Characterization of the flowfield near a wrap-around fin at mach 4.9 Conference Paper uri icon


  • 1997, American Institute of Aeronautics and Astronautics, Inc. The flowfield near a single wrap-around fin on a semicylindrical body has been investigated experimentally and numerically with the objective of quantifying the flow structure in the region near the fin/body juncture at a Mach number of 4.9 and a unit Reynolds number of about 75l06m-1. For the numerical simulation the Navier- Stokes equations were solved employing the an algebraic eddy viscosity model. In the experiment, mean flow data was obtained in the AFIT Mach 5 wind tunnel using conventional pitot and cone-static pressure probes. Shadowgraph and schlieren photography were also used for flow visualization. Comparisons between numerical and experimental data suggests that the calculations have captured the flow physics involved in this complicated flowfield. Comparisons of the numerical results to those previously obtained at Mach 2.8 suggest that the flow structure near the WAF is qualitatively invariant over this range. In particular, the vortical flow structure near the fin/body juncture which was characterized in the Mach 2.8 study is also present at Mach 4.9. However, the strength and location of this juncture vortex changes with the increase in Mach nunmber, causing a more dramatic reduction in computed rolling moment than Euler methods have predicted. This underscores the significance of viscous effects on the rolling moment produced by wrap-around fins.

published proceedings

  • 36th AIAA Aerospace Sciences Meeting and Exhibit

author list (cited authors)

  • Tilmann, C. P., & Bowersox, R.

complete list of authors

  • Tilmann, CP||Bowersox, RDW

publication date

  • January 1998