Informacja

Drogi użytkowniku, aplikacja do prawidłowego działania wymaga obsługi JavaScript. Proszę włącz obsługę JavaScript w Twojej przeglądarce.

Wyszukujesz frazę "CFD" wg kryterium: Temat


Tytuł:
Jet and droplet breakup modelling approaches
Autorzy:
Kapusta, Ł. J.
Jaworski, P.
Kowalski, J.
Powiązania:
https://bibliotekanauki.pl/articles/245813.pdf
Data publikacji:
2015
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
spray
modelling
simulation
breakup
injection
CFD
computational fluid dynamics (CFD)
Opis:
Three-dimensional computational fluid dynamics (CFD) plays important role in engines development. The mixture formation in a direct-injection piston engines poses a huge challenge in successful simulations of the engine processes. It is due to the fact that the spray as a two-phase flow complicates the computational process. Moreover, this multiphase flow is not uniform. Three main zones, depending on the distance from the nozzle exit are visible when a liquid is injected. Very dense so called “thick” in a direct vicinity of the injector hole, than “thin” as a result of pri-mary breakup downstream the injector and finally in the certain distance from the injector appears “very thin” region as a result of secondary breakup. It is important to take into account that the liquid phase in various regimes behaves differently and is under influence of different phenomena. The modelling approach needs to take in to consideration all those elements. This paper focuses on presentation of the theory and numerical models for primary and secondary breakup phenomena. The primary breakup is a process that results from a combination of three mechanisms: turbu-lence within liquid phase, implosion of cavitation’s bubbles and aerodynamic forces acting on a liquid jet. Secondary breakup regime occurs mainly due to the aerodynamic interactions between the liquid and the gaseous phase.
Źródło:
Journal of KONES; 2015, 22, 3; 83-90
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Three - dimensional numerical simulations of the combustion chamber of the rotating detonation engine
Autorzy:
Folusiak, M.
Swiderski, K.
Kobiera, A.
Lukasik, B.
Wolanski, P.
Powiązania:
https://bibliotekanauki.pl/articles/245644.pdf
Data publikacji:
2013
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
rotating detonation engine (RDE)
RDE
computational fluid dynamics (CFD)
CFD
REFLOPS
Opis:
From 2010 Warsaw University of Technology (WUT) and Institute of Aviation (IoA) jointly implement the project under the Innovative Economy Operational Programme entitled ‘Turbine engine with detonation combustion chamber’. The goal of the project is to replace the combustion chamber of turboshaft engine GTD-350 with an annular detonation chamber. During the project, the numerical group that aims to develop computer code allowing researchers to simulate investigated processes has been established. Simulations provide wide range of parameters that are hardly available from experimental results and enable better understanding of investigated processes. Simulations may be also considered as a cheap alternative for experiments, especially when testing geometrical optimizations. In this paper the analysis of simulation results of the combustion chamber of the Rotating Detonation Engine (RDE) investigated at the IoA in Warsaw is presented. Primarily, REFLOPS USG which has become a fundamental numerical tool in the research of the RDE at the IoA is briefly described and governing equations and numerical methods used are shortly presented. Some aspects of numerical simulations of the RDE, related to selection of combustion mechanism, and an initiation of rotating detonation are provided. Secondly, results of simulations of inviscid gas with numerical injectors of hydrogen are compared with available experimental results. Three different wave patterns are identified in numerical solution and briefly described. Results of simulations are compared to experimental results in combustion chamber. Results presented in this paper are part of the project UDA-POIG.01.03.01-14-071 ‘Turbine engine with detonation combustion chamber’ supported by EU and Ministry of Regional Development, Poland.
Źródło:
Journal of KONES; 2013, 20, 1; 83-88
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
CFD modeling of thermal cycle of supercharged compression ignition engine
Autorzy:
Tutak, W.
Jamrozik, A.
Gruca, M.
Powiązania:
https://bibliotekanauki.pl/articles/247943.pdf
Data publikacji:
2012
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
combustion
modelling
CFD
diesel
injection
Opis:
Results of modelling of thermal cycle of turbocharged compression ignition IC engine are presented. The object of investigation was a 6CT107 turbocharged auto-ignition internal combustion engine powered by diesel oil, installed on an ANDORIA-MOT 100 kVA/ 80 kW power generating set in a portable version. The performed simulations of the combustion process have provided information on the spatial and time distributions of selected quantities within the combustion chamber of the test engine. The numerical analysis results have been juxtaposed with the results of indicating the engine on the test stand. Modelling of the thermal cycle of an auto-ignition piston engine in the AVL FIRE was carried out within the study. Advanced numerical submodels were used to analysis of combustion process, such as: Extended Coherent Flame Model (ECFM-3Z), turbulence model k-zeta-f, injection submodels with evaporation, collisions, coalescence and other. Intake and exhaust processes were included during modelling. This resulted in a lot of information about the intake, fuel mixing, ignition process and the exhaust process. Results of modelling were compared with results from real engine.
Źródło:
Journal of KONES; 2012, 19, 1; 465-472
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
CFD tests of the exhaust system of a sports motorcycle
Autorzy:
Tkaczyk, M.
Powiązania:
https://bibliotekanauki.pl/articles/247314.pdf
Data publikacji:
2018
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
CFD
speedway
spark ignition engine
Opis:
The content of this article describes the area of the operation of speedway racing motorcycles, it reflects the specific use, and thus, the special requirements placed on the internal combustion engines used there. Then, a research tool is presented in the form of Computational Fluid Dynamics methods. The article presents basic equations as a base for software, and emphasizes the essence and necessity of adequate selection of turbulence models. Presentation of the work tool is crowned with a brief description of the application in the form of Ansys numerical analysis software and a specific place and possibilities of its application. The practical part describes the work carried out during the tests of a GM 500 type combustion engine and attempts to compare two types of exhaust systems whose advantages and disadvantages in analytical calculations are difficult to determine, whereas CFD tests accurately represent pressure fields, velocities and the most important parameter in the form of resistance of the exhaust system. The article is crowned with the results of tests enabling determination and selection of the exhaust system with lower flow resistance and recommendations adjusting the exhaust system to a specific engine.
Źródło:
Journal of KONES; 2018, 25, 4; 429-436
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Field of pressure in zone contact elements assembly PRC stationary quantification
Autorzy:
Tkaczyk, M.
Kaźmierczak, A.
Kaźmierczak, Ł.
Górniak, A.
Powiązania:
https://bibliotekanauki.pl/articles/246221.pdf
Data publikacji:
2011
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
piston combustion engines
PRC systems
CFD
Opis:
One of the most common worldwide rubbing couple which performs plane-turning motion is a pair of selling rings - cylinder sleeve of a Piston - Ring- Cylinder (PRC) system of a combustion engine. It explains the necessity of performing investigations concerning the phenomenon occurring in rubbing couple PRC. One of the most important issues is the friction losses as well as losses of the working medium from the combustion chamber. Mathematical models of gas flow in the PRC are described in the literature differ in the way of description and scope of the phenomena taken into account. In this paper approach to determine the flow spaces between the rings considering the effect of the geometry of the PRC system has been proposed. Investigation conducted with aid of CFD (Computational Fluid Dynamics) were aimed on determination of flow resistance within the surface between the piston, rings, and cylinder liner. Aim of the study was achieved - The pressure field. it has been found that it is possible to determine the pressure field in the space of the PRC system basing on the approximation of the generalized transport equations for a discrete geometric model using the finite volume method. The precision of the results depends on the account in the form of boundary conditions as well as external conditions.
Źródło:
Journal of KONES; 2011, 18, 3; 463-471
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Flow simulation through wankel engine throttle using computational fluid dynamics
Autorzy:
Wendeker, M.
Grabowski, Ł.
Pietrykowski, K.
Magryta, P.
Powiązania:
https://bibliotekanauki.pl/articles/242019.pdf
Data publikacji:
2011
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
flow simulation
CFD
Wankel engine
throttle
Opis:
The paper focuses on the airflow through the throttle in the Wankel engine (Aixro XR50). The author's main challenge was to adapt a Wankel engine for hydrogen injection system, which required a very new full electronic throttle to be installed. Thus, an injector adapter and flow meter were mounted in this engine. The engine will be used as a stationary power unit to generate electricity for small households. Using hydrogen instead of hydrocarbon fuel will reduce the emission of green house gases. The simulation was in the AVL Fire using Computational Fluid Dynamic for 9 different throttle opening angles, i.e. ranging from 20 to 90 centigrade, i.e. 20, 30, 40, 50, 60, 70, 80 and 90 centigrade. The boundary conditions being as the pressure at the inlet and outlet of the throttle module correspond to the real values in the engine. The data on the properties of the flowing medium (air) were selected by default from the AVL Fire library. The authors use the k-zeta-ef model of turbulence to simulate flow through a Wankel engine throttle. The simulation results include the distributions of pressure, velocity and stream lines. The dependence of the mass flow rate as a function of the throttle position angle was presented. The turbulence disappears when the throttle opening angle of 60 centigrade is crossed. For full throttle the velocity at the pipe walls decreases to about 12 m/s. The highest velocity throughout the model occurs just where the throttle is mounted.
Źródło:
Journal of KONES; 2011, 18, 1; 677-682
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Experimental and numerical buoyancy analysis of tracked military vehicle
Autorzy:
Kotowski, M.
Barnat, W.
Grygorowicz, M.
Panowicz, R.
Dybcio, P.
Powiązania:
https://bibliotekanauki.pl/articles/242914.pdf
Data publikacji:
2012
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
buoyancy
military vehicle
amphibious vehicle
CFD
Opis:
The paper presents experimental validation of numerical flow analysis around tracked amphibious military vehicle. The aim of the study was to validate the simulation results and visualize the flow around optimized geometry To perform numerical simulations, a Computational Fluid Dynamics code FLUENT was used. The software is dedicated to model flow, turbulence, heat transfer, and reactions. The area was divided into two domains – air and water. During the simulation, water was moving with speed specified in standardization. However the numerical techniques are constantly developed and improved there is still a strong need for verification especially in buoyancy analysis and water performance evaluation. Results showed quite good agreement with literature after some modifications of the model. Then the flow was numerically visualized. That allowed in-depth analysis of the flow around each of vehicle's parts and some major and minor modifications were proposed. Modified geometry was analyzed and obtained results will be compared with previous ones. Additional stability and manoeuvrability tests were conducted. The results will be used to modify the geometry of vehicle and conduct experimental tests to verify the numerical code performance and check the actual change in vehicle's water performance. Future work will also consider propeller influence on results.
Źródło:
Journal of KONES; 2012, 19, 4; 321-324
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Propulsion configuration effect on performance of an inverted joined wing airplane
Autorzy:
Galiński, C.
Sieradzki, A.
Kalinowski, M.
Powiązania:
https://bibliotekanauki.pl/articles/244405.pdf
Data publikacji:
2016
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
inverted joined wing
propulsion
performance
CFD
Opis:
Efficiency is crucial for an airplane to reduce both costs of operations and emissions of pollutants. There are several airplane concepts that potentially allow for increasing the efficiency. A few of them were not investigated thoroughly enough yet. The inverted joined wing configuration, where the upper wing is positioned in the front of the lower one is an example of such a concept. Therefore, a project consisting of an aerodynamic analysis and optimisation, development of the software for multidisciplinary optimisation, development of an electric propulsion system, development of an experimental scaled demonstrator, wind tunnel testing and flight-testing was undertaken by consortium led by the Institute of Aviation, including also Warsaw University of Technology, Air Force Institute of Technology and small company MSP. Results of this project led to the conclusion that inverted joined wing configuration allows to build an airplane with the best performance in the world, but its advantage against conventional airplanes is marginal. One reason for this is large trimming drag of the configuration with relatively high position of the thrust vector. Therefore, other configurations of the propulsion were also considered to see if airplane performance could be further improved. This effort is described in the present paper.
Źródło:
Journal of KONES; 2016, 23, 3; 135-141
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Design-point, off-design meanline performance analysis and CFD computations of the axial turbine to micro gasturbine engine
Autorzy:
Bar, W.
Czarnecki, M.
Powiązania:
https://bibliotekanauki.pl/articles/245777.pdf
Data publikacji:
2009
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
turbine
gasturbine
axial turbine
micro
CFD
Opis:
Presented paper consists detailed analysis of the turbine to micro gasturbine. Calculatios was made for axial turbine with given mass flow rate m=0.15 [kg/s] and total inlet temperature T3*=950 [K]. The results of Design-Point, Off-Design Meanline Performance analysis and CFD computation are presented. The differences between typical size gasturbine turbines and turbines to micro-gasturbines are highlighted and some guidelines for designers of microgasturbines are given. As a major conclusions for designers of microgasturbines there is a considerations that require to be very carefull and forewarn that typical corelations for commercial gas turbines could't be take it as granted. In particular, compression ratio — solution possibility, micro gasturbine rotor speed,turbine expansion ratio Pi T as a function of compressor and turbine efficiency, efficiency of turbine as a function of reynolds number for constant specific speed coefficient and constant specific diameter coefficient,turbine to micro gasturbine performance map for different normalized rotational speed, 2D and 3D contour plots of entropy, relative Mach number at middle cut of the blade, static pressure at middle cut of the blade are presented in the paper.
Źródło:
Journal of KONES; 2009, 16, 4; 9-16
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Numerical simulation of heat loaded aircraft engine turbine blade - internal cooling
Autorzy:
Świątek, M.
Domański, R.
Powiązania:
https://bibliotekanauki.pl/articles/242988.pdf
Data publikacji:
2012
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
CFD
internal cooling systems
thermal protection
Opis:
The objective of this thesis was to show present the impact of the turbine blade cooling on blade material temperatures well as familiarize with processes and methods of numerical simulation by designing airfoil internal cooling system. The model of airfoil was created based on drawing print nr 17.41.0114 of engine Tumański R-11F2S-300. Geometry of all models described above is created using SIMENS NX4 program based on drawings obtained from available literature, and data acquired from the Internet. The discretization into a structural finite volume grid took place in commercial pre-processor GAMBIT registered trademark (GAMBIT and FLUENT – commercial CFD codes from Ansys Inc.). Conjugated heat transfer analysis was conducted in program FLUENTregistered trademark for four different cases, where the blade material properties were changed. The goal of this thesis was to obtain temperature fields and distribution in the turbine blade airfoil and to evaluate if applied cooling would be able to cool down this thermally loaded part. Calculated results show that proposed blade heat protection method is insufficient during steady state condition, mainly on the blade leading and trailing edge. In these two locations, the blade is overheated, and the high temperature level of applied material is unacceptable for used in jet engine turbine industry.
Źródło:
Journal of KONES; 2012, 19, 4; 601-606
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Investigation of the side wind effects on the passenger ferry in rolling motion conditions
Autorzy:
Jurczak, W.
Kaup, M.
Kaup, J.
Powiązania:
https://bibliotekanauki.pl/articles/243352.pdf
Data publikacji:
2016
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
wind forces
passenger ferry
CFD analysis
Opis:
The article presents the investigation results of selected effects of the side wind on the passenger ferry in sea condition. The computational fluid dynamic (CFD) analysis has been carried out in order to calculate the forces and moments acting on the ship superstructure during rolling caused by waves. The performed analysis shows the impact of rolling amplitudes and periods on results. The use of CFD method allows calculating the vertical centre of pressure with various rolling parameters. Numerical analysis has been performed for real size ship model in transient condition. The main object of the research is to define the influence of the wind dumping effect on wave rolling motions. Additional wind dumping effect (besides of other effects) is intending to use in response amplitude operator (RAO) calculations (next part of researches). It is possible that use of additional wind dumping effect will reduce the rolling amplitudes, and consequently reduce ship accelerations due to rolling motions. Reduction of accelerations (especially horizontal), should decrease the requirements due to number of cargo lashes/belts equipment and minimize the lashing time. From other side it should shorten required harbour time and reduce the ship speed, what is the best way to save the fuel.
Źródło:
Journal of KONES; 2016, 23, 3; 241-248
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Influence of geometry and type of cooling holes on thermal load of combustion chamber
Autorzy:
Swiatek, M.
Domański, R.
Powiązania:
https://bibliotekanauki.pl/articles/246265.pdf
Data publikacji:
2010
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
aircraft engines
engine combustion chamber
combustor cooling
CFD
Opis:
The objective of this thesis is to compare various methods of combustor wall cooling and their effectiveness by numerical simulations. It was determined that the first task was to verify how much air is coming through single axial hole with 3.5% pressure drop between hot and cold part of combustion chamber. The results from this flow check serve as a base template for generating more accurate and precise models of single axial hole cooling as well as calculation of hole diameter for multihole cooling. Second task was to generate more sophisticated single hole model with boundary layer in order to better simulate the conditions in areas near the combustion chamber walls and get more accurate results. The same method was used to create multihole model. In order to compare efficiency, all created domains in every model have the same volume, model settings, operating and boundary conditions. Geometry of all models described above is created using SIMENS NX4 and SIMENS NX5 program based on drawings obtained from available literature, and data acquired from the Internet. The discretization into a structural finite volume grid took place in commercial pre-processor GAMBITŽ (GAMBIT and FLUENT - commercial CFD codes from Ansy s Inc). The airflow andheat exchange will be calculated using program FLUENTŽ. The results were shown in the thesis in terms of several comparative pictures of the temperature fields in the combustion chamber domain, and graphs representing difference in temperature fields on cooling wall of the combustion chamber.
Źródło:
Journal of KONES; 2010, 17, 4; 485-494
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Combustor liner cooling methods - numerical simulation
Autorzy:
Lazarczyk, M.
Domański, R.
Powiązania:
https://bibliotekanauki.pl/articles/247755.pdf
Data publikacji:
2010
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
aircraft engines
engine combustion chamber
combustor cooling
CFD
Opis:
The objective of this thesis is to compare various methods of combustor wall cooling and to evaluate advantages and disadvantages of each applied cooling methods. It was determined that the flrst task was to verify how much air is coming through singe radial hole with 2.5% pressure drop between hot and cold part ofcombustion chamber. Flowcheck was calculated also to see how geometry of cooling hole affects hole effective area. Second task was to generale 3d model and mesh of both calculated types of cooling. Each model mesh was covered with boundary layer in order to better simulate conditions near the combustion chamber walls and obtain accurate results. In order to run back-to-back analysis, all created models have the same number of mesh elements, same materials used, samefluent settings, same operating and boundary conditions. Geometry of all models described above was created using Unigraphics NX4 program based on drawings obtained from available literature, and data acquired from the Internet. The discretization was done in commercial pre-processor GAMBITŽ. The airflow and conjugated heat transfer analysis was calculated in program FLUENTŽ. The goal of this thesis was to obtain temperature fields and distribution in the combustion chamber domain (lip and panel wall) and to evaluate if applied cooling is sufficient to cool down heat loaded part of the combustor chamber.
Źródło:
Journal of KONES; 2010, 17, 4; 277-286
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Method for modelling temperature distribution in exhaust system of diesel engine in the light of mine systems of heat recuperation
Autorzy:
Chuchnowski, W.
Tokarczyk, J.
Stankiewicz, K.
Woszczyński, M.
Powiązania:
https://bibliotekanauki.pl/articles/242169.pdf
Data publikacji:
2011
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
recuperation
diesel engine
Peltier's cell
temperature distribution
CFD
Opis:
Analysis of temperature distribution and heat flow in the exhaust system of diesel engine to determine technical parameters of the system for heat recuperation and changing of thermal energy into electric energy was presented. Temperature of exhaust gases as well as geometrical and material features of exhaust system were the input data accepted for modelling. Computational Fluid Dynamics (CFD) was used to determine temperature distribution in the exhaust system. The software by use numerical methods finite volume method) enables solving partial differential equations consisting of equations of: continuity, Navier-Stokes, Fourier-Kirchoff and complemented with other equations important as regards the discussed phenomenon (e.g. with turbulences models)transforming them in the algebraic equations or common differential equations. CFD software enables gaining some information as regards flow rate, distribution of speed field, and pressure field as well as heat flow, temperature field and mass field. Design and principle of operation of Peltier 's cell, model of recuperator, exhaust system, and diesel engine, finite elements meshing, boundary conditions assumed in analysis of exhaust gases and water flow, distribution of temperature field (maximal temperature of scale 335 K and maximal temperature of scale 400 K) on external wall of exhaust system and cross-section of exhaust system are presented in the paper.
Źródło:
Journal of KONES; 2011, 18, 2; 101-108
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Aeroelastic analysis of helicopter rotor using virtual blade model and equivalent beam model of a blade
Autorzy:
Sieradzki, A.
Powiązania:
https://bibliotekanauki.pl/articles/242703.pdf
Data publikacji:
2016
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
rotorcraft
helicopter
blade
aeroelasticity
rotor
aerodynamics
CFD
VBM
Opis:
Modern helicopter rotor blades design requires taking into account complex aeroelastic phenomena. Sophisticated computational fluid dynamics and structural dynamics models, available on the market, coupled together enable such analysis with very high fidelity. However, the computational cost of this type of simulation is usually very high and for this reason, it cannot be used in interactive design process or optimization run. Complex Fluid Structure Interaction models are excellent tools for validation purposes, but the design process requires simpler models with lower computational cost and still relatively high accuracy and capabilities. The paper presents a new efficient methodology for calculating helicopter rotor loads, deformations and performance. It uses the well-known Navier-Stokes equations aerodynamic solver – ANSYS Fluent, and modified Virtual Blade Model (based on Blade Element Theory) for rotor flow calculation. This connection guarantees exceptional capabilities and fidelity in comparison with simulation time. The dedicated structural dynamics solver, based on equivalent beam model of a blade and Finite Difference Method, was developed and coupled with CFD part using User Defined Functions in Fluent software. The accuracy of created module was validated with wind tunnel tests data of IS-2 helicopter rotor model, performed in Institute of Aviation. The results of calculations were compared with experimental data for a hover state and a forward flight with three different flight velocities. The comparisons showed very good agreement of the data in most of the analysed cases and pointed out new research possibilities. The presented aeroelastic helicopter rotor model combines all advantages of using three-dimensional Navier-Stokes solver with relatively low computational costs and high accuracy, confirmed by wind tunnel tests. It could be used successfully in helicopter rotor blades design process.
Źródło:
Journal of KONES; 2016, 23, 1; 297-304
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
Dostawca treści:
Biblioteka Nauki
Artykuł

Ta witryna wykorzystuje pliki cookies do przechowywania informacji na Twoim komputerze. Pliki cookies stosujemy w celu świadczenia usług na najwyższym poziomie, w tym w sposób dostosowany do indywidualnych potrzeb. Korzystanie z witryny bez zmiany ustawień dotyczących cookies oznacza, że będą one zamieszczane w Twoim komputerze. W każdym momencie możesz dokonać zmiany ustawień dotyczących cookies