Numerical simulation of the influence of the control surfaces deflection on the aerodynamics of a slender axisymmetric configuration

Abstract

A possible influence of the deflection of control surfaces on the aerodynamics of an axisymmetric slender configuration at supersonic flow speeds is considered. A classical configuration consisting from the fuselage in the form of a body of revolution and having cross frontal fins and six-blade trailing stabilizers is considered as the investigation object. The physical flow pattern at the deflection of horizontal fin consoles is investigated and the estimates are obtained for the influence of this deflection on both the characteristics of elements (the body and stabilizers) as well as on the integral aerodynamic characteristics of the entire configuration. Numerical computations of the flow have been done at the freestream Mach number М = 3 in the range of attack angles α = 0−10° and the angles of the control surfaces deflection δ_cs = ±5° on the basis of the averaged Navier−Stokes equations and the SST k-ω turbulence model.