Computational Fluid Dynamics Analysis of a Missile with Grid Fins

An approach for using viscous computational e uid dynamic simulations to calculate the e owe eld and aerodynamic coefe cients for a missile with grid e ns is presented. A grid e n is an unconventional lifting and control surfacethatconsists of an outer frame supporting an inner grid of intersecting planar surfaces ofsmall chord. The calculations were made at a Mach number of 2.5 and several angles of attack fora missile without e ns, with planar e ns, and with grid e ns. Comparing the computed aerodynamic coefe cients for the missile and individual grid e ns against wind-tunnel measurement data validated the results. Very good agreement with the measured data was observed forall cone gurations investigated. Forthegrid e n case, the aerodynamiccoefe cients werewithin 6.5% of the wind-tunnel data. The normal force coefe cient on the individual grid e ns was within 11% of the test data. The nonlinear behavior of the normal force on the leeward e n at higher angles of attack was also accurately predicted. Nomenclature A = cell face area, m 2 Cm = pitching moment coefe cient based on missile base area and diameter Cp = pressure coefe cient Cx = axial force coefe cient based on missile base area Cz = normal force coefe cient based on missile base area

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