsu Province, Nanjing,210016, P.R.China
国际会议
昆明
英文
528-533
2006-09-18（万方平台首次上网日期，不代表论文的发表时间）