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: A method to efficiently generate a complete aerodynamic description for projectile flight dynamic modeling is described. At the core of the method is an unsteady, time accurate computational fluid dynamics simulation that is tightly coupled to a rigid body dynamics simulation. A set of n short time snippets of simulated projectile motion at m different Mach numbers is computed and employed as baseline data. For each time snippet, aerodynamic forces and moments and the full rigid body state vector of the projectile are known. With time synchronized air loads and state vector information, aerodynamic coefficients can be estimated with a simple fitting procedure. By inspecting the condition number of the fitting matrix, it is straightforward to assess the suitability of the time history data to predict a selected set of aerodynamic coefficients. To highlight the merits of this technique, it is exercised on example data for a fin-stabilized projectile. The technique is further exercised for a fin- and spin-stabilized projectile using simulated data from a standard trajectory code.

Generating an aerodynamic model for projectile flight simulation using unsteady time accurate computational fluid dynamic results