Validation of Compressible-Flow Panel-Methods for the Analysis of the Transonic and Supersonic Aerodynamics of Long-Range Air-Launched Missiles

A computational study has been performed to validate the use of a transonic-capable viscous-coupled panel-method flow solver (FlightStream) on a slender axisymmetric missile configuration with cruciform strakes and cruciform in-line tail control fins. The missile used matches a contemporary long-range air-launched configuration with long, low-aspect ratio strakes interfering with the tail fin controls. Experimental data from NASA/DoD includes angle of attack, roll angle, Mach Number and tail deflection angles, which are replicated in this effort for the computational analysis. Mach numbers ranged from 0.60 to 4.63. The analysis focused on configuration loads and moments across the entire subsonic, transonic and supersonic flight regimes. Selected examples from these numerical and experimental comparisons have been included to illustrate some of the features and trends found in the data and to investigate the validity of such methods for conceptual and preliminary design of long-range air-launched missiles.