Experimental and numerical investigation of dual bell nozzle flow under realistic flight conditions (K02*)

第一个资助阶段侧重于理解和预测双钟形喷嘴中的流动现象，首先是在基础层面，然后是热流燃烧和CFD层面。为了获得主级发动机喷管的资格，必须在实际飞行条件下对双钟形喷管进行研究。因此，将对环境气压波动和轮廓椭圆化对过渡行为的影响进行冷流研究，并实现C/C- sic喷管热流试验的技术论证。在此基础上，将对未来可能的阿丽亚娜构型进行轮廓优化和飞行轨迹计算。

The first funding phases focused on the understanding and predicting of flow phenomena in dual bell noz-zles, first on a fundamental level, then on hot flow combustion and CFD level. For qualification as main stage engine nozzle, the dual bell must be studied under realistic flight conditions. Therefore, cold flow investigations on ambient air pressure fluctuations and contour ovalization effect on transitional behaviour will be conducted and a technology demonstration on hot flow tests of C/C-SiC nozzle realized. Based on the gained insight, contour optimization and flight trajectory calculation will be conducted for future potential Ariane configurations.