Method for Rapid Modelling of Missile Aerodynamics

Abstract

In previous work a high-order panel method was found to be a feasible tool for rapid aerodynamic modelling of missiles within preliminary design accuracy. The present paper addresses some issues identified within that work in an attempt to expand the aerodynamic modelling capability based on the panel method. A curve-fit scheme is developed to represent missile aerodynamics across the entire Mach number range. The results show that the aerodynamic coefficients can be modelled using a relatively simple analytic curve as a function of Mach number. The accuracy of the method appears to depend mostly on the original data points and to lesser extent on the curve-fit process. Nomenclature a,b,c,d,e,f = parameters of the aerodynamic coefficient fit curve C = unspecified aerodynamic coefficient C AF = axial force coefficient C Dp = pressure drag coefficient C Lα = lift coefficient slope w.r.t. Angle-of-attack C mα = pitching moment coefficient slope w.r.t. Angle-of-attack C mδ = pitching moment coefficient slope w.r.t. control deflection C NF = normal force coefficient c p = pressure coefficient C PM = pitching moment coefficient M = Mach number α = angle-of-attack φ = roll angle Reference dimensions of the aerodynamic coefficients are maximum cross section area and maximum diameter of missile body.