Wienczyslaw Stalewski | Institute of Aviation, Warsaw (original) (raw)

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Papers by Wienczyslaw Stalewski

Journal of KONES, 2017

Simulations of ice accretion on airfoil in icing conditions were conducted using ice accretion mo... more Simulations of ice accretion on airfoil in icing conditions were conducted using ice accretion model implemented by authors in ANSYS FLUENT CFD solver. The computational model includes several sub-models intended for simulations of two-phase flow, determination of zones of water droplets impinging on the investigated surface, flow of water in a thin film on airfoil surface and heat balance in air-water-ice contact zone. The method operates in an iterative loop, which enables determination of effects of gradual deformation of aircraft surface on airflow over the surface, which has impact on distribution of collected water, flow of water film over the surface and local freezing rates. The implementation of the method in CFD solver made it necessary to complement the mathematical model of determination of local rates of deformation of aircraft surface with modification of computational mesh around the surface, which must conform, to the deformed surface. Results of simulated ice accret...

Study of transition location effect (from natural transition to fully turbulent) on separation si... more Study of transition location effect (from natural transition to fully turbulent) on separation size, shock structure and unsteadiness was the focus of this WP. Boundary layer tripping (by wire or roughness) and flow control devices (VG) were used for boundary layer transition induction. Although this type of flow field had been studied widely in the past, there remains considerable uncertainty on the effects of transition on transonic aerofoil performance. In particular it is not known how close to the shock location transition has to occur to avoid detrimental effects associated with laminar shock-induced separation. Furthermore, it was unclear how best to provoke transition on an airfoil featuring significant laminar flow and how close to the shock this needs to be performed. Finally, current CFD methods are particularly challenged by such transitional flows. In this work package some of the findings from the basic research performed in other WPs was applied. Specialized large-sca...

Journal of KONES, 2017

A modern main rotor, dedicated to the ultralight helicopter, has been designed and optimised. Due... more A modern main rotor, dedicated to the ultralight helicopter, has been designed and optimised. Due to assumed simplicity of the rotor design and taking into account some technological constraints, the principal purpose of the presented research was to design a dedicated airfoil which, when applied on the main-rotor blades, would influence satisfactory improvement in a performance of the ultralight helicopter, especially in fast flight. The design and optimisation process has been supported by a computational methodology. The in-house software has been used for direct and inverse design of shapes of the rotor-blade airfoils. Aerodynamic properties of the airfoils as well as the helicopter main rotor were evaluated based on both the two-dimensional and three-dimensional flow simulations conducted using the ANSYS FLUENT software that was used to solve U/RANS equations. Based on the results of conducted computational simulations of fast flight of the ultralight helicopter, it can be conc...

Journal of KONES, 2017

The article presents a computational analysis of the effect of the turboprop engine slipstream on... more The article presents a computational analysis of the effect of the turboprop engine slipstream on generation of aerodynamic forces induced vibrations of aircraft tail assembly (empennage). Working propellers exhaust system, engine nacelle, and wing-engine nacelle flow interference phenomenon can cause strong non-stationary disturbances behind the wing of the aircraft. These disturbances, propagating in the direction of the aircraft tail assembly, may be an important factor influencing the operation of the airplane flow control system and the source of aerodynamic forces generating vibrations of the entire plane structure. The article presents an example of analysis of this phenomenon for a light passenger-transport aircraft using advanced numerical models for simulation of the flow around the aircraft. In the computational model, Navier-Stokes flow equations were solved by finite volume method with the K-Omega SST turbulence model to calculate the turbulent kinetic energy distributi...

The influence of simulated main rotor on aerodynamic properties of four different heli copter fus... more The influence of simulated main rotor on aerodynamic properties of four different heli copter fuselage configurations has been tested. The research was done using computational fluid dynamics (CFD) method. Simulations were done for hover and forward flight conditions. The results for computation without and with main rotor modelling were compared. Changes of aerodynamic properties with respect to basic configuration were analysed.

Transactions of the Institute of Aviation, 2016

Journal of KONES. Powertrain and Transport, 2014

The paper presents results of the first stage of the research conducted within the frames of Acti... more The paper presents results of the first stage of the research conducted within the frames of Active Rotor Technologies, which is the dynamically developed sub-domain of Rotorcraft Engineering. The research concerned a computational modelling and investigations of new solutions aiming at improvement of performance of modern helicopters and their environmental impact, by active control of operation of their rotors. The paper focuses on one of such solutions applied for the active control of airflow around helicopter-rotor blades. This solution is the Active Gurney Flap-a small, flat tab located at a pressure side of rotor blade near its trailing edge, which is cyclically deployed and stowed during rotation cycles of the blade. The Active Gurney Flap seems to be very promising solution which will enable helicopters to operate with reduced power consumption or reduced main rotor tip speed whilst preserving current flight performance capabilities, especially in terms of retreating blade stall. The newly developed methodology of computational modelling of active-flow-control devices, like Active Gurney Flap, applied for enhance a helicopter performance and improve its environmental impact, has been presented. Development of the methodology was the challenging task, taking into account strongly unsteady character of modelled phenomena and large differences of scales in both the space and time domain, where very small, dynamically deflected tab strongly influences the flow around rotating, large main rotor. Exemplary CFD simulations, presented in the paper, have been conducted to validate developed methodology.

The concept of Smart Micro Vanes (SMV) has been developed and investigated through computational ... more The concept of Smart Micro Vanes (SMV) has been developed and investigated through computational simulations. The concept may significantly extend the applicability of natural-laminar-flow-and-high-aspect-ratio wing for modern, low-cost transport aircraft. The proposed device is an array of deployable micro-vanes (turbulators) located at a front part of the suction side of the wing. In nominal, cruise flight conditions the SMV are hidden in order not to trip the laminar boundary layer. In transonic flow, in extraordinary conditions of sudden gust the SMV are deployed to force laminar-turbulent transition of boundary layer on the suction side of the wing. This causes sudden drop of lift force acting on the wing and significant reduction of a danger of buffet onset. Both these phenomena are beneficial and desirable in the context of active control of aerodynamic loads acting on the wing structure. The paper presents results of computational simulations of transonic flight of simplified model of natural-laminar-flow wing in conditions of sudden-gust appearance. The simulations have been conducted for the case of clean model wing as well as for the same wing equipped with Smart Micro Vanes, deployed automatically (simulation of simple closeloop control) to protect the wing structure against excessive aerodynamic loads.

Archives of Mechanics

Design process of a turbulent wing for small aircraft, using multidisciplinary and multi-objectiv... more Design process of a turbulent wing for small aircraft, using multidisciplinary and multi-objective optimisation, based on a genetic algorithm was presented. A generic parametric model of small aircraft wing geometry was developed. In the model, a wide class of wing geometries, with and without high lift devices, was described by a relatively small number of parameters. The optimisation method used the objectives and constraints typical for multidisciplinary wing design, and was applied to the design and optimisation of turbulent wing dedicated for small, two-propeller aircraft. The research was conducted within European Project CESAR. The results of the research have been discussed.

An innovative solution dedicated for an effective control of strong separation of air flow has be... more An innovative solution dedicated for an effective control of strong separation of air flow has been proposed. The solution is based on a system of coupled pairs of nozzles located on the surface, where the strong flow separation is forecasted. When such phenomenon appears, in each pair of coupled nozzles a flow is activated, in such a way, that one of the nozzles starts blowing, while the other starts sucking the air from the main flow region. A matrix of such fluidic devices is able to significantly alleviate and even completely eliminate the strong separation of the flow on a given surface. The discussed solution has been investigated and partially optimized based on a computational-simulation approach. Additionally, an innovative idea of a fluidic actuator, feeding the nozzles with both the overpressure and underpressure has been presented.

The article presents an analysis of the wing-engine nacelle flow interference phenomenon on the e... more The article presents an analysis of the wing-engine nacelle flow interference phenomenon on the example of a light twin-engine commuter aircraft. The problems of propulsion system integration with the wing in airplanes are now frequently the subject of advanced optimization research performed by aircraft manufacturers. The shape of the engine nacelle and its connection with the wing determines the quality of the flow around the wing in that area. This is important for high-lift devices placed at the wing trailing edge behind engine nacelle used during the take-off and landing process. Additionally the flow is effected by the disturbances generated by working propellers, the presence of air inlets and an exhaust system of the engine. The article presents a process of numerical optimization of an engine nacelle rear part shape. The main goal of the process was to eliminate the flow disturbances caused by the engine nacelle-wing interference phenomenon. During analysis, the Adjoint Sol...

Studies on shockwave-boundary-layer interaction have been conducted, aimed at evaluation of possi... more Studies on shockwave-boundary-layer interaction have been conducted, aimed at evaluation of possibilities of successful application of Natural-Laminar-Flow technology in a design of transonic wing. To alleviate unfavourable effects of interaction between laminar boundary layer and a shockwave, the laminar-turbulent transition, forced by the system of micro-vanes located ahead of the shockwave has been proposed and investigated through CFD simulations.

2018 Flow Control Conference

Journal of KONES, 2017

Simulations of ice accretion on airfoil in icing conditions were conducted using ice accretion mo... more Simulations of ice accretion on airfoil in icing conditions were conducted using ice accretion model implemented by authors in ANSYS FLUENT CFD solver. The computational model includes several sub-models intended for simulations of two-phase flow, determination of zones of water droplets impinging on the investigated surface, flow of water in a thin film on airfoil surface and heat balance in air-water-ice contact zone. The method operates in an iterative loop, which enables determination of effects of gradual deformation of aircraft surface on airflow over the surface, which has impact on distribution of collected water, flow of water film over the surface and local freezing rates. The implementation of the method in CFD solver made it necessary to complement the mathematical model of determination of local rates of deformation of aircraft surface with modification of computational mesh around the surface, which must conform, to the deformed surface. Results of simulated ice accret...

Study of transition location effect (from natural transition to fully turbulent) on separation si... more Study of transition location effect (from natural transition to fully turbulent) on separation size, shock structure and unsteadiness was the focus of this WP. Boundary layer tripping (by wire or roughness) and flow control devices (VG) were used for boundary layer transition induction. Although this type of flow field had been studied widely in the past, there remains considerable uncertainty on the effects of transition on transonic aerofoil performance. In particular it is not known how close to the shock location transition has to occur to avoid detrimental effects associated with laminar shock-induced separation. Furthermore, it was unclear how best to provoke transition on an airfoil featuring significant laminar flow and how close to the shock this needs to be performed. Finally, current CFD methods are particularly challenged by such transitional flows. In this work package some of the findings from the basic research performed in other WPs was applied. Specialized large-sca...

Journal of KONES, 2017

A modern main rotor, dedicated to the ultralight helicopter, has been designed and optimised. Due... more A modern main rotor, dedicated to the ultralight helicopter, has been designed and optimised. Due to assumed simplicity of the rotor design and taking into account some technological constraints, the principal purpose of the presented research was to design a dedicated airfoil which, when applied on the main-rotor blades, would influence satisfactory improvement in a performance of the ultralight helicopter, especially in fast flight. The design and optimisation process has been supported by a computational methodology. The in-house software has been used for direct and inverse design of shapes of the rotor-blade airfoils. Aerodynamic properties of the airfoils as well as the helicopter main rotor were evaluated based on both the two-dimensional and three-dimensional flow simulations conducted using the ANSYS FLUENT software that was used to solve U/RANS equations. Based on the results of conducted computational simulations of fast flight of the ultralight helicopter, it can be conc...

Journal of KONES, 2017

The article presents a computational analysis of the effect of the turboprop engine slipstream on... more The article presents a computational analysis of the effect of the turboprop engine slipstream on generation of aerodynamic forces induced vibrations of aircraft tail assembly (empennage). Working propellers exhaust system, engine nacelle, and wing-engine nacelle flow interference phenomenon can cause strong non-stationary disturbances behind the wing of the aircraft. These disturbances, propagating in the direction of the aircraft tail assembly, may be an important factor influencing the operation of the airplane flow control system and the source of aerodynamic forces generating vibrations of the entire plane structure. The article presents an example of analysis of this phenomenon for a light passenger-transport aircraft using advanced numerical models for simulation of the flow around the aircraft. In the computational model, Navier-Stokes flow equations were solved by finite volume method with the K-Omega SST turbulence model to calculate the turbulent kinetic energy distributi...

The influence of simulated main rotor on aerodynamic properties of four different heli copter fus... more The influence of simulated main rotor on aerodynamic properties of four different heli copter fuselage configurations has been tested. The research was done using computational fluid dynamics (CFD) method. Simulations were done for hover and forward flight conditions. The results for computation without and with main rotor modelling were compared. Changes of aerodynamic properties with respect to basic configuration were analysed.

Transactions of the Institute of Aviation, 2016

Journal of KONES. Powertrain and Transport, 2014

The paper presents results of the first stage of the research conducted within the frames of Acti... more The paper presents results of the first stage of the research conducted within the frames of Active Rotor Technologies, which is the dynamically developed sub-domain of Rotorcraft Engineering. The research concerned a computational modelling and investigations of new solutions aiming at improvement of performance of modern helicopters and their environmental impact, by active control of operation of their rotors. The paper focuses on one of such solutions applied for the active control of airflow around helicopter-rotor blades. This solution is the Active Gurney Flap-a small, flat tab located at a pressure side of rotor blade near its trailing edge, which is cyclically deployed and stowed during rotation cycles of the blade. The Active Gurney Flap seems to be very promising solution which will enable helicopters to operate with reduced power consumption or reduced main rotor tip speed whilst preserving current flight performance capabilities, especially in terms of retreating blade stall. The newly developed methodology of computational modelling of active-flow-control devices, like Active Gurney Flap, applied for enhance a helicopter performance and improve its environmental impact, has been presented. Development of the methodology was the challenging task, taking into account strongly unsteady character of modelled phenomena and large differences of scales in both the space and time domain, where very small, dynamically deflected tab strongly influences the flow around rotating, large main rotor. Exemplary CFD simulations, presented in the paper, have been conducted to validate developed methodology.

The concept of Smart Micro Vanes (SMV) has been developed and investigated through computational ... more The concept of Smart Micro Vanes (SMV) has been developed and investigated through computational simulations. The concept may significantly extend the applicability of natural-laminar-flow-and-high-aspect-ratio wing for modern, low-cost transport aircraft. The proposed device is an array of deployable micro-vanes (turbulators) located at a front part of the suction side of the wing. In nominal, cruise flight conditions the SMV are hidden in order not to trip the laminar boundary layer. In transonic flow, in extraordinary conditions of sudden gust the SMV are deployed to force laminar-turbulent transition of boundary layer on the suction side of the wing. This causes sudden drop of lift force acting on the wing and significant reduction of a danger of buffet onset. Both these phenomena are beneficial and desirable in the context of active control of aerodynamic loads acting on the wing structure. The paper presents results of computational simulations of transonic flight of simplified model of natural-laminar-flow wing in conditions of sudden-gust appearance. The simulations have been conducted for the case of clean model wing as well as for the same wing equipped with Smart Micro Vanes, deployed automatically (simulation of simple closeloop control) to protect the wing structure against excessive aerodynamic loads.

Archives of Mechanics

Design process of a turbulent wing for small aircraft, using multidisciplinary and multi-objectiv... more Design process of a turbulent wing for small aircraft, using multidisciplinary and multi-objective optimisation, based on a genetic algorithm was presented. A generic parametric model of small aircraft wing geometry was developed. In the model, a wide class of wing geometries, with and without high lift devices, was described by a relatively small number of parameters. The optimisation method used the objectives and constraints typical for multidisciplinary wing design, and was applied to the design and optimisation of turbulent wing dedicated for small, two-propeller aircraft. The research was conducted within European Project CESAR. The results of the research have been discussed.

An innovative solution dedicated for an effective control of strong separation of air flow has be... more An innovative solution dedicated for an effective control of strong separation of air flow has been proposed. The solution is based on a system of coupled pairs of nozzles located on the surface, where the strong flow separation is forecasted. When such phenomenon appears, in each pair of coupled nozzles a flow is activated, in such a way, that one of the nozzles starts blowing, while the other starts sucking the air from the main flow region. A matrix of such fluidic devices is able to significantly alleviate and even completely eliminate the strong separation of the flow on a given surface. The discussed solution has been investigated and partially optimized based on a computational-simulation approach. Additionally, an innovative idea of a fluidic actuator, feeding the nozzles with both the overpressure and underpressure has been presented.

The article presents an analysis of the wing-engine nacelle flow interference phenomenon on the e... more The article presents an analysis of the wing-engine nacelle flow interference phenomenon on the example of a light twin-engine commuter aircraft. The problems of propulsion system integration with the wing in airplanes are now frequently the subject of advanced optimization research performed by aircraft manufacturers. The shape of the engine nacelle and its connection with the wing determines the quality of the flow around the wing in that area. This is important for high-lift devices placed at the wing trailing edge behind engine nacelle used during the take-off and landing process. Additionally the flow is effected by the disturbances generated by working propellers, the presence of air inlets and an exhaust system of the engine. The article presents a process of numerical optimization of an engine nacelle rear part shape. The main goal of the process was to eliminate the flow disturbances caused by the engine nacelle-wing interference phenomenon. During analysis, the Adjoint Sol...

Studies on shockwave-boundary-layer interaction have been conducted, aimed at evaluation of possi... more Studies on shockwave-boundary-layer interaction have been conducted, aimed at evaluation of possibilities of successful application of Natural-Laminar-Flow technology in a design of transonic wing. To alleviate unfavourable effects of interaction between laminar boundary layer and a shockwave, the laminar-turbulent transition, forced by the system of micro-vanes located ahead of the shockwave has been proposed and investigated through CFD simulations.

2018 Flow Control Conference