Abstract:Results of experiments aimed at studying the linear and nonlinear stages of the development of natural disturbances in the boundary layer on a swept wing at supersonic velocities are presented. The experiments are performed on a swept wing model with a lens-shaped airfoil, leadingedge sweep angle of 45 • , and relative thickness of 3%. The disturbances in the flow are recorded by a constant-temperature hot-wire anemometer. For determining the nonlinear interaction of disturbances, the kurtosis and skewness are… Show more
“…14 To avoid this and to achieve prolongation of the linear stage in the developing disturbance, two new swept wing models (one for natural experiments and another for controlled experiments 15 ) were made with the same level of surface curvature, but with reduced thickness of 3% thickness of the profile. Experiments 14,16,17 under natural conditions performed at M = 2 and low unit Reynolds numbers have revealed that the distance from the leading edge to the onset of transition increased several times in comparison with the above mentioned experiments. 13 This enables investigating the details of the evolution of disturbances in the supersonic boundary layer on swept wing, both in a controlled and natural experiment.…”
Section: Introductionmentioning
confidence: 60%
“…18 This research is a continuation of a series of experimental studies of the origin of turbulence on the swept wing (Figure 1) in a supersonic flow. 14,16,17,19,20 The results of these studies will be useful in the creation of modern engineering methods for predicting the position of the laminar-turbulent transition. Figure 1.Swept wing model: (a) top view; (b) aerofoil.…”
The paper is devoted to an experimental and theoretical study of effect of moderate angle-of-attack variation on disturbances evolution and laminar-turbulent transition in a supersonic boundary layer on swept wing at Mach 2. Monotonous growth of the transition Reynolds numbers with angle of attack increasing from −2° to 2.7° is confirmed. For the same conditions, calculations based on linear stability theory are performed. The experimental and computational results show a favourable comparison.
“…14 To avoid this and to achieve prolongation of the linear stage in the developing disturbance, two new swept wing models (one for natural experiments and another for controlled experiments 15 ) were made with the same level of surface curvature, but with reduced thickness of 3% thickness of the profile. Experiments 14,16,17 under natural conditions performed at M = 2 and low unit Reynolds numbers have revealed that the distance from the leading edge to the onset of transition increased several times in comparison with the above mentioned experiments. 13 This enables investigating the details of the evolution of disturbances in the supersonic boundary layer on swept wing, both in a controlled and natural experiment.…”
Section: Introductionmentioning
confidence: 60%
“…18 This research is a continuation of a series of experimental studies of the origin of turbulence on the swept wing (Figure 1) in a supersonic flow. 14,16,17,19,20 The results of these studies will be useful in the creation of modern engineering methods for predicting the position of the laminar-turbulent transition. Figure 1.Swept wing model: (a) top view; (b) aerofoil.…”
The paper is devoted to an experimental and theoretical study of effect of moderate angle-of-attack variation on disturbances evolution and laminar-turbulent transition in a supersonic boundary layer on swept wing at Mach 2. Monotonous growth of the transition Reynolds numbers with angle of attack increasing from −2° to 2.7° is confirmed. For the same conditions, calculations based on linear stability theory are performed. The experimental and computational results show a favourable comparison.
Experimental results are presented on the linear development of a wave train in a three-dimensional supersonic boundary layer on a swept wing with 45°-sweep angle at Mach number M = 2.0. Artificial disturbances in the boundary layer were excited by periodical glow discharge mainly at frequencies 10 and 20 kHz. The maximum of the controlled pulsation amplitude was localized in the boundary layer in normal to the swept-wing surface direction for spatial amplitude distributions as well as for the amplitude wave spectra. The asymmetry of the wave characteristics of the unstable disturbances in the boundary layer of a swept wing caused by the presence of crossflow is confirmed. The stability characteristics, including dispersion relations and amplification rates over a wide range of wave inclination angles, are obtained for disturbances with prescribed frequencies 10 and 20 kHz.
scite is a Brooklyn-based organization that helps researchers better discover and understand research articles through Smart Citations–citations that display the context of the citation and describe whether the article provides supporting or contrasting evidence. scite is used by students and researchers from around the world and is funded in part by the National Science Foundation and the National Institute on Drug Abuse of the National Institutes of Health.
