An aeroelastic prediction model for slender wings in supersonic flow

Abstract: Aeroelasticity is a multidisciplinary subject encompassing several fields of study. Aeroelastic behaviour is defined by the relation between inertial-, elastic- and aerodynamic forces that appear in dynamic systems in steady- or unsteady conditions. Published literature in the field of supersonic aeroelasticity does not generally provide a thorough demonstration of application. Further, high precision methods incorporated in commercial software often require an extensive preparatory phase and entail a significant computational cost. Thus, the absence of rapid and affordable estimation models for supersonic aeroelastic analyses appears evident. Hence, the scope of this report is to demonstrate and describe the development of an estimation model for aeroelastic analysis of wing structures. The developed model should generate rapid results indicative of the true aeroelastic behaviour of slender wings with thin airfoil geometries in varying supersonic flow conditions. The wing is modelled as a structural finite element beam with properties based on Euler bending- and St. Venant torsion theory. Moreover, two quasi-steady aerodynamic models of Piston theory and Unified Oscillatory Supersonic-Hypersonic theory are presented. The aerodynamic models are implemented in the finite element wing model through strip theory. The computational aeroelastic model is assembled to perform aeroelastic analyses in steady- and quasi-steady conditions. The developed models are evaluated against the previously conducted aeroelastic studies of the Torii Matsuzaki wing by Hiroshi Torii and Yuji Matsuzaki and Marius-Corné Meijer. The conclusion regarding the developed model for supersonic aeroelastic analysis is that it generates results rapidly for varying geometries and flow conditions. Unfortunately, when analysing the aeroelastic behaviour of wings with double-symmetric airfoils, a paradox of infinite stability ensues. Due to lack of modern experimental data and time limitations, no further validation of the aeroelastic model is presented. Thus, the developed aeroelastic prediction model cannot presently be fully evaluated as it requires additional work and validation.