Most recent issue published online in the International Journal of Aerodynamics.
International Journal of Aerodynamics
http://www.inderscience.com/browse/index.php?journalID=140&year=2022&vol=7&issue=3
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International Journal of Aerodynamics
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© 2022 Inderscience Publishers Ltd
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International Journal of Aerodynamics
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http://www.inderscience.com/browse/index.php?journalID=140&year=2022&vol=7&issue=3
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Computational modelling of elongated body aerodynamics at variable pitch angles in post-critical flow condition
http://www.inderscience.com/link.php?id=129957
Special types of unmanned aerial vehicles are intended to fall unpowered through the air during the initial descent upon release from another aircraft. To predict dynamics of these vehicles in such high-speed falls and later develop means for steering, their aerodynamic characteristics need to be understood. In this work, a cylindrical body is simulated in steady translation through the air in post-critical flow regimes. Validation studies carried out for cylinders with known aerodynamic properties suggested the usage of Detached Eddy Simulation approach with SST <em>k</em>-<em>ω</em> turbulence model and <em>γ</em> transition model. The force and moment coefficients are determined for a rounded-edge cylinder in a range of pitch angles. The drag coefficient initially increases with the pitch angle, but at higher angles the drag variation becomes smaller. The side force demonstrates a well-defined maximum at a medium pitch angle. The aerodynamic moment for inclined body positions tend to force the body into the transverse orientation with respect to the incident flow.
Computational modelling of elongated body aerodynamics at variable pitch angles in post-critical flow condition
Konstantin I. Matveev; Miles P. Wheeler
International Journal of Aerodynamics, Vol. 7, No. 3 (2022) pp. 195 - 207
Special types of unmanned aerial vehicles are intended to fall unpowered through the air during the initial descent upon release from another aircraft. To predict dynamics of these vehicles in such high-speed falls and later develop means for steering, their aerodynamic characteristics need to be understood. In this work, a cylindrical body is simulated in steady translation through the air in post-critical flow regimes. Validation studies carried out for cylinders with known aerodynamic properties suggested the usage of Detached Eddy Simulation approach with SST <em>k</em>-<em>ω</em> turbulence model and <em>γ</em> transition model. The force and moment coefficients are determined for a rounded-edge cylinder in a range of pitch angles. The drag coefficient initially increases with the pitch angle, but at higher angles the drag variation becomes smaller. The side force demonstrates a well-defined maximum at a medium pitch angle. The aerodynamic moment for inclined body positions tend to force the body into the transverse orientation with respect to the incident flow.]]>
10.1504/IJAD.2022.129957
International Journal of Aerodynamics, Vol. 7, No. 3 (2022) pp. 195 - 207
Konstantin I. Matveev
Miles P. Wheeler
School of Mechanical and Materials Engineering, Washington State University, Pullman, Washington, USA ' School of Mechanical and Materials Engineering, Washington State University, Pullman, Washington, USA
aerodynamics
unmanned aerial vehicles
CFD
2023-04-04T23:20:50-05:00
Copyright © 2023 Inderscience Enterprises Ltd.
7
3
195
207
2023-04-04T23:20:50-05:00
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Speed deficit determination in the wake of a Darrieus-Troposkein turbine
http://www.inderscience.com/link.php?id=129992
A series of tests on small Darrieus-Troposkein Turbines (DTT) were performed with a wind tunnel, to determine the speed deficit and turbulence intensity that adds to the wake. These tests were made in order to provide information on the interaction that could result on an array of this type of wind turbines, laid on the rooftop of a building. The tested turbines had a diameter of 0.85 m and a height of 1.30 m. It had two blades of symmetrical cross section NACA 0024, with a solidity of 0.44 and tested with a Specific Speed (TRS) of 2.5. The decrease of the rotor speed was 10% with a wind speed from 9 to 13 m/s. The turbulence intensity added by the turbine in the wake, measured at a distance of one diameter was 0.27, and 0.17 measured at two diameters.
Speed deficit determination in the wake of a Darrieus-Troposkein turbine
Jorge Lassig; Carlos Labriola
International Journal of Aerodynamics, Vol. 7, No. 3 (2022) pp. 208 - 223
A series of tests on small Darrieus-Troposkein Turbines (DTT) were performed with a wind tunnel, to determine the speed deficit and turbulence intensity that adds to the wake. These tests were made in order to provide information on the interaction that could result on an array of this type of wind turbines, laid on the rooftop of a building. The tested turbines had a diameter of 0.85 m and a height of 1.30 m. It had two blades of symmetrical cross section NACA 0024, with a solidity of 0.44 and tested with a Specific Speed (TRS) of 2.5. The decrease of the rotor speed was 10% with a wind speed from 9 to 13 m/s. The turbulence intensity added by the turbine in the wake, measured at a distance of one diameter was 0.27, and 0.17 measured at two diameters.]]>
10.1504/IJAD.2022.129992
International Journal of Aerodynamics, Vol. 7, No. 3 (2022) pp. 208 - 223
Jorge Lassig
Carlos Labriola
Department of Mechanical Engineering, University National of Comahue, Neuquén, Rio Negro, Argentina ' Department of Mechanical Engineering, University National of Comahue, Neuquén, Rio Negro, Argentina
Darrieus
wake
speed deficit
turbulence intensity
urban wind
2023-04-04T23:20:50-05:00
Copyright © 2023 Inderscience Enterprises Ltd.
7
3
208
223
2023-04-04T23:20:50-05:00
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Study of the flight of the Acer negundo samara
http://www.inderscience.com/link.php?id=130036
Samaras have been the object of intensive study in recent years. This inspiring aerodynamic rotary decelerator attracts research attention because of its simplicity: it is composed of a thin wing and a concentrated load. Specimens from <em>Acer negundo</em> seeds were taken in two batches to perform experimental measurements and for model configuration, mass properties and aerodynamic characteristics. The samara flight was then characterised by nutation angle, falling and rotation velocities. Then simulations were performed, and their results were compared with those of the experiments. The contrast exercise found that the simulation tool helps predict the behaviour of the flight of samaras. The contributions of this work are to characterise the flight of a particular maple samara belonging to <em>Acer negundo</em> specie, utilising experimental research and simulations of the samara flight using a simple routine developed for atmospheric decelerators, this last in order to determine the suitability of this tool for this particular application.
Study of the flight of the Acer negundo samara
F. Porritiello; V. Nadal Mora; J. Piechocki
International Journal of Aerodynamics, Vol. 7, No. 3 (2022) pp. 224 - 235
Samaras have been the object of intensive study in recent years. This inspiring aerodynamic rotary decelerator attracts research attention because of its simplicity: it is composed of a thin wing and a concentrated load. Specimens from <em>Acer negundo</em> seeds were taken in two batches to perform experimental measurements and for model configuration, mass properties and aerodynamic characteristics. The samara flight was then characterised by nutation angle, falling and rotation velocities. Then simulations were performed, and their results were compared with those of the experiments. The contrast exercise found that the simulation tool helps predict the behaviour of the flight of samaras. The contributions of this work are to characterise the flight of a particular maple samara belonging to <em>Acer negundo</em> specie, utilising experimental research and simulations of the samara flight using a simple routine developed for atmospheric decelerators, this last in order to determine the suitability of this tool for this particular application.]]>
10.1504/IJAD.2022.130036
International Journal of Aerodynamics, Vol. 7, No. 3 (2022) pp. 224 - 235
F. Porritiello
V. Nadal Mora
J. Piechocki
UIDET GTA-GIAI, Departamento de IngenierÃa Aeroespacial, Facultad de IngenierÃa, Universidad Nacional de La Plata, La Plata, Buenos Aires, Argentina ' UIDET GTA-GIAI, Departamento de IngenierÃa Aeroespacial, Facultad de IngenierÃa, Universidad Nacional de La Plata, La Plata, Buenos Aires, Argentina ' UIDET GTA-GIAI, Departamento de IngenierÃa Aeroespacial, Facultad de IngenierÃa, Universidad Nacional de La Plata, La Plata, Buenos Aires, Argentina
rotary wing decelerator
samara seed
rotary wing aerodynamics
low Reynolds number aerodynamics
2023-04-04T23:20:50-05:00
Copyright © 2023 Inderscience Enterprises Ltd.
7
3
224
235
2023-04-04T23:20:50-05:00
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Mathematical modelling and an insight into aircraft landing profile under influence of gust vibration
http://www.inderscience.com/link.php?id=130045
An aircraft pass through various phases of flight during operations but landing phase may jeopardise flight safety, if executed inefficiently. Various factors may compromise a safe landing but wind disturbance is unpredictable and difficult to handle during the landing phase. This study provides an insight using mathematical modelling into flight handling issues of an aircraft during landing under the influence of disturbances caused by wind while considering pilot input as an important factor for the handling issues. A mathematical modelling using equation of motion for a transport aircraft has been carried out to study gust profile and its effects on aircraft flightpath during lading. The numerical analysis includes a detailed parametric study of the effect of gust frequencies and amplitudes to aircraft handling technique during approach and landing. The vertical gust disturbances have more effects on the flightpath than the disturbances caused by a horizontal gust during landing and descend.
Mathematical modelling and an insight into aircraft landing profile under influence of gust vibration
Devinder Kumar Yadav; Perumal Kannan; Shuhaimi Mansor
International Journal of Aerodynamics, Vol. 7, No. 3 (2022) pp. 236 - 272
An aircraft pass through various phases of flight during operations but landing phase may jeopardise flight safety, if executed inefficiently. Various factors may compromise a safe landing but wind disturbance is unpredictable and difficult to handle during the landing phase. This study provides an insight using mathematical modelling into flight handling issues of an aircraft during landing under the influence of disturbances caused by wind while considering pilot input as an important factor for the handling issues. A mathematical modelling using equation of motion for a transport aircraft has been carried out to study gust profile and its effects on aircraft flightpath during lading. The numerical analysis includes a detailed parametric study of the effect of gust frequencies and amplitudes to aircraft handling technique during approach and landing. The vertical gust disturbances have more effects on the flightpath than the disturbances caused by a horizontal gust during landing and descend.]]>
10.1504/IJAD.2022.130045
International Journal of Aerodynamics, Vol. 7, No. 3 (2022) pp. 236 - 272
Devinder Kumar Yadav
Perumal Kannan
Shuhaimi Mansor
School of Aviation, Australian University, Mubarak Al-Abdullah Al-Jaber Area, Safat, Kuwait ' Embry Riddle Aeronautical University, Bukit Timah Road, Singapore ' Universiti Teknologi, Skudai, Iskandar Puteri, Johor Bahru, Malaysia
aircraft
airworthiness
aeronautical
aerodynamics
engineering
flight
landing
pilot
2023-04-04T23:20:50-05:00
Copyright © 2023 Inderscience Enterprises Ltd.
7
3
236
272
2023-04-04T23:20:50-05:00