Aerodynamic predictions using supersonic paneling methods accountingfor vorticity and nonlinear compressibility effects

Abstract

Panel and line sinqularity methods can be used to economically predict aerodynamic loads acting on tactical missiles. Due to high maneuverability and hiqh speeds encountered by supersonic missiles, nonlinear corrections are required in detailed aerodynamic predictions to account €OK vortex wakes and shocks. Airbreathing missiles can be affected by mutual inlet/airframe interference and by additional aerodynamic forces associated with inlet off-design operation. Methods are summarized €or apnroximating vortex formation and wakes on missiles. Combined nonlinear/linear theory for pressure calculations is OUtlined. A preliminary method for modeling two-dimensional supersonic inlets with a panel method is summarized, and a nonlinear correction to account for the presence of shock waves in flow fields is referenced. Comparisons with experiment indicate that panel and line singularity methods in conjunction with nonlinear corrections can predict detailed missile loadings. Additive forces associated with supersonic inlets can be estimated with a panelinq method. Linearly calculated flow field results are improved by incorporating shock wave simulations and local Mach number variation.