Aerodynamic Configuration Design of a Missile

Abstract

In this proposed paper the aerodynamic characteristics of various sections such as body, wing and tail of an anti-aircraft missile were computed using analytical methods. Generally predicting the aerodynamic characteristics is mandatory in case of performance analysis. Drag characterization is carried out at different Mach number varying from subsonic to supersonic for different altitudes. It is found that at 15km the drag is reduced to about 23% of that on 5km while considering supersonic Mach numbers. To predict the normal force coefficient values linear wing theory, Newtonian impact theory and slender wing theory is used. Normal force coefficients were calculated at different angle of attacks (1, 5 & 10). This paper also includes predicting of centre of pressure and sizing the tail, which helps in maintaining the missile at static neutral stability. The predicted aerodynamic characteristics were in good agreement with the results in the literature.