Laminar-turbulent transition tripped by step on transonic compressor profile

Flaszyński, Paweł; Doerffer, Piotr; Szwaba, Ryszard; Piotrowicz, Michal; Kaczyński, Piotr

doi:10.1007/s11630-018-0977-4

Cited by 7 publications

(4 citation statements)

References 2 publications

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“…The velocity profile in experimental investigations characterizes similar thickness as in numerical simulations, however in the centre of the wake a lower velocity was obtained as well for AoA of 1.8 ○ and 2.4 ○ . This is an expected result, because numerical simulations are quite often characterized by a larger velocity decrease [12] at this point. Figure 13 shows the results of the drag and lift coefficient measurements determined based on forces measured using aerodynamic balances.…”

Section: Resultssupporting

confidence: 61%

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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Section: Resultssupporting

confidence: 61%

Wind tunnel investigations of aircraft airfoil in cruise conditions

Kaczyński

Szwaba

Piotrowicz

et al. 2022

J. Phys.: Conf. Ser.

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“…Transition within the boundary layer can be forced through application of surface roughness [4], a turbulator step [5], or air-jet vortex generators (AJVG) [6]. Although such passive control methods are already in use for the boundary layer separation control [7,8], the mechanism of the shock wave-laminar boundary layer interaction and, in particular, the source of the strong shock unsteadiness are still not well understood.…”

Section: Introductionmentioning

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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“…Based on the effectiveness of the flow structure in the blade passages, the optimal location of the suction slots on the upper and lower wall has been determined. Additionally, these suction slots and perforated walls also help in achieving the required inflow conditions in the test section [20]. The number of blades in the test section was chosen to be three blades based on multiple aspects like test section configuration, experimental feasibility, etc.…”

Section: Figure 1: Cad Model Of Designed Test Sectionmentioning

confidence: 99%

Low Reynolds Number Effect on Highly Loaded Compressor Stator Cascade

Joseph,

Flaszynski,

Doerffer

et al. 2023

European Conference on Turbomachinery Fluid Dynamics and Thermodynamics

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The performance of a highly loaded compressor stator is limited by increased viscous losses caused by operating at a low Reynolds number (Re). The numerical investigation has been carried out on a linear stator cascade profile with an inlet Mach number of 0.9. A test section has been designed based on the extracted streamlines from cascade simulations to perform an experimental investigation of Shock Wave Boundary Layer Interaction (SBLI). Three-dimensional simulations have been carried out on the test section model using a steady state RANS with EARSM turbulence model including transition effects. The low Re number 2.3 × 10 5 case has been investigated on test section configuration and is compared with the high Re number 7.3×10 5 case while maintaining the same Mach inflow conditions. A detailed comparison of boundary layer and SBLI investigations have been performed to analyze the different Reynolds number effects on a representative test section configuration.

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Laminar-turbulent transition tripped by step on transonic compressor profile

Cited by 7 publications

References 2 publications

Wind tunnel investigations of aircraft airfoil in cruise conditions

Wind tunnel investigations of aircraft airfoil in cruise conditions

Transition Effect on the Flow Dynamics in a Compressor Blade Passage

Low Reynolds Number Effect on Highly Loaded Compressor Stator Cascade

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