Analysis,Optimization And Application Of Hypersonic Two-dimensional Curved Shock Compression

As a new type of compression method,the 2-D curved shock compression might have the potential to further enhance compression system performance of air-breathing hypersonic vehicle.In this dissertation,computation method,design method,performance optimization and application of the curved shock compression are studied.A rapid analysis method for curved shock compression flow field is proposed.Equations for approximately calculating parameters on curved shock,streamline and outlet based on compression surface configuration is developed,which could be used to quickly determine parameter values and flow features in the field.A group of test results showed that,compared with the method of characteristics solution,root mean square error of this approximate method for calculating coordinates of curved shock and streamlines is within 1.1%,for calculating pressure,Mach number and velocity angle on compression surface,shock and streamlines is within 4.5%,for calculating average outlet pressure,Mach number and total pressure is within 4.1%.A practical optimization system is established for the curved shock compression flow field design.The method of inverse designing compression surface configuration based on given gas dynamic parameters is applied.Certain key problems as the design parameters setting,automatic flow field computation,and field feature detection are studied.The optimization system could automatically search for design solution satisfying specified requirements,based on the computation and analysis of a large number of design samples,and could also speed up the optimization process by applying design experience of researchers.Several design tests show the validity of the system.In order to further figure out the characteristics of curved shock compression,the effects of design parameters on field performance parameters are analyzed based on large amount of sampling computation data and gas dynamic theory,the compression performance potential is explored through several multi-objective optimization cases,a detailed comparison and analysis is carried out between a set of typical curved shock compression field and traditional compression methods as Multi-ramp compression,Isentropic compression and Ramp-Isentropic compression and the results show that the curved shock compression has obvious advantage.Wind tunnel test of inlet with external compression surface applying curved shock compression is performed,and the results show that the inlet outlet average Mach number is 2.5,total pressure recovery is 0.43,and critical pressure ratio is 195 times under design condition.These research of curved shock compression are further developed to be applied on the internal compression of hypersonic inlet.The series combination method of multiple curved shock compression flow field is proposed,so as integrated inverse design of hypersonic inlet external and internal compression is accomplished.Based on this method,inlet with better comprehensive performance could be obtained through sampling computation and optimization,and one of which is verified through wind tunnel test.The experimental data show that the inlet outlet average Mach number is 2.7,total pressure recovery is 0.51 under design condition,which is consistent with the design expectation.