Invariant Vortex-Force Theory Extending Classical Aerodynamic Theories to Transonic Flows

Recent studies about the Lamb vector have led to development of vortex-force theory: a formulation able predict aerodynamic force in compressible flows and decompose it into lift, lift-induced drag, profile drag. Here, revised theory developed at ONERA collaboration with University Naples is presented applied steady transonic flows. In mathematical developments, special care given presence shock wave discontinuities within flowfield. The equivalence between new definition, Kutta–Joukowski lift theorem, Maskell’s drag formula (“Progress Towards Method for Measurement Components Drag Wing Finite Span,” Procurement Executive, Ministry Defence, Royal Aircraft Establishment TR 72232, Farnborough, England, U.K., 1972) Betz’s (“A Direct Determination Wing-Section Drag,” NACA TM 337, 1925) are emphasized. also presents several practical advantages: decomposition naturally invariant reference point chosen calculation moment transformations, computation can be performed fine part grid, close body skin. finally tested on NASA Common Research Model wing–fuselage configuration cruise flight conditions.