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

Abstract

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.

Keywords

• |submerged inlet|large maneuvering state|nested grid|total pressure distortion index|distortion characteristics|hysteresis effect