摘要
研究双喷管火箭发动机燃气流对直升机的影响 ,对燃气流场中的压力、温度和速度分布等进行理论计算和试验测量 .研究采用数值计算和试验测量相结合的方法 ,控制方程为三维、雷诺平均 Navier- Stokes方程及 k-ε二方程的紊流模型 ,并且对该发动机进行了燃气流场的测试 ,对流场中的总压强进行了直接测量 ,进行了两次试验 ;在两次测点位置 ,试验结果与数值计算值相差分别为 3%和 7% ;证明了对双喷管火箭燃气射流流场的数值计算具有了较好的精度 。
The effect of double nozzle jet of a rocket to a helicopter is studied by calculating and testing the pressure, temperature and velocity of the flow. A three dimensional Navier Stokes equation is solved with a standard k ε turbulent model. Two experiments were carried out and the total pressure of jet flow was tested. Based on the tests, the differences between the calculated and test results were found to be 3% and 7% respectively. It proved that the results of calculation can well be used in engineering applications
出处
《北京理工大学学报》
EI
CAS
CSCD
北大核心
2002年第4期418-421,共4页
Transactions of Beijing Institute of Technology
