Abstract: The complex flow field of a mixed-compression inlet of solid fuel ramjet extended-ranged projectile with struts was numerically simulated by using the 3D Reynolds-averaged Navier-Stokes equations in terms of different attack angles and inflow Mach numbers, and also the wind tunnel test was made. The schlieren photographs of inlet, the distribution of static pressure along the inlet and the influence of different operations on total pressure at the exit of inlet were obtained. The results indicate that the numerical flow structure and wind tunnel test schlieren photographs of inlet are identical. With the increase in angle of attack, the air flow enters into the inlet, the total pressure recovery coefficient decreases, and the Mach number of exit almost holds the line. At the subcritical state, the influence of attack angle on total pressure recovery coefficient increase significantly, and its value is lower than that in the critical state. Furthermore, under the same inflow Mach number, the total pressure recovery coefficient increases as the backpressure at the exit of inlet raises.

Key words: fluid mechanics, mixed-compression inlet, extended-range projectile, wind tunnel test, numerical simulation