A novel contour design technique of super/hypersonic nozzle diverging section with sharing throat
来源期刊：中南大学学报(英文版)2014年第7期
论文作者：GUO Shan-guang(郭善广) WANG Zhen-guo(王振国) ZHAO Yu-xin(赵玉新) LIU Jun(柳军)
文章页码：2766 - 2771
Key words：supersonic flow; nozzle design; throat section; multiple Mach number; method of characteristics
Abstract: A straightforward technique has been developed to quickly determine the wall contour of super/hypersonic nozzles working at multiply Mach number which share a common throat section. Mach number distribution along the centerline of the nozzle is specified in advance and divided into two sections, both of which are described by the b-spline function. The first section is shared by different exit Mach number nozzles. The nozzle contour is determined by the method of characteristics plus boundary layer correction. An example of this design method is employed to illustrate the technique with a computational fluid dynamics calculation. The simulation results indicate that desired Mach numbers are obtained at the nozzle exit, and the good flow quality is attained for different nozzles within δMa/Ma<±0.56% in the flow core region. This technique improves the design precision of the converging-diverging nozzle, cancels waves completely, and achieves nozzles with multiple Mach number exiting which share a common throat section.
GUO Shan-guang(郭善广), WANG Zhen-guo(王振国), ZHAO Yu-xin(赵玉新), LIU Jun(柳军)
(Science and Technology on Scramjet Laboratory, National University of Defense Technology,
Changsha 410073, China)
Abstract:A straightforward technique has been developed to quickly determine the wall contour of super/hypersonic nozzles working at multiply Mach number which share a common throat section. Mach number distribution along the centerline of the nozzle is specified in advance and divided into two sections, both of which are described by the b-spline function. The first section is shared by different exit Mach number nozzles. The nozzle contour is determined by the method of characteristics plus boundary layer correction. An example of this design method is employed to illustrate the technique with a computational fluid dynamics calculation. The simulation results indicate that desired Mach numbers are obtained at the nozzle exit, and the good flow quality is attained for different nozzles within δMa/Ma<±0.56% in the flow core region. This technique improves the design precision of the converging-diverging nozzle, cancels waves completely, and achieves nozzles with multiple Mach number exiting which share a common throat section.
Key words:supersonic flow; nozzle design; throat section; multiple Mach number; method of characteristics
