Control of Separated Flow over Swept Missile Fin Using Pitching Oscillations

Abstract

Nomenclature b = maximal span of fin c = root chord of fin f = frequency of pitching oscillations F = nondimensional frequency Re c = Reynolds number based on c u = longitudinal velocity x=c = nondimensional longitudinal location = angle of attack = amplitude of oscillations = sweep angle

Zonal Detached-Eddy Simulation Applied to the Tip-Clearance Flow in an Axial Compressor

“…Thus it is flexible and suitable for simpleboth academic and industrial applications. Moreover, it was already applied to a wide panel of cases, from the simulation of an aircraft, [16][17][18][19] to jet, 20,21 and base flows, 22,23 through the flow control applications 24,25 , the flow around a simplified launcher afterbody 26 and the dynamic stall over rotorcraft airfoil. 27,28 This method is also well-suited for wall bounded flows, especially for wall resolved LES 29 and wall modeled LES.…”