INFLUENCE OF SMALL ANGLES OF ATTACKS ON THE LAMINAR-TURBULENT TRANSITION ON A SWEPT WING AT MACH NUMBER M = 2

Read more Experimental studies on the effect of small angles of attack on the laminar-turbulent transition of swept-wing supersonic boundary layer have been performed. In the experiments, a 3 % symmetrical swept-wing model with a lenticular profile and a swept angle of 45° was used. The position of the transition was determined using a hot-wire anemometer. The growth of pulsations was measured. The positions of the laminar-turbulent transition were determined. The amplitude-frequency pulsation spectra in the supersonic boundary layer were obtained for certain values of the angle of attack. In the framework of the linear theory of stability, calculations on the effect of small angles of attack on the development of perturbations were provided. A comparison of the experimental Reynolds number of the transition for different values of the angle of attack of the model and the calculated dependences obtained for different values of the N-factor was made. The results of calculations on the linear stability theory are in good qualitative agreement with the experimental data.

Keywords:
supersonic boundary layer, swept wing, laminar-turbulent transition, angle of attack.
УДК 532.526

INFLUENCE OF SMALL ANGLES OF ATTACKS ON THE LAMINAR-TURBULENT TRANSITION ON A SWEPT WING AT MACH NUMBER M = 2