为掌握战斗机在大迎角和过失速机动飞行时进气道的稳、动态气动特性，采用基于动态嵌套网格的非定常雷诺平均Navier-Stokes （URANS）方程和大迎角风洞试验方法对某战斗机进行了研究，并通过大迎角和过失速机动飞行试验进行了验证。结果表明：大迎角稳态下进气道气动性能随迎角增大逐渐降低，天地相关性吻合良好，而计算仿真和飞行试验均捕捉了眼镜蛇机动下进气道的非定常迟滞效应。通过研究获得了战斗机在大迎角和过失速机动下的进气道气动特性，建立了过失速机动下进气道非定常非线性特性问题的研究方法。
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.
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