Abstract: This paper presents the designing procedures of the wall contour of aerospike nozzle using characteristic method and a sample result; obtains the numerical results of viscous side nozzle internal flow field from transonic to supersonic flow,the Euler solution of the flow field along the plug wall and after the plug bottom,and summarizes the solid propellant test system simulating the working property of aerospike nozzles, experimental results and the main conclusions. Rocket engine with aerospike nozzle is a complex and challenging research direction. It will play important role in the development of a new generation reusable launch vehicle.