Quantitative diagnostics of shock wave - boundary layer interaction by digital speckle photography

Фомин, Н. А.; Lavinskaya, E. I.; Doerffer, Piotr; Szumski, J.-A.; Szwaba, Ryszard; Telega, Józef Joachim

doi:10.1007/978-3-540-85168-4_73

Cited by 8 publications

(6 citation statements)

References 9 publications

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“…Different tripping devices may be used to induce the transition in the boundary layer; however, the presented experiments focused on the effects of roughness and microsteps on the unsteady aerodynamic phenomena in a compressor fan blade passage. For this purpose, a model of a compressor passage was designed and assembled in a wind tunnel [19] (at the Institute in Gdansk) in order to investigate the flow structure on the suction side of the blade. e compressor passage model was mounted in a rectilinear test section of a transonic wind tunnel, as shown in Figure 1(a).…”

Section: Methodsmentioning

confidence: 99%

Transition Effect on the Flow Dynamics in a Compressor Blade Passage

Szwaba

Kaczyński

Telega

2021

Shock and Vibration

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An experimental investigation was carried out to study the effect of the boundary layer transition on the flow dynamics in the blade passage of a compressor cascade. A model of a turbine compressor passage was designed and assembled in a transonic wind tunnel for this purpose. Two different flow control methods were used in the experiment to induce the transition upstream of the shock wave, one concerning the microstep application and the other using distributed roughness strips. Two locations of spanwise microsteps for the transition trigger were chosen, one at the leading edge and the other closer to the shock wave position. The distributed roughness in the form of standard sandpaper strips with different heights was applied in three various locations on the blade upstream of the shock. The main objective of investigations is to present the influence of the laminar and turbulent shock wave-boundary layer interaction on the flow dynamics in a compressor fan passage, and the specific objective is to show how the parameters of particular transition control methods affect the flow dynamics in the investigated channel. The major challenge for this research was to minimize the disturbance caused by the microstep or roughness to the laminar boundary layer, while still ensuring a successful transition. Very interesting results were obtained in the flow control application for the boundary layer transition control, demonstrating a positive effect on the flow unsteadiness in changing the nature of the interaction.

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Section: Methodsmentioning

confidence: 99%

Transition Effect on the Flow Dynamics in a Compressor Blade Passage

Szwaba

Kaczyński

Telega

2021

Shock and Vibration

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“…The internal dimensions of the test stand were 1800 mm long, 350 mm high and 100 mm wide. More details about experimental facility are included in Fomin [10]. In order to investigate the aircraft airfoil in cruise conditions the dedicated test section was designed based on the reference flow data delivered by AIRBUS Toulouse.…”

Section: Methodsmentioning

confidence: 99%

“…Other example of measurement in medium size wind tunnel but in subsonic condition can be found in F. Grasso [8] which investigation was also intended for measurement of airfoil from wind turbine together with optimisation process and numerical calculation. However, wind tunnel measurements are sensitive on any errors thus one should put a great attention to details and procedures in order to avoid potential issues which can result from adequate model size regard to wind tunnel dimensions, proper model positioning or secondary flows [9] It is also worth pointing out that the test campaigns in large transonic wind tunnels are expensive and the power needed for the their operation often reaches 1MW, therefore, it was taken the challenge to carry out this type of measurements in a smaller wind tunnel [10], in which the cost of testing is about one order lower.…”

Section: Introductionmentioning

confidence: 99%

Wind tunnel investigations of aircraft airfoil in cruise conditions

Kaczyński

Szwaba

Piotrowicz

et al. 2022

J. Phys.: Conf. Ser.

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Presented work is focused on analysis of the flow over the 2D model of Airbus A320 airfoil wing in cruise phase of the flight. For this purpose the measurement channel with an airfoil model was designed and assembled in a transonic wind tunnel to obtain a similar flow pattern as in the reference two-dimensional freestream flow. Experimental investigations were conducted in the IMP PAN transonic wind tunnel with a relative narrow test section which is a novel approach in terms of these type of research. The test section was designed using CFD simulations based on 2D freestream flow for the tested wing profile and in the next step the research were continued experimentally in transonic wind tunnel with a measurement chamber width of 100 mm. This paper presents the results of reference investigations on the A320 wing profile which combines experimental tests and CFD calculations. The obtained results show that the approach presented in the paper is appropriate and the obtained flow features in the tunnel do not differ much from the freestream conditions.

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“…The measurements were carried out at the IMP PAN supersonic wind tunnel facility. The wind tunnel is an intermittent, vacuum type wind tunnel, described in more detailed manner in [25]. The test section with a nozzle is schematically depicted in Figure 3.…”

Section: Methodsmentioning

confidence: 99%

Shock Waves Asymmetry in a Symmetric Nozzle

2019

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The results of the experimental research on the symmetry of supersonic flow in a symmetric convergent-divergent nozzle are presented. The investigations were focused on the fact that for some flow conditions the flow in a precisely symmetric nozzle becomes asymmetric. Starting from a specific value of Mach number, the flow becomes asymmetric in terms of shock wave λ-foot geometry on both sides of a symmetric nozzle. The evolution of the abovementioned asymmetry has been analysed for Mach number value ranging from M = 1.26 to M = 1.59 with the nozzle opening angle of up to 6.5° on each side. The presented results indicate that for the same flow parameters as Mach number and Reynolds number, and for the same geometry of the nozzle, different λ-foot size is formed at each wall. This unexpected behaviour is responsible for the flow asymmetry. Numerical simulations carried out earlier confirm the appearance of shock wave asymmetry. The side in which the asymmetry takes place is accidental, as the full symmetry of simulation mesh and experiment setup was secured. In numerical simulation the asymmetry follows always the same direction. In experiments the direction of asymmetry happens alternatively without any apparent reason. The explanation of the phenomena is provided in this paper.

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Quantitative diagnostics of shock wave - boundary layer interaction by digital speckle photography

Cited by 8 publications

References 9 publications

Transition Effect on the Flow Dynamics in a Compressor Blade Passage

Transition Effect on the Flow Dynamics in a Compressor Blade Passage

Wind tunnel investigations of aircraft airfoil in cruise conditions

Shock Waves Asymmetry in a Symmetric Nozzle

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