Aerodynamic configuration of a missile is defined based on its length, diameter, nose geometry and flare, if any on the tail. The aerodynamic surfaces i.e. wings and fins are designed around the criteria of stability and control. The important dimensions here are span, chord and sweep angle. Each of the above-mentioned geometric parameters affect the drag, lifting and stability of the missile. The design procedure makes use of empirical DATCOM correlations to estimate aerodynamic coefficients. This software app requires input of all geometrical parameters for missile cylinder, fins, wings, nose and tail flare. The output is component wise and integrated aerodynamic coefficients.
Refer: Tool Manual
