关键词: 进气道, 动态嵌套网格, 大迎角稳态, 过失速机动, 相关性分析, 迟滞效应

Abstract: In order to capture the inlet aerodynamic characteristics of fighter under high angles of attack and unsteady nonlinear post-stall maneuvers, the Unsteady Reynolds Averaged Navier-Stokes (URANS) numerical simulation employing dynamic overset grids technique and wind tunnel tests are used. Flight tests under above conditions are adopted for validation and in-depth analysis. Results indicate that under high angle of attack steady state, wind tunnel test prediction matches well with flight test data and both reveal inlet performance reduction as the angle of attack increases. The unsteady over-loop effects of the inlet under cobra maneuver are observed in both URANS calculations and flight tests. Furthermore, fighter inlet aerodynamic characteristics are uncovered under high angle of attack and post-stall maneuver conditions in the scope of current investigation. The method for inlet unsteady and nonlinear characteristics analysis is finally established.

Key words: inlet, dynamic overset grids, high angle of attack steady state, post-stall maneuver, relevance analysis, over-loop effect