Aeroelastic predictions of a thin panel in supersonic flow with a shock/boundary layer interaction (SBLI) are evaluated relative to wind tunnel experiments. Measured time histories of the panel displacement and velocity show stationary deflections as well as post-flutter oscillations for a range of shock impingement strengths. The fully coupled, computationally efficient aeroelastic modeling framework is formulated with a nonlinear structural reduced-order model and quasi-steady enriched piston theory aerodynamics. The aeroelastic model predicts the observed shape of the stationary responses with correlation coefficients larger than 0.8 for all SBLI conditions. In regards to dynamic responses, the model captures flutter onset as well as the post-flutter periodic oscillations for attached SBLI. The system’s sensitivity to different initial conditions and shock impingement location is also investigated for attached SBLI. Shock-induced flow separation emerges as the SBLI strength increases. For the strongest shock, the computations predict flutter but do not capture the frequency content of the measured post-flutter response. This discrepancy is tied to the breakdown of the quasi-steady flow assumption in piston theory with increasing flow separation and highlights the need for unsteady flow models.

相对于风洞实验，评估了具有冲击/边界层相互作用 (SBLI) 的超音速流中薄板的气动弹性预测。面板位移和速度的测量时间历程显示了固定偏转以及一系列冲击冲击强度的后颤振。完全耦合、计算效率高的气动弹性建模框架由非线性结构降阶模型和准稳态富集活塞理论空气动力学组成。对于所有 SBLI 条件，气动弹性模型预测观察到的静止响应形状，相关系数大于 0.8。关于动态响应，该模型捕获了附加 SBLI 的颤振开始以及颤振后周期性振荡。系统对不同初始条件和冲击冲击位置的敏感性也针对附加的 SBLI 进行了研究。随着 SBLI 强度的增加，出现了冲击引起的流动分离。对于最强的冲击，计算预测颤振但不捕获测量的颤振后响应的频率内容。这种差异与活塞理论中准定常流动假设随着流动分离的增加而失效有关，并突出了对非定常流动模型的需求。