中文摘要：

基于雷诺平均Navier—Stokes方程与多块搭接网格技术，数值模拟了协同射流（CFJ）翼型及桨叶的黏性绕流，分析了CFJ技术的增升减阻效果及工作机理。研究了CFJ的功率及效能比的分析方法，量化分析了cFJ的能量利用率。开展了喷口大小、喷口动量系数等参数对CFJ翼型性能的影响规律研究，并在此基础上开展了应用CFJ的临近空间螺旋桨高增效方法研究。结果表明：数值模拟结果与实验值吻合良好，在不同状态下，CFJ控制技术均能显著改善翼型气动性能。其中，最大升力系数提高了60％～130％；阻力系数降低了100％～440％，部分小迎角工况甚至出现负阻力系数，升阻比显著提高；翼型失速特性明显改善，失速迎角提高了近10°；能量利用率高，效能比可达440％。最终，在最优参数条件设置下，采用基于CFJ控制技术的临近空间螺旋桨可提高效率5％以上。

英文摘要：

Based on the Reynolds-averaged Navier-Stokes equations and multi-block grid technology, a numerical simulation is implemented of a high performance airfoil and near space propeller using the co-flow jet （CFJ） flow control method, based on which the mechanism and performance of CFJ technology are studied. In order to quantify the energy efficiency of the CFJ technology, analysis methods of power demand and energy efficiency are proposed. Based on the influence of different jet slot sizes, jet momentum coefficient and other parameters on the CFJ technology performance are investigated, the research of high synergy method for near space propeller by co-flow jet flow control are carried out. It is shown that the numerical simulation results agree well with the experimental data. In different states, CFJ technology can significantly improve the aerodynamic performance of the airfoil： the maximum lift coefficient may increase by 60 %-130%, the drag coefficient may be reduced by 100 %-440 %, and even negative drag coefficient may appear at low angles of attack, so much so that the liftdrag ratio is significantly improved. Also, the airfoil stall characteristics are significantly improved with the stall angle of attack increasing by nearly 10°. Furthermore, the power demand is very low and the energy efficiency is enhanced up to 440%. Finally, due to these improvements, the efficiency of the near space propeller using CFJ technology is increased by more than 5 % for the proposed optimal jet slot size and jet momentum coefficient.