Flow-Separation Lines on Axisymmetric Bodies with Tapered Tails

摘要

WHEN a slender body of revolution translates at moderatenincidence (5 deg u0005 u0001 u0005 30 deg), adverse pressure gradientsndue to the crossflow cause the boundary layer to separate on thenleeside and produce two shear layers that roll up to form symmetricnvortices of opposite rotation [1,2]. The flow separation results innsignificant aerodynamic forces andmoments that depend strongly onnincidence. Although these bodies have relatively simple geometry,nthey have been historically difficult tomodel, because they lack sharpnedges that fix the separation lines. The present work extends the separation-line model of Schindel [3], developed for missiles, tonbodies of varying cross-sectional area, allowing one to predict thenseparation line along the tapered tail.