L. E. Ericsson

TL;DR: In this article, an analytic method is presented which employs static experimental data to predict the separated flow effect on incompressible unsteady aerodynamics, the key parameters in the analytic relationship between steady and nonsteady aerodynamic are the time lag before a change of flow conditions can affect the separation-induced aerodynamic loads, the accelerated flow effect, and the moving wall effect.

TL;DR: The limit cycle oscillation in roll of very slender delta wings is caused by asymmetric vortex shedding from the wing leading edges and not by vortex burst as discussed by the authors, and the breakdown or burst of the leading edge vortices of a delta wing can lead to static instability with associated roll divergence vortex burst however can never be the cause of wing rock because it has a dynamically stabilizing effect on the roll oscillations.

TL;DR: In this paper, an analytic method is described which uses static experimental data to predict the separated flow effect on rigid and elastic vehicle dynamics, and an analytic theory is formulated that can predict the separation-induced unsteady aerodynamics if the static characteristics are known from theory or experiment.

TL;DR: In this article, the authors used the Reynolds number to estimate the pitch rate of the nose tip roll rate of a single forebody vortice, which is based on dmax and freestream conditions; usually Re = Rd Reynolds number, Rd = U^d/v^ reference area.

TL;DR: L'effet de paroi mobile est present aussi bien dans les ecoulements bidimensionnel que tridimensionnels as mentioned in this paper, and influence sur le decollement des couches limites laminaires et turbulentes.