Aerodynamic and Aeroelastic Characterization of a Forward-Swept, Laminar Aircraft Wing under Realistic Flight Conditions

Kurzfassung

This study presents the aerodynamic and aeroelastic characteristics of a forward-swept laminar wing model tested in a cryogenic transonic wind tunnel under flight-relevant Mach and Reynolds numbers. A novel pitch oscillator enabled forced pitch oscillations, allowing for dynamic load and response analysis. Static tests reveal typical lift and drag trends with increasing Mach number, accompanied by increased bending deformation and reduced twist. Pressure measurements at four spanwise locations identify a spanwise-shifting shock system, including a double-shock structure near the root, which emerges only above critical flow conditions. Unsteady acceleration data show amplified tip accelerations and stronger trailing-edge responses, whose frequency spectra reveal the structural eigenmodes with slight shifts due to aerodynamic effects. Unsteady pressure coefficients reveal a distinct phase shift at the shock location, causing a significant lag in the pressure response relative to angle of attack. Overall, the results provide a detailed insight into the coupled aerodynamic and aeroelastic behavior of a forward-swept, laminar wing under transonic flow.