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ASYMMETRY AND NON-UNIQUENESS OF THE SOLUTION TO THE PROBLEM OF A SEPARATED FLOW ABOUT A SLENDER WING/LOW-ASPECT-RATIO BODY CONFIGURATION WITH SIDESLIP

Volumen 43, Edición 2, 2012, pp. 147-154
DOI: 10.1615/TsAGISciJ.2012005494
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SINOPSIS

Earlier investigations into the problem of a separated flow about a slender wing/low-aspect-ratio body configuration with zero sideslip show that the flow becomes asymmetrical at angles of attack greater than 13 °, and a considerable side force appears. It is obvious that two mirror-symmetrical solutions with the side force having identical absolute values with opposite signs have to exist. The present paper is devoted to obtaining such solutions and to investigating the flow about the configuration with non-zero sideslip angles β. The computations show that the side force is an essentially nonlinear function of the sideslip angle at sufficiently high angles of attack. The cz (β) curves acquire the form of a loop, and the problem at | β | < 4−5° has two solutions. The derivatives of the side force coefficient cz with respect to the sideslip angle at β = 0 become negative. At angles of attack greater than 35°, the flow is accompanied by an asymmetrical breakdown of the vortex shed from one of the wing edges, which affects the aerodynamic forces acting on the configuration. Computed flow patterns in a cross section of the conical part of the model are presented to illustrate specific features of the flow.

REFERENCIAS
  1. Peake, D. J., Owen, F. K., and Hoguchi, H., Symmetrical and asymmetrical separations about a yawed cone.

  2. Voevodin, A. V., Assymetry and nonuniqueness of the solution to the problem of separated flow over a slender conical wing–body combination.

  3. Wardlaw, A. B., Jr., Multivortex model of symmetrical shedding on slender bodies at high angle of attack.

  4. Zakharov, S. B. and Zubtsov, A. V., Experimental study of a separated flow about a low-aspect-ratio delta wing.

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