Vee-tail conceptual design criteria for commercial transport aeroplanes

Sanchez-Carmona, Alejandro; Cuerno-Rejado, Cristina

doi:10.1016/j.cja.2018.06.012

Cited by 12 publications

(16 citation statements)

References 12 publications

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“…Furthermore, the placement of propellers over the V-tail avoids the downwash of the front Furthermore. The overall control power needed for a combined elevator-rudder input is less than compared to a conventional tail, since a high deflection can be obtained for a small elevator-rudder control input in the V-tail configuration [24].…”

Section: Aerodynamic Control Surfacesmentioning

confidence: 99%

“…It was calculated using Equation ( 24 It is important to note that the miscellaneous drag is due to the fuselage upsweep angle of 15 degrees. It was calculated using Equation ( 24), D/q = C D S ref = 3.83 u 2.5 A max (24) where S ref is the wing reference area, q is dynamic pressure, u is upsweep angle and A max is maximum fuselage cross-sectional area [28].…”

Section: Total Parasite Dragmentioning

confidence: 99%

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Design and Analysis of VTOL Operated Intercity Electrical Vehicle for Urban Air Mobility

et al. 2021

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This paper discusses the conceptual design of an intercity electrical vertical take-off-and-landing aircraft. A literature survey of existing eVTOL aircrafts, configuration selection, initial sizing, weight estimation, modelling and analysis was conducted. The present intercity eVTOL aircraft has the capability to carry four passengers along with one pilot for a distance of 500 km. Two specific aircraft modes, such as air-taxi and air-cargo mode, are considered in the present design. Market entry is predicted before 2031. Subsequently, innovative technologies are incorporated into the design. The present design features an aerodynamically shaped fuselage, tapered wing and a V-tail design. It can carry a nominal payload of 500 kg to a maximum range of 500 km at a cruise speed of Mach 0.168. The present eVTOL is comprised of a 5 m-long fuselage and an 11 m wingspan. It utilizes six tilt-rotor propeller engines. The maximum take-off weight and empty weight are 1755 kg and 1255 kg, respectively. The unit price is expected to be between USD 14.83 and 17.36 million. This aircraft has an aesthetically pleasing, intelligent and feasible design.

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Section: Aerodynamic Control Surfacesmentioning

confidence: 99%

Section: Total Parasite Dragmentioning

confidence: 99%

Design and Analysis of VTOL Operated Intercity Electrical Vehicle for Urban Air Mobility

et al. 2021

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“…The authors selected these as a first approximation to the problems because they can be modeled in a simple, but accurate enough, way in order to accomplish with the necessities of the conceptual design stages. The solution of the feasible design space for V-tail configurations taking into account these conditions has already been performed [24].…”

Section: Design Strategy and Reference Aircraftmentioning

confidence: 99%

“…However, some parameters need to be estimated. For instance, the maximum control deflections have been taken from Sanchez-Carmona and Cuerno-Rejado [24]; the percentage of chord that the controls take up is considered as 25%, according to the state of the art of other airplanes; and the airfoils for the tail surfaces selected are NACA 0012 in the case of the horizontal tailplane and NACA 0009 for the vertical tailplane. Once these tail parameters are known, it is possible to estimate the contributions of the tails to the zero-lift drag coefficient of the airplane.…”

Section: Design Strategy and Reference Aircraftmentioning

confidence: 99%

“…Thus, it is necessary to use design criteria based on the regulation in force to establish the feasible design for each tail configuration. A proposal of how to deal with the certification requirements to size an unconventional tail configuration has already been presented [24]. Thus, the next step is to analyze the impact of these novel tail configurations in weight and drag of the aircraft and, consequently, in fuel consumption and emissions of a given route.…”

Section: Introductionmentioning

confidence: 99%

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Design Process and Environmental Impact of Unconventional Tail Airliners

Sanchez-Carmona

Cuerno-Rejado

2021

Aerospace

Self Cite

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The future of aviation depends on reducing the environmental impact of the aircraft. Unconventional configurations can be the change the industry needs to achieve that goal. Therefore, the development of a tool that allows analyzing these configurations will contribute to their being considered more easily in future designs. This design procedure is based on an aerodynamic model and a weight methodology validated for unconventional tail designs. The load cases selected to size the structure were extracted from the certification regulations in force. In order to validate the methodology, the V-tail configuration was selected as a case study. The fuel savings reached with this tail configurations are around 0.7%, and the reduction in NOx emissions are even greater. Thus, the methodology has been validated and it can be easily adapted to other unconventional tail configurations.

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A CFD-Based Collaborative Approach for Box-Wing Aircraft Aerodynamic Assessment: The PARSIFAL Study Case

Abu Salem,

Palaia,

Carini

et al. 2023

Aerotec. Missili Spaz.

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This article presents a detailed aerodynamic investigation on a transport aircraft with a box-wing lifting system. The aerodynamic development of this configuration is presented through the description of the collaborative and multi-fidelity design approach that took place within PARSIFAL, an European project aiming to develop the box-wing configuration for a civil transonic aircraft. The article starts from an accurate description of the collaborative methodological framework employed and offers an overview of the development of the box-wing aerodynamics together with the highlight on its most significant characteristics and aerodynamic features identified. The design development is detailed step by step, with specific focus on the challenges faced, starting from the conceptual investigations up to the most advanced evaluations. Significant focus is given to the assessment of the aerodynamic performance in transonic flight for the box-wing lifting system, and to the design solutions provided to overcome issues related to this flight regime, such as drag rise and flow separation. In addition, the high-fidelity shape optimisation techniques employed in the advanced stage of the design process are detailed; these allow to define a final configuration with improved aerodynamic performance.

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Vee-tail conceptual design criteria for commercial transport aeroplanes

Cited by 12 publications

References 12 publications

Design and Analysis of VTOL Operated Intercity Electrical Vehicle for Urban Air Mobility

Design and Analysis of VTOL Operated Intercity Electrical Vehicle for Urban Air Mobility

Design Process and Environmental Impact of Unconventional Tail Airliners

A CFD-Based Collaborative Approach for Box-Wing Aircraft Aerodynamic Assessment: The PARSIFAL Study Case

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