On introduction of controlled disturbances into a longitudinal vortex in a supersonic boundary layer

Theoretical and an experimental research results of the disturbances development in a swept wing boundary layer are presented at Mach number М = 2. In experiments development of natural and small amplitude controllable disturbances downstream was studied. Experiments were carried out on a swept wing model with a lenticular profile at a zero attack angle. The swept angle of a leading edge was 40°. Wave parameters of moving disturbances were determined. In frames of the linear theory and an approach of the local self-similar mean flow the stability of a compressible three-dimensional boundary layer is studied. Good agreement of the theory with experimental results for transversal scales of unstable vertices of the secondary flow was obtained. However the calculated amplification rates differ from measured values considerably. This disagreement is explained by the nonlinear processes observed in experiment

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Sensitivity of a supersonic boundary layer to acoustic disturbances

Fluid Dynamics ◽

10.1007/bf01054169 ◽

1992 ◽

Vol 27 (1) ◽

pp. 29-34 ◽

Cited By ~ 7

Author(s):

A. V. Fedorov ◽

A. P. Khokhlov

Keyword(s):

Boundary Layer ◽

Supersonic Boundary Layer ◽

Acoustic Disturbances

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Heat Transfer Effects of a Longitudinal Vortex Embedded in a Turbulent Boundary Layer

Journal of Heat Transfer ◽

10.1115/1.3248039 ◽

1987 ◽

Vol 109 (1) ◽

pp. 16-24 ◽

Cited By ~ 99

Author(s):

P. A. Eibeck ◽

J. K. Eaton

Keyword(s):

Heat Transfer ◽

Boundary Layer ◽

Turbulent Boundary Layer ◽

Delta Wing ◽

Stanton Number ◽

Longitudinal Vortex ◽

Test Facility ◽

Pressure Probe ◽

Transfer Effects ◽

Heat Transfer Effects

The heat transfer effects of an isolated longitudinal vortex embedded in a turbulent boundary layer were examined experimentally for vortex circulations ranging from Γ/U∞δ99 = 0.12 to 0.86. The test facility consisted of a two-dimensional boundary-layer wind tunnel, with a vortex introduced into the flow by a half-delta wing protruding from the surface. In all cases, the vortex size was of the same order as the boundary-layer thickness. Heat transfer measurements were made using a constant-heat-flux surface with 160 embedded thermocouples to provide high resolution of the surface-temperature distribution. Three-component mean-velocity measurements were made using a four-hole pressure probe. Spanwise profiles of the Stanton number showed local increases as large as 24 percent and decreases of approximately 14 percent. The perturbation to the Stanton number was persistent to the end of the test section, a length of over 100 initial boundary-layer thicknesses. The weakest vortices examined showed smaller heat transfer effects, but the Stanton number profiles were nearly identical for the three cases with circulation greater than Γ/U∞δ99 = 0.53 cm. The local increase in the Stanton number is attributed to a thinning of the boundary layer on the downwash side of the vortex.

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Detachment of a supersonic boundary layer in front of the bottom edge of a contour of a body

USSR Computational Mathematics and Mathematical Physics ◽

10.1016/0041-5553(88)90164-4 ◽

1988 ◽

Vol 28 (2) ◽

pp. 177-184

Author(s):

M.A. Kravtsova ◽

A.I. Ruban

Keyword(s):

Boundary Layer ◽

Supersonic Boundary Layer ◽

Bottom Edge

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