Flow separation about ellipttic cones at incidence

Flow separation about ellipttic cones at incidence

Crabbe, R.S.

National Research Council Canada, National Aeronautical Establishment, High Speed Aerodynamics Section

1965-08-31

A method is presented for calculating the separation of a laminar incompressible boundary layer about a right elliptic cone at incidence. Slender body theory is used to formulate a conical surface flow field, and Cooke's small cross-flow method is then applied to the boundary layer. The separation !ine is shown to lie a long a generator. When applied to the prediction of separation on two elliptic cones, each at zero roll and 900 roll (pure pitch and pure yaw), and one circular cone, the method gives good agreement with experiment al results over an incidence range in which s lender body theory may be expected to apply. In the cases of the two elliptic cones it is most accurate for the stenderer at zero roll and least accurate for the thicker at 900 roll. The calculations reveal the existence of inviscid flow separation lines on the leeward surface of the elliptic cones at 900 roll. These occur where the inviscid zero-incidence cross-flow is cancelled by that due to incidence, and are the locations of "lobes" of boundary layer fluid. The lines coincide on the leeward attachment line at an incidence weil below th at required for the onset of boundary layer separation

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National Research Council Canada

Campus only

National Research Council Aeronautical Report LR 436

Aerospace Engineering Reports

report

(c)1965 National Research Council Canada