Researches into the effects of asymmetric fluid flow bias around the projectile on aerodynamic coefficients

Abstract

In the analysis of projectile flight dynamics it is of utmost importance to know the values of aerodynamic coefficients and their derivatives. The calculation of flight path elements and projectile flight stability is practically impossible without these values. The purpose of this paper is the automation in the process of calculation of unguided projectile aerodynamic coefficients for different angles of attack. The movement of every projectile with axial symmetry in space consists of mass center translation and rotation around its own mass center. The flight of these projectiles is characterized by the conditions of slight perturbances, supposing that angles of attack do not exceed several degrees. This fact enables the application of laws of linear aerodynamics while calculating aerodynamic characteristics or their derivatives. The projectile often has complex geometric configuration and the calculation of aerodynamic characteristics is thus connected with the previous knowledge of aerodynamics of their configuration elements. The program solution AERO 1 is made in FORTRAN, it is universal and can be applied to all classical projectiles without fins.

Keywords

• aerodynamic coefficient
• aerodynamic force and moment
• asymmetric fluid flow bias
• derivative of the aerodynamic coefficient
• angle of attack
• mass center