空天飞机喷管的气动设计

本文首先阐述了喷管气动设计在整个空天飞机气动设计中的重要地位,介绍了两种用于空天飞机的二维不对称喷管的无粘流气动设计方法。一种是基于 Rao 的最大推力喷管设计方法;另一种是基于最小长度喷管的设计方法。重点介绍了 NASA Langley 研究中心固定几何形状的超燃冲压发动机喷管的气动设计。分析了发动机位置、上壁倾角、外罩内侧倾角和外罩长度对飞行器性能的影响。最后,介绍了空天飞机喷管流动的风洞实验和计算流体力学的进展,并提出了尚待进一步研究的问题。

THE AERODYNAMIC DESIGN OF NOZZLE FOR AEROSPACE PLANE

The important position of nozzle aerodynamic design in the aerodynamic design of the aerospace plane is expounded in this paper.Twodesign methods of the inviscid flow of two-dimensional asymmetric nozzlefor the aerospace plane ane introduced.One is based on a design method fothe maximum thrust nozzle of Rao.Another one is based on a design meth-od of the minimum length nozzle.It puts emphasis on the aerodynamic de-sign of nozzle of Fixed-Geometry Scramjet at NASA Langley Research Cen-ter.The effects of Scramjet location,nozzle upper wall angle,interiornozzle cowl angle,nozzle cowl length on performance of the aerospace planeare analysed.The progresses of the wind tunnel testing and the computa-tional fluid dynamics of the nozzle flow for the aerospace plane are reported.The problems of the nozzle flow required further research for the aerospaceplane are put forward.