Improved design and performance analysis of counterflow thrust vectoring technology under high subsonic

With the development of aviation technology and the scramble for air supremacy is becoming increasingly fierce, people put forward higher requirements on the performance of the fighter. The thrust vector nozzle based on flow control has many advantages compared with the traditional mechanical contr ol method, in the thrust vector technology, the thrust loss is low, it can also be applied in subsonic speed. Thrust vector technology has a wider application background. In this paper, the basic principle of counter current thrust vector technology is explained firstly, then the simplified derivation of the formula and the definition of related parameters are derived by the control body analysis. And fluent software is used to simulate the existing experimental model, the obtained numerical results are compared with the experimental data available in the literature, verification proves that the numerical method is feasible. Then change the Maher number of outflow size of vector analysis to effect change. Finally, for thrust vector effect is not obvious under the Maher problem, the design provides a method for vacuum reverse two secondary channel, and its feasibility by using the method of numerical analysis, the vacuum in the two channel is increased, and the thrust vector angle can reach to 18.1 degrees from 1.7 degrees, an increase of about 10 times.