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冲压发动机或火箭冲压发动机与弹体一体化的问题,从理论上讲包括装有空气喷气推进系统的整个导弹构型的性能与发动机试验台性能(加上弹体、弹翼、控制系统但无发动机舱的外部空气动力特性)之间的各种差异点。本文重点论述了绕细长圆形体的流动特性,以及一个和多个进气道在此种气流中的内部性能。为了对这种性能有所认识,论述了单一进气道在有攻角和偏航角状况下的性能,以及如何采用可调几何尺寸的办法提高性能。本文后半部分论述了涉及外部或弹体一体化的问题,即带发动机舱导弹和不带发动机舱导弹的力和力矩测量以及与发动机舱有关的阻力估价。
The problem of integrating a ramjet or rocket ramjet with a projectile theoretically includes the performance of the entire missile configuration fitted with an air jet propulsion system and the performance of the engine test rig (plus projectiles, wings, control systems but no External aerodynamic characteristics of the engine compartment). This article focuses on the flow behavior around an elongated circular body and on the internal performance of one or more inlets in such airflow. To understand this performance, the performance of a single inlet at both angle of attack and yaw angle is discussed, and how to use adjustable geometry to improve performance. The second half of this article addresses the issues involved in the integration of external or projectile forces, namely force and torque measurements with and without engine compartment missiles, and the valuation of the resistance associated with the engine compartment.