| The ramjet engine has many advantages such as simple structure, light weight, littlevolume, big ratio of pushing and gravity, low cost, and etc, so it will be the first choosingpower installation of the long-distance and beyond long-distance cannonball of improvedrange. The inlet is one pivotal component of the ramjet engine, its performance has quitean effect on the range, so the numerical simulation of its flow field is becoming more andmore important and has scientific significance and practical values.This paper has carried on the structural design to the inlet, the design parameterscontain half cone-angle combinations and the rules of expanding pressure. Among, halfcone-angle combinations can be divided into two parts, single cone-shaped and doublecone-shaped, each of them has three kinds of choice. The choice basis of half cone-angle ishigh total pressure recovery. The half cone-angles of single cone-shaped are 25°, 30°and35°. The half cone-angle combinations of double cone-shaped are 20°-13°, 22°-10°and22°-13°. The rules of expanding pressure can be devided into four parts, same expandingangle, same area gradient, same Mach number gradient and same pressure gradient. Thegeneratrixs which satisfy the rules of expanding prssure can be got with relative computeand programs. The fluent software was used to simulate the inlets' two dimensional flowfield related to critical and supercritical status at zero degree attack angle. Then threedimensional flow fieldat four degree attack angle was simulated. The velocity vectors, thepressure contours, the total pressure contours, Mach number contours and surface pressuredistribution of the inlets' flow field were given. The influence of structure parameters onflow structure, total pressure recovery, mass flow ratio and flow field distortion wereanalysed.The conclusions and methods of this paper can be used for the structure design of theinlet in ramjet assisted range projectile and make a good foundation for the followingresearch. |
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