Reduced-Order Aerodynamics with the Method of Integrated Circulation

This paper describes an approach for extracting physics-derived aerodynamic load calculations at data rates which are sufficient to support 60 Hz flight dynamic simulations. The load data originates with a surface vorticity solver which has been augmented by the replacement of the inviscid boundary condition with a fully integrated boundary layer model. The resulting aerodynamic load calculations from this solver are of sufficient fidelity to guide the early of subsonic air vehicles. Solutions using geometry that accurately represents the outer mold lines of prospective vehicles require seconds to minutes; however, this paper shows that the solutions can be reduced to geometric elements which are additive. This reduction maintains a high degree of fidelity to the complete configuration solutions while achieving analysis times of approximately 0.01 seconds for typical configurations. The method, verification studies, and sample results are included in the paper.