Temat: aircraft transport - Katalog OPAC zbiorów

Skocz do pozycji: 1.

Tytuł:: The use of light aircraft in domestic transport in Poland
Autorzy:: Kołodziejczyk, R.
Powiązania:: https://bibliotekanauki.pl/articles/241893.pdf
Data publikacji:: 2014
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: transport
small aircraft transport
domestic air transport
routes analysis
passengers flow
Opis:: The work concerns the analysis of the possibilities of using light aircraft in the regional passenger transport. This analysis was based on the existing airport infrastructure in Poland. Between 43 existing airports with paved runways and length more than 1,000 meters potential routes of aircraft traffic were set. The study compared the light aircraft transport to the car transport. One of the benchmark criteria was the travel time between different destinations, using both means of transport. The second criterion is the financial aspects of travel. For this purpose, a statistics of light aircraft and calculated their Direct Operating Cost as a function of various parameters such as maximum weight, the number of passenger seats, cruise speed were created. Analysis also included air navigation charges on the routes and the operator profit. The calculations allowed identifying potential routes where the plane would be competitive with the car in terms of travel time and costs by one person. The number of these routes was dependent on the speed of travel, the number of seats on the plane as well as the fill factor of these seats. The analysis also applies to determine the number of passengers traveling between the regions. In 2013, domestic air transport handled less than 2.5 million passengers, which in comparison to the countries of Western Europe is a poor result. This is caused mainly by a small amount of domestic routes as well as a small number of regional airports. The implementation of the concept of using light aircraft in regional connections aims to increase the speed of travel, increase the safety in passenger transport, cost reduction and partial replacement of road transport by air transport.
Źródło:: Journal of KONES; 2014, 21, 4; 239-246
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 2.

Tytuł:: Engineering availability of aircrafts
Autorzy:: Lewitowicz, J.
Powiązania:: https://bibliotekanauki.pl/articles/242226.pdf
Data publikacji:: 2009
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: transport
aircraft
diagnostic
failure
Opis:: Engineering availability and operational readiness of an aircraft are requisites for its ability to operate. After the aircraft has been supplied, both features determine airworthiness of the aircraft, in compliance with the ARC (Airworthiness Review Certificate). Improvement in methods of maintaining the aircraft availability proceeds in compliance with the MSG (Maintenance Steering Group) rules. The paper has been intended to outline the process of maintaining the engineering availability of the aircraft, with account taken of: aircraft maintainability, importance of the engineering diagnostics, and evaluation ratesfor dijferent maintenance patterns. Maintaining technical ability/ airworthiness of an aircraft, ground service of aircrafts, service-friendliness of an aircraft, unfitness and damages to an aircraft, ground diagnostic andprovision equipment for A-380, computer aided verification of an inspection of a front undercarriage (B) of an aircraft (A) and service of the B-787 aircraft (C), percentage for composite material portion in the structure of some aircrafts and helicopters, positions of composite material airframe elements in B-75 7/7 67, B-777, B-787 are presented in the paper.
Źródło:: Journal of KONES; 2009, 16, 2; 255-262
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 3.

Tytuł:: Modification of aerodynamic wing loads by fluidic devices
Autorzy:: Stalewski, W.
Sznajder, J.
Powiązania:: https://bibliotekanauki.pl/articles/243884.pdf
Data publikacji:: 2014
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: transport
aircraft engineering
mechanical engineering
Opis:: Airplane wing load control systems are designed for modification/redistribution of aerodynamic loads in order to decrease risk of structural damage in conditions of excessive loads, to improve passenger comfort in turbulent atmosphere or to act as flight control systems. Classical examples include systems involving symmetric deflections of ailerons reducing wing root bending moments (Lockheed C-5 Galaxy) or deflections of spoilers stabilizing landing approach path (Lockheed TriStar). The fast development of Micro Electromechanical Systems and their application in Flow Control System opens the perspectives of designing practical wing load control systems based on fluidic actuators, modifying local aerodynamic loads by inducing changes to flow, for example, by inducing flow separation in the boundary layer or modifying Kutta condition on the trailing edge. This is the principle of operation of novel concepts of flow control actuators proposed by Institute of Aviation and discussed in the paper. The systems include actuators in the central part of the wing section, reducing local lift similarly to classical spoilers and actuators on the modified trailing edge, acting similarly to ailerons. The potential advantages in comparison to classical devices include potentially shorter reaction time because of avoiding the necessity of moving large surfaces against high dynamic pressure, which is important in conditions of fast-changing loads in turbulent atmosphere.
Źródło:: Journal of KONES; 2014, 21, 3; 271-278
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 4.

Tytuł:: Field repairs of aircraft engines
Autorzy:: Cwojdziński, L.
Lewitowicz, J.
Powiązania:: https://bibliotekanauki.pl/articles/241779.pdf
Data publikacji:: 2012
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: transport
aviation
aircraft
field repairs
optimization
Opis:: The challenge to the manufacturer or service provider is how to assess and define true customer expectations and then how to design, manufacture and sell the product to best meet those expectations. Each product must provide operational capabilities, which allow military forces to maintain technical and logistic superiority over a potential adversary even if it is just natural or induced environment, which can be expected over the operating and maintenance portion of life cycle. Battle damage repair is a critical factor in managing operation. We acknowledge that traditional cost minimizing measures are not always central and other performance measures such as time of repair, reliability and availability become more relevant. Assessing aircraft damages in the field and making appropriate decisions on the reparability, making repairs at the lowest repair level possible and evaluating airworthiness of subsequent repairs is critical to the air forces maintaining its force projection capability. Among other, combat damage of helicopters, damaged areas and erosion on leading edges of the compressor first stage rotor blades, achievable and optimum solution, goal function – duration minimisation, goal function – cost minimisation are presented in the paper.
Źródło:: Journal of KONES; 2012, 19, 4; 131-138
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 5.

Tytuł:: Research method of dynamic capability of an actuating block of the SSP-FK aircraft fire suppression system in false alarm aspect
Autorzy:: Szelmanowski, A.
Zieja, M.
Głyda, K.
Tokarski, T.
Powiązania:: https://bibliotekanauki.pl/articles/244205.pdf
Data publikacji:: 2016
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: transport
aircraft fire suppression systems
research
simulation methods
aircraft fire protection
Opis:: Numerous cases of self-activation of the SSP-FK aircraft fire suppression system (including commissioning of valves and extinguishing tanks) testify about the fact that it is not yet fully understood in the technical aspect, and because of the performed role on the aircraft is the basic element to ensure flight safety. Solving problems with false fire signalling of the SSP-FK system is an important issue for the safe operation of aircraft and military helicopters, because it is preventive (to warn the crew of the possibility of fire) and rescue system (aiming at extinguish the fire) in each phase of a flight. In addition, the SSP-FK system is used on many types of military aircraft (including helicopters from W-3/3W/3WA/3PL and Mi/8/14/17/24 family as well as An-28 and Tu-154M aircraft. The paper presents selected results of work in the Air Force Institute of Technology in the study of SSP-FK fire suppression system (as one of the main protection systems on-board) used on many types of military aircraft operated in the Polish Armed Forces. In determining the conditions of the false signalling of fire, simulation models of action blocks implementing of the SSP-FK fire suppression system were developed. The research on simulation models was performed in Matlab-Simulink and Circuit-Maker computing packages. The results of these works were used to diagnose selected modules and blocks of the SSP-FK system during the study of actual cases of their false activation.
Źródło:: Journal of KONES; 2016, 23, 3; 525-531
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 6.

Tytuł:: Development of the aircraft power plants - challenges
Autorzy:: Szczeciński, S.
Powiązania:: https://bibliotekanauki.pl/articles/242001.pdf
Data publikacji:: 2008
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: transport
combustion engines
internal combustion aircraft engine
Opis:: On the background of a current level of the aircraft power plants modernities presented here is the trial settlement of the possible directions of their further development - resultant from the current and future economic, military, sports needs. The general direction of development of all types of aeronautical propulsion systems, and also of these produced a long time ago and exploited for many years, is their permanent " upgrade" in the new equipment and of methodic of the current technical state checking for the purpose of the indispensable flights safety assurance, the prolongation of the failure-free exploitation time - but also the maintenance of the economic concurrency requirements. Recently, a categorical form receives the requirement of the noise limitation of aviation power plants and the limitation for emission of toxic elements in exhaust. In the piston engines, the direction of developments are aimed on the design of compression ignition engines, fuelled with standardized aircraft jet fuel. Their additional valour is their smaller fuel expenditure, about 30% less with respect to their spark ignition equivalents. Particularly important is the task of decrease the quantities of fuel used up, the limitation of number of produced engines through raising their efficiency and durability, limitation of noisiness of engines alone and driven: propellers, ventilators and the lifting rotors of helicopters, the limitation of thrust, required to the flight of the airplanes and the helicopters. One turned attention on ecological requirements, which force the application of mineral fuels completed by biofuels.
Źródło:: Journal of KONES; 2008, 15, 4; 545-555
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 7.

Tytuł:: Study on kerosene atomization process under a high speed air stream
Autorzy:: Perkowski, W.
Irzycki, A.
Snopkiewicz, K.
Grudzień, Ł.
Kawalec, M.
Powiązania:: https://bibliotekanauki.pl/articles/247137.pdf
Data publikacji:: 2011
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: transport
aircraft engine
combustion chamber
fuel atomization
Opis:: For the needs of fuel-injection system development for the experimental detonation combustion chamber with a rotating detonation (PoiG - Project: "Turbine engine with detonation combustion chamber") a series of experiments with injection of kerosene under a high speed air stream was performed at the Institute of Aviation. The proper preparation of combustible mixture is very important for the initiation and sustenance of a rotating detonation. The task in case of kerosene-air mixture is far more difficult than for mixtures of hydrogen-air or kerosene-oxygen. A simple stream injector has been tested as a base system, and the kerosene was injected perpendicular to the air stream vector directly from the plane wall of the constant cross-section channel. The process of injection and atomization of kerosene was observed in the special transparent visualization chamber, enabling the spray observation of two mutually perpendicular directions. In subsequent experiments air pressure, air temperature and air flow velocity as well as and injection pressure of kerosene were varied. The tested process was photographed and, in case of chosen experiments, filmed using a high-speed digital camera. The surveys were aimed at identifying and assessing of following parameters of fuel atomization process: the range of the fuel stream and filling grade of research channel with aerosol, aerosol homogeneity and the size of forming it droplets, the possible presence of fuel streams flowing down the walls of channel. The resulting photos allowed for more comprehensive, but only a qualitative assess of the spraying process, while the filmed small regions of visualization chamber allowed the counting down and dimensioning of droplets. This paper presents a test facility and measuring techniques applied during the research activity and selected results of carried out tests.
Źródło:: Journal of KONES; 2011, 18, 4; 341-347
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 8.

Tytuł:: Resonance tests - vibration mode shapes from the wing torsion group
Autorzy:: Wiśniewski, W.
Powiązania:: https://bibliotekanauki.pl/articles/245897.pdf
Data publikacji:: 2009
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: transport
aircraft
resonance tests
vibration mode
torsion wing
Opis:: Resonances of the „ wings torsion " mode shapes to a large extent depend on the structural parameters of the wing, and more specifically to the existence or not of fuel tanks at the wings ends, munitions hard points or engines mounted on the wings. In the paper the group of resonances is presented with mode shapes in which the one, two or three node aircraft wing torsion is present. It is shown in the paper, that these vibration mode shapes consist both of fuselage bending or torsion. Resonance frequencies with mode shapes in which one, two or three node wing torsion occurs depend fundamentally on existence of wing hardpoints. If hardpoints are occupied by fuel tanks, these frequencies are varying continuously in wide range. The various interesting from cognitive point of view combinations have place then, including variable frequencies and variable mode shapes as a function of fuel consumption. The aim for the analysis of 3 cases of resonance a wing torsion mode shapes of airplanes and gliders was to investigate the relationships and mechanisms that are taking place and operate between the torsioningl vibration of the wings and bending or torsion vibrations of the fuselage. Recognition of these phenomena should facilitate the researcher to understand and search effectively and explore the resonances of„ wing torsion " mode shapes.
Źródło:: Journal of KONES; 2009, 16, 4; 557-561
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 9.

Tytuł:: Problems of failures of airplanes and helicopters
Problemy uszkodzeń statków powietrznych
Autorzy:: Lewitowicz, J.
Powiązania:: https://bibliotekanauki.pl/articles/246444.pdf
Data publikacji:: 2007
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: transport
statki powietrzne
diagnostyka
uszkodzenia
aircraft
diagnostics
failure
Opis:: Trzy obszary diagnostyki: genezowanie, kontrola stanu i prognozowanie wymagają wiedzy o możliwych uszkodzeniach statków powietrznych. Uszkodzenia zmieniają procesy użytkowania samolotów i śmigłowców. Mają one wpływ na bezpieczeństwo lotów. W pracy opisano wpływ uszkodzeń na proces użytkowania statków powietrznych. Omówiono problematykę uszkodzeń załączając przykłady charakterystycznych uszkodzeń. Artykuł koncentruje się na rodzajach niesprawności i uszkodzeń oraz fizyce i diagnostyce uszkodzeń. Odpadnięcie górnej części pokrycia kadłuba samolotu w czasie podejścia do lądowania, korozyjno - zmęczeniowe pęknięcie belki skrzydła, udziały procentowe uszkodzeń w podziale na specjalności lotnicze i przyczyny wypadków lotniczych, udział procentowy uszkodzeń w różnych fazach lotu samolotów, złomy zmęczeniowe łopatek sprężarki i turbiny oraz dysku turbiny silnika odrzutowego są przedstawione w artykule. Uszkodzenia pierwotne stanowią podstawę do wnioskowania statystycznego o trwałości i niezawodności elementów i zespołów lotniczych. Uszkodzenia wtórne są rejestrowane jako skutki uszkodzeń pierwotnych. Dla praktyki eksploatacyjnej najbardziej przydatna jest klasyfikacja uszkodzeń elementów, która umożliwia makroskopową ocenę postaci uszkodzenia oraz domniemanej przyczyny jej powstania.
Three basic areas of diagnostics: genesis, checking of condition and prognosis should be developed including the aeronautical applications. This we to be realized because of a number of new destructive agents as the ageing of complication of software systems and automatic control systems even when the level of reliability of the systems is very high. But one should rate the increasing of failures costs as a part of all operators. The paper concentrates on kinds of inefficient and damages and on the physics and diagnostics of damages. Upper-fuselage skins separated in the course of approach, corrosion and fatigue induced fracture of a wing beam, percentage of damages/failures attributable to particular aeronautical branches and causes of air accidents (military aviation per one year), percentage of damages/failures at different stages of aircraft flight, fatigue fractures of compressor and turbine blades of a turbojet engine. Primary damages determine base for the statistical conclusion on durability and dependability of elements and air-sets. Secondary damages are registered as results primary damages. For the exploitive practice most useful is the classification of damages of elements which makes possible the macroscopic estimation character of the damage and supposed reason its appearance.
Źródło:: Journal of KONES; 2007, 14, 3; 339-346
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 10.

Tytuł:: Conceptual design of blended wing body business jet aircraft
Autorzy:: Mulyanto, T.
Luthfi Imam Nurhakim, M.
Powiązania:: https://bibliotekanauki.pl/articles/242317.pdf
Data publikacji:: 2013
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: transport
business jet aircraft
blended wing body
conceptual design
Opis:: Blended Wing Body concept offers several advantages compared to traditional aircraft tube and wing concept. The advantages mainly come from the distributed aerodynamic and structural loads, which leads to better aerodynamic performance as well as lighter structural weight. Most of the existing studies were focused on big transport aircraft carrying 400 to 800 passenger. In this study, a conceptual design of a business jet aircraft applying blended wing body concept is carried out. The market forecast for this category of aircraft can reach up to 24000 aircraft in the next 20 years. The possibility of having larger cross section is one of the competitive advantages, notably in a long-range flight. The requirement stated was to fly a trans-atlantic flight and carrying up to 18 passengers. It has to have a low floor height permitting easy passenger access. The design process consists of initial weight estimation, initial sizing, and preliminary aerodynamics, weight and balance and performance analysis. Some design consideration specially related with Blended Wing Body concept will be discussed, i.e. take-off and landing aerodynamics, structural concept, stability and control. The final design resulted in twin-engine aircraft, a Maximum Take-off Weight of 44 ton, cabin floor area of 6.9 x 10 m, winglet and split rudder for directional stability and control, and elevons for longitudinal and lateral control.
Źródło:: Journal of KONES; 2013, 20, 4; 299-306
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 11.

Tytuł:: Reduction emission level of harmful components exhaust gases by means of control of parameters influencing on spraying process of biofuel components for aircraft engines
Autorzy:: Jankowski, A.
Powiązania:: https://bibliotekanauki.pl/articles/245547.pdf
Data publikacji:: 2011
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: transport
aircraft engines
alternative fuels
fuel atomization
exhaust gas emissions
Opis:: The aim of the research is to test the fuel additives which decrease dimensions of atomised fuel drops, by applying changes to the specific parameters which impact the atomisation process. Those parameters include density, surface tension, viscosity and the viscosity index. Dimensions of drops of biofuels are much bigger compared to hydrocarbon fuels. By modifying the physical and chemical parameters of biofuels, dimensions of drops in an atomised fuel stream should become smaller. Those dimensions play a major role for the level of emissions of hydrocarbon and carbon monoxide, as well as mainly nitrogen oxides and particulates. The research on emissions of toxic components of fuel is relatively advanced today in the field of piston combustion engines, especially for use in car vehicles. However, the dynamic development of the air transport brings more pressure on the issue of toxic emissions in the case of aircraft engines. The level of toxic emissions from aircraft engines may be from ten up to even several thousand times greater than the level of emissions from piston engines. The issue of how biofuel additives can affect the process of fuel atomisation and thus enable the control over the atomisation to obtain the smallest possible drops leading to reduced nitrogen oxides emissions is a new and original issue. The reduced nitrogen oxides emissions in the case of biofuels is of utmost significance because, according to latest knowledge, those levels are increasing.
Źródło:: Journal of KONES; 2011, 18, 3; 129-134
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 12.

Tytuł:: Possibilities of voice supporting of the pilot in multi-task military aircraft
Autorzy:: Szelmanowski, A.
Pazur, A.
Prusik, T.
Malanowicz, A.
Powiązania:: https://bibliotekanauki.pl/articles/247441.pdf
Data publikacji:: 2017
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: transport
aviation
aircraft voice supporting system
cockpit voice activated system
lotnictwo
Opis:: The article presents selected results of the analytical works, carried out in the Air Force Institute of Technology, in the field of possibilities to support the pilot’s work in the cabin of the modern multi-task aircraft or military helicopter with the use of the computer voice communication assistant, with automatic recognition of the pilot’s voice and speech, which operates in conditions of the lack of time. There are presented the voice systems warning the pilot of the occurrence of an emergency state, as the so-called voice guides, P-591-04 type, used in the MiG-29 multipurpose aircraft and RI-65 type, used in the Mi-17 and Mi-24 helicopters. As an example of implementation of the concept of a new system supporting the pilot’s work, there was selected the voice communication system, constructed in the Air Force Institute of Technology for the W-3PL multi-purpose helicopter with the ZSA integrated avionics system. The main research problems related to the construction of integrated avionics systems, verbally supporting the pilot’s work, were discussed, and the specialized tools and research stations used in the Air Force Institute of Technology for the phonoscopic speech and voice studies, were presented. Furthermore, an example of the functional diagram and the system architecture of the pilot’s work verbal supporting for a selected emergency situation on the aircraft board were demonstrated, as well as the expected range of that system’s applications.
Źródło:: Journal of KONES; 2017, 24, 1; 333-338
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 13.

Tytuł:: Possibility of upgrading fighter aircraft MiG-29 in the field of helmet-mounted display systems
Autorzy:: Pazur, A.
Borowski, J.
Kowalczyk, H.
Szelmanowski, A.
Powiązania:: https://bibliotekanauki.pl/articles/244909.pdf
Data publikacji:: 2017
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: transport
aviation
aircraft glass cockpit systems
helmet mounted display systems
lotnictwo
Opis:: The article presents selected results of the analytical work carried out in the Air Force Institute of Technology in the field of information visualization capabilities of helmet-mounted guidance and navigation in fighter aircraft MiG- 29. There is presented the SzCz-3UM headset system of target’s indication, currently used on-board of MiG-29, which is directly cooperating with the pilot during the combat flight. There was presented that the information from the onboard systems of this aircraft containing analogue devices must be computer-processed into digital form in order to present flight data in the helmet-mounted display system. However, MiG-29 aircraft, used in the Polish Air Force, are equipped with modern digital avionics (integrated avionics system) based on the MIL-1553B digital data buses, which gives the possibility of the new helmet-mounted imaging of flight parameters via the computer data processing from aircraft’s devices and on-board installations. To develop guidelines for the construction of the helmet-mounted system for the MiG-29, the SWPL-1 Cyklop flight data-displaying system was adopted (system developed in the Air Force Institute of Technology as avionics system modernization for Mi-17 military helicopters). There are discussed the main problems of scientific and specialist research positions used in the Air Force Institute of Technology to assess the accuracy of the selected equipment components of avionics systems and determine credibility of information provided to the pilot during the flight.
Źródło:: Journal of KONES; 2017, 24, 1; 291-298
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 14.

Tytuł:: Analysis of effects of shape and location of micro-turbulators on unsteady shockwave-boundary layer interactions in transonic flow
Autorzy:: Sznajder, J.
Kwiatkowski, T.
Powiązania:: https://bibliotekanauki.pl/articles/242878.pdf
Data publikacji:: 2016
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: transonic flow control
laminar-turbulent transition
flow simulations
aircraft engineering
transport
vehicles
Opis:: Solutions for turbulisation of a part of laminar boundary layer upstream of shockwave on laminar airfoil in transonic flow were investigated by means of solution of Unsteady Reynolds-Averagd Navier-Stokes equations using as a closure the four-variable Transition SST turbulence model of ANSYS FLUENT solver. This turbulence model has the capability of resolving laminar-turbulent transition occurring in undisturbed flow as well as under the influence of flow-control devices. The aim of the work was to investigate possibilities of improvement of aerodynamic characteristics of laminar wing of a prospective transport aircraft in adverse conditions characterised by occurrence of a shockwave over a laminar-turbulent transition region with separation of laminar flow under the shockwave. The subject is important for application of laminar flow technology, offering economic and environmental advantages due to decreased friction drag, into civil transport aviation. Natural laminar-turbulent transition in the investigated conditions takes place with occurrence of “laminar separation bubble” under the foot of a shockwave and the resulting shockwave is intensive and prone to unsteady oscillations, the “buffet” phenomenon, limiting operational range of flight parameters. In order to counteract the harmful effects of natural laminar-turbulent transition in transonic flow two types of turbulators, placed upstream of the shockwave, were investigated. One of them consisted of delta-shaped vortex generators, producing chordwise-oriented vortices. The other consisted of rectangular micro-vanes, perpendicular to flow and to airfoil surface producing vortices of rotation axes oriented spanwise. Effectiveness of both types of turbulators was investigated for varying height and their location on airfoil chord. Both types of turbulators have proved their effectiveness in tripping laminar boundary layer. The specific effects of the tutbulators, different for each type occurred in the region where laminar separation takes place on clean airfoil. As a result, the changes of lift and drag were different for each type of turbulators.
Źródło:: Journal of KONES; 2016, 23, 2; 373-380
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 15.

Tytuł:: Determination of ice deposit shape and ice accretion rate on airfoil in atmospheric icing conditions and its effects on airfoil characteristics
Autorzy:: Sznajder, J.
Sieradzki, A.
Stalewski, W.
Powiązania:: https://bibliotekanauki.pl/articles/242499.pdf
Data publikacji:: 2017
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: aerodynamics
two-phase flow
simulation of ice accretion
aircraft engineering
transport
vehicle
Opis:: 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 accretion on NACA 0012 airfoil were compared with results of experiment conducted in icing wind tunnel for a 420 s long process of ice accretion in steady-flow, steady angle-of-attack conditions. Close agreement of values and location of maximum ice thickness obtained in experiment and in the flow, simulations can be observed. For the airfoil deformed with ice, contour determination of its aerodynamic characteristics at several other angles of attack was conducted proving dramatic degradation of its aerodynamic characteristics due to ice deformation.
Źródło:: Journal of KONES; 2017, 24, 2; 271-278
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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