Research On Plasma Flow Field Control Technology Of Combined Power Adjustable Inlet

In recent years,plasma aerodynamic excitation flow field control technology has become a research hotspot of scholars in various countries in improving the aerodynamic performance of aircraft.In the concept of bending shock wave aerodynamic regulation,based on the thermal effect of plasma aerodynamic excitation,the flow field control technology of wide-speed inlet port is studied.Firstly,the effects of the length,thickness and temperature of the plasma aerodynamic excitation zone on the starting performance of the two-dimensional bending shock inlet are studied under low mach number.It is found that there are limit values for the length,thickness and temperature of the plasma action zone.The thickness is the key factor affecting the plasma aerodynamic excitation effect.At the same time,comparative analysis shows that with the increase of the number of suction holes,the plasma aerodynamic excitation can make the inlets start at a lower Mach number.Then the application mode of plasma flow field control technology in super-rated operation of wide-speed inlet is studied.The inlet model with sealing mach number of 4.0 is designed,and plasma aerodynamic excitation is applied.The numerical simulation of the flow field evolution process was carried out when the mach number was 5.0.The influence of the distribution position of the plasma action zone on the external shock wave control of the inlet compression surface is analyzed.It is found that the effect of pushing the shock wave re-attachment is optimal when the plasma action zone is located in the middle and rear sections of the curved wall of the inlet.At the same time,the two-dimensional numerical simulation of the full flow channel was carried out in the working Mach number range.It was found that the flow coefficient was basically improved by more than 20% compared with the conventional fixed geometry inlet with a sealing mach number of 5.0.The total pressure recovery coefficient between the incoming Mach numbers between 2.5 and 4.0 has been improved to varying degrees.Finally,based on the aerodynamic model of the two-dimensional bending shock inlet,the numerical simulation of the three-dimensional flow field is carried out.It is found that the total width of the plasma action zone needs to reach a certain value to achieve the plasma aerodynamic excitation of to push the external pressure shock wave to re-sealing.When the total width is constant,reducing the width of a single plasma active zone while increasing its number can make the flow field of the inlet more uniform.