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Tytuł:
The effect of using the Kline-Fogleman modification upon the coefficient characteristics of aerodynamic forces in the airfoil
Autorzy:
Szczepaniak, R.
Bąbel, R.
Grzywacz, A.
Stryczniewicz, W.
Kowaleczko, G.
Powiązania:
https://bibliotekanauki.pl/articles/245705.pdf
Data publikacji:
2018
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
airfoil
CFD
aerodynamics characteristics
Kline-Fogleman modification
NACA0012 airfoil
Opis:
The wing is the main aircraft construction element, whose main task is to produce the lift, balancing the aircraft weight as well as ensuring the execution of all flight states for which the aircraft was designed. The selection of appropriate airfoils or the development of new ones is one of the most important constructions goals. As a rule, constructors aim at ensuring a sufficiently large lift with little aerodynamic drag in order to increase the scope of utility angles of attack and such shaping of these characteristics so that the aircraft performance, close to the critical angles of attack, guarantees an adequate level of safety. One of the methods of improving the aerodynamic properties of airfoils is the Kline-Fogleman modification. It involves an application of a step into the airfoil contour at a place. It enforces the creation of a swirling air stream, preventing the separation and maintaining airflow over the profile and thus the reduction of drags, as well as delaying separation. The use of this type of a solution is justified when designing unmanned aerial vehicles, of small sizes, which move with slow speeds and sometimes-large angles of attack, including those close to critical angels of attack. The Kline-Fogleman modification decreases the likelihood of aircraft stalling. The aim of this work is to present an analysis of airflow over NACA0012 airfoil with Kline-Fogleman modification. The calculations were made by solving the problem of numerical fluid mechanics. For calculations, the Comsol Maribor programme was used. The investigation focused on several different airfoil modifications (KFm-1, KFm-2, KFm-3). This enabled a selection of a solution, providing the most desirable aerodynamic characteristics.
Źródło:
Journal of KONES; 2018, 25, 2; 349-356
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Airfoil Tonal Noise Prediction Using Urans
Autorzy:
Klimczyk, Witold
Sieradzki, Adam
Powiązania:
https://bibliotekanauki.pl/articles/36829323.pdf
Data publikacji:
2023
Wydawca:
Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:
airfoil tonal noise
aeroacoustics
CFD
Opis:
To examine the feasibility of the laminar boundary layer (LBL), vortex shedding (VS) tonal noise modelling using unsteady Reynolds-averaged Navier-Stokes (URANS) was investigated for the non-symmetric S834 airfoil. A transition SST turbulence model was used to model the laminar-turbulent transition and its vital influence on the laminar bubble and hydrodynamic instabilities generation. The influence of turbulence on the unsteady vortex patterns was investigated. Hence, the hybrid aeroacoustic analysis with Lighthill analogy was conducted to obtain the acoustic pressure field. The approach allowed us to model hydrodynamic instabilities and the resulting VS tonal noise. The frequency of VS matched the experimental data, giving the same 1/3 octave tonal peak only for a limited freestream turbulence regime. The simplification of the present method did not allow us to model the aeroacoustic feedback loop, and resulted in lack of instabilities for higher freestream turbulence.
Źródło:
Transactions on Aerospace Research; 2023, 4 (273); 1-17
0509-6669
2545-2835
Pojawia się w:
Transactions on Aerospace Research
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Application of evalutionary approach to thermodynamical optimization of gas turbine airfoil cooling configuration
Autorzy:
Nowak, G.
Powiązania:
https://bibliotekanauki.pl/articles/240622.pdf
Data publikacji:
2010
Wydawca:
Polska Akademia Nauk. Czytelnia Czasopism PAN
Tematy:
algorytmy ewolucyjne
optymalizacja
płaty turbiny
airfoil cooling
evolutionary algorithm
optimization
turbine airfoil
Opis:
Cooling of the hot gas path components plays a key role in modern gas turbines. It allows, due to efficiency reasons, to operate the machines with temperature exceeding components. melting point. The cooling system however brings about some disadvantages as well. If so, we need to enforce the positive effects of cooling and diminish the drawbacks, which influence the reliability of components and the whole machine. To solve such a task we have to perform an optimization which makes it possible to reach the desired goal. The task is approached in the 3D configuration. The search process is performed by means of the evolutionary approach with floating-point representation of design variables. Each cooling structure candidate is evaluated on the basis of thermo-mechanical FEM computations done with Ansys via automatically generated script file. These computations are parallelized. The results are compared with the reference case which is the C3X airfoil and they show a potential stored in the cooling system. Appropriate passage distribution makes it possible to improve the operation condition for highly loaded components. Application of evolutionary approach, although most suitable for such problems, is time consuming, so more advanced approach (Conjugate Heat Transfer) requires huge computational power. The analysis is based on original procedure which involves optimization of size and location of internal cooling passages of cylindrical shape within the airfoil. All the channels can freely move within the airfoil cross section and also their number can change. Such a procedure is original.
Źródło:
Archives of Thermodynamics; 2010, 31, 2; 3-20
1231-0956
2083-6023
Pojawia się w:
Archives of Thermodynamics
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Wind tunnel research on the influence of active airflow on the lift force generated by the airfoil
Autorzy:
Magryta, P.
Powiązania:
https://bibliotekanauki.pl/articles/103075.pdf
Data publikacji:
2013
Wydawca:
Stowarzyszenie Inżynierów i Techników Mechaników Polskich
Tematy:
wind tunnel
airfoil
3D printer
Opis:
The paper discusses the results of wind tunnel tests of airfoils with additional active airflow applied to their upper surfaces. These studies were carried out for a range of velocities up to 28 m/s in an open wind tunnel. Several types of airfoils selected for the examination feature different geometries and are widely applied in today’s avia¬tion industry. The changes in the lift and drag force generated by these airfoils were recorded during the study. The test bench for the tests was equipped with a compressor and a vacuum pump to enable airflow through some holes on the airfoil upper surface. A rapid prototyping method and a 3D printer based on a powder printing technique were applied to print the airfoils. All of their surfaces were subject to surface grind¬ing to smooth their external surfaces. The wind tunnel tests with and without active airflow applied to airfoils are summarised in the paper.
Źródło:
Advances in Science and Technology. Research Journal; 2013, 7, 19; 60-65
2299-8624
Pojawia się w:
Advances in Science and Technology. Research Journal
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Stability and bifurcation analysis for an airfoil model with a high-order nonlinear spring
Autorzy:
Li, Shuqun
Zhou, Liangqiang
Powiązania:
https://bibliotekanauki.pl/articles/2086970.pdf
Data publikacji:
2022
Wydawca:
Polskie Towarzystwo Mechaniki Teoretycznej i Stosowanej
Tematy:
nonlinear airfoil model
bifurcation
stability
normal form
Opis:
In this paper, the stability and bifurcation of an airfoil model with a high-order nonlinear spring are investigated both analytically and numerically. Two possible types of bifurcation at the equilibrium point are studied. It is proved that the zero characteristic root can only be a single zero. With the help of the center manifold theory and the normal form theory, the expressions of critical bifurcation curves leading to initial bifurcation and secondary bifurcation are obtained. Numerical simulations confirm the theoretical results.
Źródło:
Journal of Theoretical and Applied Mechanics; 2022, 60, 2; 185--197
1429-2955
Pojawia się w:
Journal of Theoretical and Applied Mechanics
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
A combined numerical-experimental model of air foil bearing compliant structure
Autorzy:
Łagodziński, J.
Zieliński, P.
Powiązania:
https://bibliotekanauki.pl/articles/175400.pdf
Data publikacji:
2016
Wydawca:
Polska Akademia Nauk. Czytelnia Czasopism PAN
Tematy:
airfoil bearing
numerical model
gas bearing coefficients
Opis:
The paper concerns the development process of numerical-experimental model of air foil bearing compliant structure. Theoretically, static and dynamic characteristics of the foil bearing are the result of elastic combined properties of the two serially connected elements. One of them is a thin gas film of very small thickness and relatively high static and dynamic stiffness. The second elastic element is a pretensioned bump foil spring. This paper focuses on the properties of compliant foil structure and leaves aside the gas film behavior. At the beginning of the model development, the global stiffness and damping properties of compliant structure were obtained from the test stand measurements. In the next step, some assumptions concerning the model were made. The main one was the replacememy of the single bumps of the corrugated foil by the set of elastic-damping numerical elements. At last, the fine-tuning of the model was carried out. The tuning involved changing of subelements local damping and stiffness properties, which in effect influenced the global properties of foil bearing. The tuning criterion for the model was defined as follows: the bearing global stiffness and damping properties of the model should not differ from the experimentally obtained values more than 10%.
Źródło:
Transactions of the Institute of Fluid-Flow Machinery; 2016, 133; 117-129
0079-3205
Pojawia się w:
Transactions of the Institute of Fluid-Flow Machinery
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Numerical study of the parallel vortex airfoil interaction
Autorzy:
Piechna, J.
Szumowski, A.
Powiązania:
https://bibliotekanauki.pl/articles/1953972.pdf
Data publikacji:
1998
Wydawca:
Politechnika Gdańska
Tematy:
parallel vortex airfoil interaction
numerical study
airfoil flow
finite volume method
instantaneous flow patterns
pressure distribution
lift coefficients
Opis:
The effect of a strong vortex interacting with an airfoil flow is investigated numerically. The finite volume method for Euler equations is applied. Instantaneous flow patterns, including pressure distributions along the airfoil and lift coefficients, were calculated for various miss distances of the vortex passing parallely to the airfoil plane. It has been found that the effects of interaction are much stronger when the vortex approaching the airfoil accelerates the flow at the pressure surface than in the case when the vortex decelerates the flow at the suction surface. The lift coefficient only slightly depends on the vortex core radius if the velocity induced at the airfoil surface by vortices of various cores is constant. In contrast to this the intensity of the acoustic disturbance produced during the interaction strongly depends on the core radius even for a constant induced flow velocity.
Źródło:
TASK Quarterly. Scientific Bulletin of Academic Computer Centre in Gdansk; 1998, 2, 2; 357-372
1428-6394
Pojawia się w:
TASK Quarterly. Scientific Bulletin of Academic Computer Centre in Gdansk
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Developing a new approach in diagnostic methods of technical state of propeller of gas pumping unit
Autorzy:
Zamikhovskyi, L.
Ivanyuk, N.
Powiązania:
https://bibliotekanauki.pl/articles/298946.pdf
Data publikacji:
2013
Wydawca:
Akademia Górniczo-Hutnicza im. Stanisława Staszica w Krakowie. Wydawnictwo AGH
Tematy:
blade
gas flow
integral equation
airfoil
aerodynamic characteristics
wear
Opis:
To estimate the influence of changes in aerodynamic and shape characteristics of propellers of the gas pumping unit on process variables of gas pumping unit using the mathematical modeling methods. The method theoretically based Fredholm equation of the second kind for the tangential velocity component, its computational solution, and estimation of aerodynamical characteristics of airfoil of blades in special chosen frame of reference depending on the airfoil and attack angle. For the estimation of influence of shape configuration changes, which are determined by the configuration of blades of propeller on vibration characteristics of blades, cross-sectional area of blades and its second moment the numerical methods are used. Different methods of reproducing of shape configuration of airfoil of blades using experimental data of coordinates of relevant set points of airfoil are considered. Theoretical results could be used in the research and estimation of influences of configuration blade change and quantity of strained blades on the productivity of pumping units. The conducted research and its results can be the basis of creating of new non-destructive testing methods for gas pumping units and creating a new system of control. Shown results allow increasing operational reliability of facilities that were under research and systems, which can be helpful for Ukrainian gas and oil industry facilities.
Źródło:
AGH Drilling, Oil, Gas; 2013, 30, 2; 345-351
2299-4157
2300-7052
Pojawia się w:
AGH Drilling, Oil, Gas
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Steady and unsteady analysis of NACA 0018 airfoil in vertical-axis wind turbine
Autorzy:
Rogowski, K.
Hansen, M. O. L.
Maroński, R.
Powiązania:
https://bibliotekanauki.pl/articles/279244.pdf
Data publikacji:
2018
Wydawca:
Polskie Towarzystwo Mechaniki Teoretycznej i Stosowanej
Tematy:
airfoil characteristics
vertical-axis wind turbine
computational fluid dynamics
Opis:
Numerical results are presented for aerodynamic unsteady and steady airfoil characteristics of the NACA 0018 airfoil of a two-dimensional vertical-axis wind turbine. A geometrical model of the Darrieus-type wind turbine and the rotor operating parameters used for numerical simulation are taken from the literature. Airfoil characteristics are investigated using the same mesh distribution around the airfoil edges and two turbulence models: the RNG k-ε and the SST Transition. Computed results for the SST Transition model are in good agreement with the experiment, especially for static airfoil characteristics.
Źródło:
Journal of Theoretical and Applied Mechanics; 2018, 56, 1; 203-212
1429-2955
Pojawia się w:
Journal of Theoretical and Applied Mechanics
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Airfoil selection for wing in ground effect craft
Autorzy:
Rojewski, A.
Bartoszewicz, J.
Powiązania:
https://bibliotekanauki.pl/articles/245626.pdf
Data publikacji:
2017
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
transport
ekranoplan
numerical analysis
wing in ground effect
airfoil
Opis:
The main purpose of this article was to select airfoil, which generates the biggest lift coefficient, with possibly smallest drag coefficient when the airfoil flies in the wing in ground effect. Wing in ground effect occurs in the direct proximity of ground, the article presents wing in ground effect creation mechanism description with automotive and aerospace examples. The article shows also wing in ground conditions of Ansys Fluent software simulation for all cases with conditions of analysis convergence. The article contains results of the numerical analysis for ten airfoils in three different positive angles of attack in the wing in ground flight; ten airfoils for free stream flight in the same angles of attack as in wing in ground effect, results contains lift and drag coefficients with NACA M8 airfoil presentation as authors choice for wing in ground effect crafts airfoil with full simulation results for angles of attack from –5° to 15°, with profile characteristics. The article shows physics of stall in the wing in ground effect, and a description why stall in WIG effect flight occurs only with drag coefficient rise without lift coefficient drop, and safety measures for aircraft landing with wing in ground effect influence.
Źródło:
Journal of KONES; 2017, 24, 4; 265-269
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Helicopter blade morphing strategies aimed at mitigating environmental impact
Strategie aktywnego kształtowania profilu łopat helikoptera w celu redukcji negatywnego wpływu ich pracy na środowisko
Autorzy:
Pagano, A.
Ameduri, S.
Cokonaj, V.
Prachar, A.
Zachariadis, Z.
Drikakis, D.
Powiązania:
https://bibliotekanauki.pl/articles/281874.pdf
Data publikacji:
2011
Wydawca:
Polskie Towarzystwo Mechaniki Teoretycznej i Stosowanej
Tematy:
blade twist
airfoil camber control
SMA
morphing
main rotor
Opis:
The requirement of mitigating the environmental impact of helicopters has been addressed globally within the FRIENDCOPTER Project in the sense that several aspects (such as noise abatement, vibration reduction, fuel consumption) have been studied in parallel with different approaches among which there is the active blade control. In the work at hand, attention is paid on two topics aimed at mitigating helicopter environmental impact through a morphing strategy: the aerodynamic optimization of a blade section whose camber can be affected by an actuator and the design of a SMA based static twist concept, aimed at extending the helicopter flight envelope. The latter device is based on a SMA rod which is integrated in the spanwise direction within the blade structure at different positions. The actuator, when heated, transmits a torque couple which induces twist onto the blade. The twist variation due to the SMA device activation has been predicted by a FE approach (MSC/Marc software implemented with the SMA Brinson model). Finally, rotor performance in hover has been estimated with the actuator in power on and off positions, highlighting benefits coming from several spanwise integrations/distributions of the SMA device.
Wymóg jak najmniejszej uciążliwości helikopterów na otaczające środowisko został wyartykułowany w projekcje europejskim FRIENDCOPTER, w którym kilka zagadnień (takich jak redukcja hałasu, drgań, obniżanie zużycia paliwa) poddano równoległym badaniom, łącznie z problemem odpowiedniego kształtowania profilu łopat wirnika głównego do osiągnięcia tych celów. W prezentowanej pracy uwagę skupiono na ograniczaniu środowiskowej uciążliwości helikopterów poprzez przyjęcie dwóch koncepcji kształtowania łopat wirnika – aerodynamiczną optymalizację przekroju łopaty, której kształt może być deformowany za pomocą aktuatorów oraz wprowadzenie stopów z pamięcią kształtu (SMA) do skręcania profilu łopaty, co pozwala na rozszerzenie obwiednich osiągów helikoptera. Drugie rozwiązanie zostało oparte na zastosowaniu prętów SMA zintegrowanych z łopatą w kilku miejscach wzdłuż jej długości. Aktuatory SMA generują pary momentów skręcających przy podgrzaniu. Modelowanie tego efektu opisano za pomocą metody elementów skończonych (przy użyciu modelu Brinson SMA i oprogramowania MSC/Marc). Na koniec przedyskutowano wydajność wirnika głównego dla helikoptera w zawisie przy włączonym i wyłączonym układzie sterowania. Podkreślono korzyści uzyskane z wzdłużnego wkomponowania w łopatę wirnika kilku aktuatorów SMA.
Źródło:
Journal of Theoretical and Applied Mechanics; 2011, 49, 4; 1233-1259
1429-2955
Pojawia się w:
Journal of Theoretical and Applied Mechanics
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Propeller optimization for small unmanned aerial vehicles
Autorzy:
Kusznir, T.
Smoczek, J.
Powiązania:
https://bibliotekanauki.pl/articles/246608.pdf
Data publikacji:
2017
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
unmanned aerial vehicles
particle swarm optimization (PSO)
airfoil modelling
Opis:
Small-unmanned aerial vehicle propellers usually have a low figure of merit due to operating in the low Reynold’s number region due to their size and velocity. The airflow on the airfoil becomes increasingly laminar in this region thus increasing the profile drag and consequently reducing the figure of merit of the rotor. In the article, the airfoil geometries are parameterized using the Class/Shape function transformation. Particle swarm optimization is used to design an airfoil, operating in a Reynolds number of 100,000, which has a high lift to drag ratio. To avoid exceeding geometric constraints of the airfoil, a deterministic box constraint is added to the algorithm. The optimized airfoil is then used for a preliminary design of a rotor; given some design, constraints on the tip chord the rotor radius and the blade root chord, with parameters that achieve the highest theoretical figure of merit. The rotor parameters are obtained using a combination of momentum theory and blade element theory. The figure of merit of an optimal propeller with the same geometric parameters is then compared using the optimized airfoil and the Clark Y airfoil. The optimization is done in MATLAB while the aerodynamic coefficients are obtained from XFOIL. The results of the numerical simulation are presented in the article.
Źródło:
Journal of KONES; 2017, 24, 2; 125-132
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Numerical investigation of endplates influence on the wing in ground effect lift force
Autorzy:
Rojewski, Adam
Bartoszewicz, Jarosław
Powiązania:
https://bibliotekanauki.pl/articles/950130.pdf
Data publikacji:
2019
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
endplates
ekranoplan
numerical analysis
wing in ground effect
airfoil
Opis:
The article presents a comparison of the wing in ground effect magnitude of conceptual WIG craft model main characteristics for a wing with and without endplates which are also known as winglets in regular aircraft. In article, the author describes WIG effect with and WIG craft, which operates on low altitude, smaller than the length of wing chord, mostly above the water reservoir. WIG effect phenomenon is simple. The first aircraft needs to fly at adequate altitude, with a smaller distance between lower airfoil surface and ground static pressure rises, leading to rising of lift force. The main advantage of the wing in ground effect craft on regular aircraft is a much higher lift to drag ratio, also this phenomenon provides to drop in specific fuel consumption of aircraft and allows flying with heavier cargo due to higher lift force. Characteristics present in the article were designated from simulations, which were conducted in Ansys Fluent software. Results obtained for a wing with endplate in numerical analysis shows the superiority of this approach. Endplates provide to increase WIG effect by a decrease in induced drag through the move out vertices from the wing tips, which are made by differential pressure above and under the wing. As winglets in regular aircraft, endplates provide to save fuel. WIG craft does not need airports so it could be a cheap alternative for modern aircraft.
Źródło:
Journal of KONES; 2019, 26, 4; 205-210
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
The influence of the blades leading edge anti-erosion protection on main rotor performances
Autorzy:
Wojtas, M.
Czajkowski, Ł.
Sobieszek, A.
Powiązania:
https://bibliotekanauki.pl/articles/243585.pdf
Data publikacji:
2018
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
airfoil
rotor blades
flight tests
light rotorcrafts
ultra-light rotorcrafts
Opis:
This article presents the influence of rotor blade airfoil shape on main rotor performances. In this case, we analysed the influence of anti-erosion tape, which is applied to the leading edge of the blade to protect the blades from environmental conditions. In Gyro-Tech Innovation an Aviation Company and Institute of Aviation the independent tests of helicopter and gyroplane main rotors were performed. Research includes: bench tests, on the test stand for dynamic testing of insulated rotors and tests on two flying constructions, gyroplane Cavalon produced by AutoGyro GmbH Company and ultralight helicopter Dynali H3. On the test bench, a two-blade rotor, used in ultralight and unmanned helicopters, was tested. In article, the authors present importance of the proper selection and application of anti-erosion coatings on rotor blades. Discuss the behaviour of the above-mentioned constructions with main rotor blades leading edge covered anti-erosion tape, during flight tests. The results of bench tests, including the comparison of polar curves of the main rotor with anti-erosion coating and without were also presented and discussed. In the summary of this article among others the solution of technological pocked introduced in the rotor blade, corresponding to the thickness of the anti-erosion tapes, in such way that after tape is applied it does not change the contour of the blade airfoil were presented.
Źródło:
Journal of KONES; 2018, 25, 2; 409-414
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Design and optimisation of main rotor for ultralight helicopter
Autorzy:
Stalewski, W.
Powiązania:
https://bibliotekanauki.pl/articles/243641.pdf
Data publikacji:
2017
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
rotorcraft
ultralight helicopter
main rotor
airfoil
computer-aided design
optimisation
Opis:
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 concluded that the newly designed main rotor, compared to the baseline, may give certain improvement in helicopter performance in fast flight. In addition, the application of this newly designed rotor may lead to increase of a maximum speed of the helicopter flight, due to the greater lift force achievable by this rotor on the retreating blade, which is favourable from point of view of keeping of a lateral balance of the helicopter in fast flight.
Źródło:
Journal of KONES; 2017, 24, 4; 287-295
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
Dostawca treści:
Biblioteka Nauki
Artykuł
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