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50<br />
Stability, transition and flow control of supersonic boundary layer<br />
on swept wing<br />
N.V. Semionov a , A.D. Kosinov a , Yu.G. Yermolaev a<br />
The paper is devoted to an experimental study of disturbances evolution in<br />
linear and non-linear areas of development and transition control in a threedimensional<br />
supersonic boundary layer on swept wing. The problem of transition<br />
to turbulence in 3-D boundary layers is very important and very complicated. In a<br />
3D case exist along with the wellknown TollmienSchlichting waves, which<br />
development results to the turbulent transition in the 2D boundary layers,<br />
stationary vortexes with axes directed along the outer streamlines and some<br />
traveling waves (not TS waves). Development of all instability disturbances and<br />
their relative role in transition strongly depend on the environmental conditions.<br />
The experiments were made in a supersonic wind tunnel T-325 of the ITAM with<br />
test section dimension 200200600 mm at Mach numbers M=2.0 and 3.5. In<br />
experiments the models of swept wing with subsonic or supersonic leading edge<br />
were used. The disturbances were measured by constant temperature hot-wire<br />
anemometer. To measure a transition position the pneumometric or hot-wire<br />
methods were used.<br />
As a result of researches the key difference of a nature of instability in<br />
pressure gradient flat and spatial supersonic boundary layers was revealed. The<br />
transition takes place as a result of interaction of stationary and traveling<br />
disturbances. Is shown, that the main mechanism of turbulence beginning in<br />
supersonic boundary layer on a swept wing - secondary instability of cross-flow.<br />
A technique of control of laminar - turbulent transition on swept wing at<br />
supersonic speeds of flow was designed. The research of disturbances development<br />
in artificial laminarizated supersonic boundary layer on model of a swept wing<br />
from area of a linear stage of development up to area of transition was executed.<br />
This work has been supported by the RFBR grant 05-01-00176.<br />
a Institute of Theoretical and Applied <strong>Mechanics</strong>, Novosibirsk, Russia
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