Experiment And Numerical Simulation On The Inlet's Flow Field Of Ramjet Pill Assisted Range Projectiles

This paper referred to simulating the supersonic double cone inlet' s flow field of ramjet pill assisted range projectiles at a variety of working circumstances, pressure contours, density contours and Mach number contours of inlet' s flow field were given' When cone combination, relative location of cone core and cowl lip, the pressure of outlet, inflow Mach number and angle were changed, flow field and performance parameters of inlet can be affected. Simultaneity, productive mechanism and inducing factors of the inlet surge were also discussed. Then the best working conditions and the best model of inlet were obtained. After inlet model' s three dimensional structural grid was generated, proper numerical scheme and onflow model were choosed, then numerical computation on flow field of inlet was taken, finally the better results were got. At the same, wind-tunnel experimental research about some inlet model was fulfilled. Then, results of wind-tunnel experiment and results of numerical simulation were comparised, error ratio was under permission range, which ulteriorly validated the reliability of numerical simulation method. Therefore, the conclusions and method of this paper can be helpful to design the inlet of improved range's cannonball theoretically and technologically.