The basic aerodynamic characteristics and control surface effectiveness of three axisymmetric projectile configurations were studied experimentally at supersonic speeds. The test configurations included a previously studied generic body with fins and augmented versions with cropped delta wings and split canards. Measurements were carried out at Mach 2 and 4 at the Florida State University Polysonic Wind Tunnel (PSWT). Control surface deflections investigated in this study included 20° tail fin deflections and 10° rear canard deflections. Flow visualization techniques using high speed shadowgraphy and surface oil flow were carried out to study the complex fluid dynamic flow features. Results indicate that the delta wing model was able to significantly improve the lift to drag ratio when compared to the baseline model. The split canard model was able to display slightly enhanced maneuverability than the baseline model with only tail fins, with a minimal addition to drag as compared to the baseline model. There is an evidence of forebody and control surface vortex interactions, which needs to be further investigated in the future.
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