大机动工况下内埋式进气道非定常流场特性分析

Research on Unsteady Flow Field Characteristics of Submerged Inlet under Large Maneuver Condition

为探究大机动飞行时埋入式进气道的稳、瞬态气动特性之间存在的差异,本文以巡航导弹为研究对象,采用CFD数值方法对埋入式进气道进行稳、瞬态分析。研究表明:大机动过程中瞬态与等效稳态计算结果的趋势保持一致,但结果存在一定差异。当弹体及进气道作周期性俯仰运动时,瞬态与稳态计算的总压恢复系数相差最大时约为2%;当弹体及进气道作周期性偏航运动时,瞬态与稳态计算的总压恢复系数相差最大时约为7%。同时,在瞬态计算结果中存在明显的迟滞效应,该迟滞效应随着机动过程中角速度的增大而更加明显。

In order to explore the differences in steady-state and transient aerodynamic characteristics of submerged inlets during high maneuvering flight,this study focuses on cruise missile and adopts CFD numerical methods to conduct steady-state and transient analysis of the submerged inlets.The research indicates that the trends of the transient and equivalent steady-state calculations during high maneuvering remain consistent,but there are certain differences in the results.When the missile body and inlet undergo periodic pitching motion,the maximum difference in total pressure recovery coefficient between transient and steady-state calculations is about 2%.When the missile body and inlet undergo periodic yawing motion,the maximum difference in total pressure recovery coefficient between transient and steady-state calculations is about 7%.Additionally,there is a noticeable hysteresis effect in the transient calculation results,which becomes more pronounced with the increase in angular velocity during the maneuvering process.