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为了满足超燃冲压发动机三维流道排气系统一体化设计需要,基于轴对称最大推力喷管流动的基准流场,采用流线追踪方法发展了三维尾喷管构型设计技术。根据典型的高超声速飞行条件,设计得到了进口方形,尺寸50mm×50mm,长度560mm,出口高度147mm的三维尾喷管无粘构型,并对其进行了粘性修正。对该尾喷管构型在设计状态进行了无粘和有粘流场计算,得到了推力和升力等性能参数,并对其流场结构有了初步的认识。计算发现,流线追踪构型能有效增大推力,而粘性力是造成推力损失的重要因素。
In order to meet the need of the integrated design of the three-dimensional runner exhaust system of scramjet, a three-dimensional tail nozzle configuration design technique was developed based on the flow field of the axisymmetric maximum thrust nozzle. According to the typical hypersonic flight conditions, a three-dimensional tail nozzle with a square shape, a size of 50mm × 50mm, a length of 560mm and an outlet height of 147mm was designed and its viscosity was modified. The design of this nozzle configuration was studied in terms of non-stick and viscous flow field, and the thrust and lift parameters were obtained. The flow field structure was preliminarily understood. The calculation shows that the streamline tracking configuration can effectively increase the thrust, and the viscous force is the important factor that causes the thrust loss.