Experimental investigation of supersonic wrap-around fin aerodynamic Mach number effects
Conference Paper
Overview
Overview
abstract
1999 American Institute of Aeronautics & Astronautics. All Rights Reserved. An experimental Mach number parametric (M [2.15, 3.83]) study was conducted to investigate the apparent rolling-moment reduction with increasing Mach number noted in flight test experiments. The aerodynamic loading and the surface flow in the fin region of wrap-around fin missiles in high-Reynolds number (Rec 0.3-0.9 x 106) supersonic cross-streams were investigated using photoluminescent pressure-sensitive paint and surface oil-flow visualizations with fluorescent pigment as the seeding medium. Schlieren photography was used to characterize the fin generated shock structures. Two curved fin missiles were tested, one having a solid fin, and the other, a slotted fin. The fin pressures were integrated for rolling-moments; these data confirmed the solid-fin-missile reduction in rolling-moment with increasing Mach number. The slotted-fin missile exhibited a similar rolling-moment Mach number dependence. Analysis of the pressure distributions, surface streamlines, and shock structures indicated that the flowfields experienced very strong and complicated inviscid-viscous interactions, and that these interactions had a significant impact on the aerodynamic loading of the fins. Finally, the slotted-fin-missile demonstrated the potential for increased roll stability and reduced wave drag.
