Experimental study of stability and transition of supersonic boundary layer on swept wing at mach number 2-4

The paper is devoted to an experimental study of the laminar€ turbulenttransitionandtheinstabilitydisturbancesevolutioninathreedimensional(3D)supersonicboundarylayeronasweptwingwithsharp and blunted leading edges at M=2€4. The detailed data of the natural disturbances development are obtained. Characteristic zones of disturbances evolution are determined. It is found that for Mach numbers 2 and2.5measurementscanbe performedinthe regionofthelinearstage of disturbances evolution, and the experimental data can be compared with the results of the calculations on the linear stability theory. The