Computational Study of the Magnus Effect on Boattailed Shell

Sturek, Walter B.; Mylin, Donald C

doi:10.2514/3.51208

Cited by 1 publication

(1 citation statement)

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“…[15,20,22,30,31] focus on wind tunnel or flight tests, and Refs. [14,16,18,19,21,[23][24][25][26][27][28][29][32][33][34][35][36][37][38][39][40] on numerical prediction and validation. ' An example of the resultant Magnus force coefficient distribution in the drag plane (plane that contains the longitudinal axis of the projectile and the upstream flow velocity vector) combined with the skin friction lines pattem is shown in Fig.…”

Section: Introductionmentioning

confidence: 99%

Magnus Effect: Physical Origins and Numerical Prediction

Cayzac

Carette

Denis

et al. 2011

Journal of Applied Mechanics

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An oven'iew of the Magnus effect of projectiles and missiles is presented. The first part of the paper is devoted to the description of the physical mechanisms governing the Magnus effect. For yawing and spinning projectiles, ai small incidences, the spin induces a weak asymmetry of the boundary layer profiles. At high incidences, increased spin causes the separated vortex sheets to be altered. Vortex asymmetiy generates an additional lateral force which gives a vortex contribution to the total Magnus effect. For finned projectiles or missiles, the origin of the Magnus effect on fins is the main issue. There are two principal sources contributing to the Magnus effect. Firsilw the interaction between the asymmetric houndary layer-wake of the hody and the fins, and secondly, the spin induced modifications of the local incidences and of the flow topology around the fins. The second part of the paper is devoted to the numerical prediction and validation of these flow phenomena. A state of the art is presented including classical CFD methods based on Reynolds-averaged Navier-Stokes (RANS) and unsteady rans (URANS) equations, and also hybrid RANS/LES approach called ZDES. This last method is a recent advance in turbulence modeling methodologies that allows to take into account the unsteadiness of the flow in the base region. For validation purposes computational results were compared with wind tunnel tests. A wide range of angles of attack, .^pin rates. Reynolds and Mach numbers (subsonic, transonic and supersonic) have heen investigated.

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