Conceptual design and CFD analysis of a new prototype of agricultural aircraft

Bravo-Mosquera, Pedro David; Cerón-Muñoz, Hernán Darío; Díaz-Vázquez, Guillermo; Catalano, Fernando Martini

doi:10.1016/j.ast.2018.07.014

Cited by 40 publications

(19 citation statements)

References 27 publications

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“…Por otra parte, las consideraciones anteriores fueron las bases principales para el diseño de los estabilizadores de la aeronave, los cuales se complementaron con las definiciones generales de la estabilidad dinámica y estática, tanto longitudinal como lateral, demostradas en la ecuación 1 (Bravo-Mosquera et al, 2018).…”

Section: Estimación Aerodinámicaunclassified

Diseño de aeronave de combate no tripulada de quinta generación para el apoyo aéreo cercano

Aguirre

García

et al. 2021

Ciencia y Poder Aéreo

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La evolución en el diseño de aeronaves de combate se ha visto modificada por la inclusión de nuevos parámetros de alta exigencia, dentro de los cuales se incluyen las áreas de investigación relacionadas con la aerodinámica, la furtividad y la optimización en los procesos de operación. El presente artículo contempla el diseño de un Vehículo de Combate Aéreo no Tripulado (UCAV) para la ejecución de misiones de Apoyo Aéreo Cercano (CAS por sus siglas en inglés) en las próximas décadas. Los resultados obtenidos demuestran las habilidades de los UCAV como aeronaves de quinta generación para el reemplazo de flotas reconocidas a nivel mundial (A-10 Thunderbolt II y Sukhoi Su-25) y, además, garantiza su utilidad y viabilidad en los futuros entornos de combate. Así mismo, la investigación se enfoca en una de las variables de mayor discusión respecto a la supervivencia en el combate aéreo, se trata de la furtividad por fenómenos electromagnéticos, con la cual se obtuvieron valores de Sección Equivalente de Radar (RCS) iguales a -24,18 dBsm o representables en un área de detectabilidad de 0,0038 m2 en configuración limpia, de modo que este valor es inferior al de aeronaves furtivas como lo es el Northrop Grumman B-2 Spirit. Finalmente, el diseño permite la operación con un máximo peso de despegue de 61,900 lb y una carga paga de 11,240 lb que se acondicionan a una configuración alar y de estabilizadores para rangos transónicos.

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Section: Estimación Aerodinámicaunclassified

Diseño de aeronave de combate no tripulada de quinta generación para el apoyo aéreo cercano

Aguirre

García

et al. 2021

Ciencia y Poder Aéreo

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“…Blended Wing Body aircraft) [7,8]. Furthermore, under certain considerations, these correlations have been firstly adapted and then employed for the conceptual design of unmanned aerial platforms that generally fit in the category of HALE UAVs [9][10][11]. However, their applicability on the design of other UAV categories (specially medium, small and micro) could lead to over or underestimate the aircraft components since UAVs employ different design trade-offs compared with transport aircraft [12].…”

Section: Introductionmentioning

confidence: 99%

“…Nonetheless, micro, small, and MALE UAVs employ power systems ranging lower than the aforesaid power and thrust ranges [9,10,23]. Thus, the above correlations and performance data can not be implemented to set the design space of smaller UAV configurations.…”

Section: Introductionmentioning

confidence: 99%

Propulsion Sizing Correlations for Electrical and Fuel Powered Unmanned Aerial Vehicles

Alulema¹,

Valencia²,

Narvaez³

et al. 2020

Preprint

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“…Bravo-Mosquera et al [6] presented conceptual design and prototype of an agricultural aircraft. Following the traditional design methods applied, six different winglet designs, which have different cant angles analyzed by means of a computational fluid dynamics program using Reynolds-Averaged-Navier-Stokes (RANS) equations.…”

Section: Introductionmentioning

confidence: 99%

Effects of Taper Ratio on Aircraft Wing Aerodynamic Parameters: A Comperative Study

Güzelbey¹,

Eraslan²,

Doğru³

2019

European Mechanical Science

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Wing design is one of the most important tasks for a designer to overcome during an aircraft design process. Therefore, a designer need to optimize so many wing geometrical parameters with the aim of obtaining an efficient wing geometry complying with requirements of the design. Taper ratio is one of these parameters, which is the ratio of root and tip chord lengths of a wing. In this study, firstly, a high aspect ratio rectangular aircraft wing was numerically investigated in terms of some aerodynamic parameters including induced drag coefficient, Oswald efficiency factor and lift coefficient together with its span-wise distribution by means of XFLR5 computational fluid dynamics program. The assessment of mesh accuracy of the program was done at the beginning of the analyses. Later on, with the aim of observing the effects of taper ratio on aircraft wing aerodynamic parameters, the revised versions of the wing, which have the taper ratios from 0.2 to 1.2 (with the increment of 0.2) were analyzed. In conclusion, depending on the analyses results, the wings having different taper ratios were compared in terms of obtained aerodynamic parameters and span-wise lift distributions. Moreover, tip vortices of each wing, together with their sizes, were obtained and also compared.

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Conceptual design and CFD analysis of a new prototype of agricultural aircraft

Cited by 40 publications

References 27 publications

Diseño de aeronave de combate no tripulada de quinta generación para el apoyo aéreo cercano

Diseño de aeronave de combate no tripulada de quinta generación para el apoyo aéreo cercano

Propulsion Sizing Correlations for Electrical and Fuel Powered Unmanned Aerial Vehicles

Effects of Taper Ratio on Aircraft Wing Aerodynamic Parameters: A Comperative Study

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