A computer code for aerodynamic analysis of sounding rockets at supersonic speeds. (4th August 2014) - Vira, Naren
This article presents a practical and low–cost method of computing the aero–dynamic characteristics of sounding rockets and other similar vehicles, such as high–speed bombs, projectiles and guided missiles in supersonic flight. The vehicle configuration consists of a slender axisymmetric body with a conical or ogive nose, cylinders, shoulders and boattails, if any, and having sets of two, three or four fins. The geometry of the fin cross–section can be single wedge, double wedge, modified single wedge or modified double wedge. First the aerodynamics of the fins and the body are analysed separately; then fin–body and fore– and aft–fin interferences are accounted for when they are combined to form the total vehicle. Results and formulae presented in this work reflect many of the major as well as minor additions, modifications and refinements made to the Theoretical Aerodynamic Derivatives (TAD) computer program originally developed at the NASA Goddard Space Flight Center. New research findings are also incorporated in the TAD computer program which predicts the following six aerodynamic characteristics of a vehicle as functions of the flight Mach number: the normal force coefficient derivative, centre of pressure location, roll forcing and roll damping moment coefficient derivatives, pitch forcing and pitch damping moment coefficient derivatives.