论文部分内容阅读
采用特征线方法设计了具有直线初始激波、内收缩段消除激波反射、出口参数均匀可控的基准内锥流场.基于密切内锥(osculating inward turning cone,OIC)乘波体设计方法,发展了一体化密切内锥乘波前体进气道(osculating inward turning cone waverider inlet,OICWI)设计技术.基于一体化基准内锥流场和前体进气道设计技术,设计了密切内锥乘波前体进气道.采用数值软件对设计的乘波前体进气道进行了仿真分析,结论如下:①OICWI的设计是遵循气动原理的.②一体化密切内锥乘波前体进气道的前缘形状、内收缩比及出口参数可以根据需求定量准确设计.③理论设计结果和模拟结果吻合一致,证明设计方法是正确可靠的.④数值模拟研究结果表明一体化密切内锥乘波前体进气道具有较好的出口流场均匀度及较高的流量捕获率和较高的总压恢复特性.
Using the characteristic line method, a reference inner cone flow field with straight initial shock wave and internal contraction section eliminating shock reflection and exit parameter is designed.According to the osculating inward turning cone (OIC) multiplicative wave body design method, (OICWI) design technique was developed.According to the integrated cone flow field and precursor inlet design technology, the design of close inner cone multiplication Wave front inlet.The numerical simulation software was used to simulate the inlet of the wavefront precursor.The conclusions of the study are as follows: ① The design of OICWI is based on the principle of aerodynamics.②The integration of the inner inlet of the cone-wave precursor The leading edge shape, the internal shrinkage ratio and the outlet parameters can be quantitatively and accurately designed according to the requirements.③The theoretical design results are in good agreement with the simulation results, which proves that the design method is correct and reliable. ¢ 数The numerical simulation results show that the integrated close-in- Body inlet has better exit flow uniformity and higher flow capture rate and higher total pressure recovery characteristics.