Conical gas flows with shock waves and turbulent boundary layer separation |
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Authors: | M A Zubin N A Ostapenko A A Chulkov |
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Institution: | 1.Institute of Mechanics,Moscow State University,Moscow,Russia |
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Abstract: | The results of a theoretical and experimental investigation of nonsymmetric flow around a V-wing with supersonic leading edges
are presented. The range of the angles of attack and yaw, on which additional singular lines are formed on the windward cantilever
of the wing, are experimentally determined using different techniques of flow diagnostics. These are one convergence line
and two divergence lines in the transverse flow which were not previously observable in the calculations of ideal-gas flow
around wings. It is established that the appearance of the three new alternating singular lines located between the central
chord of the wing and a convergence line, exterior to them and occurring within the framework of the ideal gas model, is associated
with the relation between the intensities of two contact discontinuities. One of these proceeds from the branching point of
the bow shock above the leeward cantilever, while the second issues out of the triple point of a λ-shaped shock configuration accompanying developed turbulent-boundary-layer separation generated by an internal shock incident
on the leeward cantilever surface. If the intensity of the contact discontinuity proceeding from the branching point of the
bow shock is large as compared with that of the contact discontinuity of the λ-configuration, then the flow pattern realized on the windward cantilever is analogous to that obtained within the framework
of the ideal gas model, that is, it includes one convergence line on the wing surface. Under these conditions, the results
of the calculations within the framework of the ideal gas model are applicable for understanding the phenomena occurring in
the wing shock layer in a considerable part of the control parameter range, including the regimes with intense internal shocks
generating turbulent boundary layer separation from the leeward cantilever. Corrections should be made only for a carachteristic
pressure distribution in the separation zone and, as a consequence of separation, for an elevated pressure level in the vicinity
of the central chord which is the stagnation line of the transverse flow that has passed across the oblique and terminating
shocks of the λ-configuration and possesses a higher stagnation pressure than the flow that has passed in an ideal gas across the internal
shock incident normally on the leeward cantilever. This is possible only when the divergence line, at which the stream surface
enclosing the turbulent boundary layer separation zone enters, does not go over from the leeward onto the windward cantilever. |
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