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Aircraft Delay Maneuvers Crossword
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Received: November 20, 2021 / Reviewed: December 30, 2021 / Accepted: January 7, 2022 / Published: January 12, 2022
Taking into account the current needs of green aviation, this study focuses on a new concept of Box Wing Aircraft (BWA). Branded as SmartLiner (BWA/SL), this aircraft concept comes as a triplane with forward and aft wings. The aerodynamic performance and structural characteristics of this BWA/SL aircraft are explored here through numerical simulations, using Computational Fluid Dynamics (CFD) and Fluid-Structure Interaction (FSI). The computational approach is first validated using NASA's Common Research Model (CRM) aircraft, which is then taken as a reference solution to compare the aerostructural characteristics of the BWA/SL concept. The results show that, although its design is still preliminary and needs optimization, the BWA/SL aircraft presents a very decent aerodynamic performance, with high lift capacity and a reasonable lift-drag ratio. In addition, thanks to its specially designed closed structure, it has high structural properties, even in extreme load scenarios. Based on this preliminary analysis and considering the space left for further improvements, this aircraft concept thus emerges as a potentially promising alternative for the development of more environmentally friendly aircraft.
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Modern air transport currently faces many challenges, including the need to reduce its environmental impact. In particular, pollution emissions are the main obstacle to a sustainable future for air transport, the constant growth (+5% per year) which also raises environmental concerns worldwide. One way to reduce pollutant emissions involved in air transport is to optimize aircraft design to maximize its transport capacity and minimize fuel consumption. This can be achieved by increasing the aircraft's lift capacity (thus increasing its payload) and reducing its drag penalty (thus reducing the power required on the aircraft). In other words, one way forward is to further improve the aerodynamic performance of aircraft by increasing their lift-to-drag (L/D) ratio. Research efforts in this area are very active worldwide, and proposed solutions range from simple or conservative (e.g. passive flow control using vortex generators) to more complex or advanced (e.g. new aircraft and/or plant architecture).
With regard to new aircraft configurations and with other modalities (for example, flying wing [1], support wing aircraft [2]), one can describe the concept of Box-Wing aircraft (BWA) [ 3] (see Figure 1) . Based on the first works of L. Blériot and G. Voisin [4, 5] (1906), this concept was later rationalized by the theory of Prandtl-Minck [6, 7], according to which an aircraft with a closed wing system should be together They offer better aerodynamic performance than traditional 'tube and wing' configurations. In fact, unlike a conventional aircraft whose lift is generated by a single wing, a box-wing aircraft has several airfoils (the wing, but also the horizontal tail) that are connected to each other, pulling with these connections. wing tip vortices. The benefits are expected to be manifold, namely (i) more lift generated (i.e. more allowable payload and/or smaller required wingspan), (ii) less induced drag generated (i.e. less included fuel consumption) and then (iii) greater structural integrity (ie less weight than structural strength) – all of which will eventually lead to better performance and therefore lower emissions.
The last decade has seen active research on box-wing aircraft around the world. One can refer to the concept of BWA currently being explored by Lockheed Martin (see Figure 1) under NASA's Environmentally Responsible Aviation Project (ERAP) initiative [8]. The proposed concept advantageously combines box wing design, advanced lightweight composite materials and highly efficient engines (with a bypass rate approximately five times higher than existing engines). It is claimed that this BWA aircraft will offer a 16% higher lift-to-drag ratio than a conventional aircraft, along with lower noise emissions. Several large-scale projects carried out under the auspices of the European Commission can also be mentioned, namely PARSIFAL [9, 10, 11, 12, 13, 14, 15, 16, 17] and IDINTOS [18, 19]. In particular, the recent EU project PARSIFAL extensively explored the concept of the so-called Prandtal plan, which was investigated from different angles, including the market perspective [9], the conceptual design perspective [10, 11, 12 ] and more techniques. aspects (eg performance [13], stability [14], aerodynamics [15, 16], structure [17]). In addition, more specific studies have been conducted by several universities around the world; Several works investigated the BWA concept from a design point of view [20, 21, 22, 23, 24, 25, 26, 27] while others focused on more specific things, such as the aerodynamic performance of the box wing itself [28, 29 , 30], 31, 32, 33, 34], as well as structural [35, 36] and stability [37, 38, 39, 40] aspects.
All these initial studies gave rise to the possible emergence of the era of BWA planes. That said, there are still many places to be explored to further strengthen and improve the concept of such an unconventional aircraft. Also, these early conceptual days are the perfect time period to think more outside the box (-wing), for example, exploring even more radical BWA concepts. This is what led to the recent development of a new box-wing aircraft concept, later referred to as the SmartLiner (SL). Originally designed by the present third author, this new concept (currently pending patent approval) takes the form of a triplane consisting of wings swept back and swept forward (see Figure 2). The main driver behind this concept is based on Prandlt's idea [6, 7] that a triplane with the same lift (or wingspan) should exhibit less induced drag than a biplane [41, 42]. Compared to a normal BWA (biplane), the current BWA/SL concept consists of an additional intermediate wing, which is connected to the other two. This new design is expected to provide better aerostructural characteristics than typical Prandlt (two-wing) aircraft, thanks to (i) its much stiffer closed frame structure, (ii) its increased lift areas, and (iii) its expected low drag induction associated with wingtips. Furthermore, thanks to its larger lift area, this BWA/SL concept can accommodate a low wingspan, thus allowing for a design based on high proportion thin wings. In turn, this will allow designing wings using laminar flow airfoils, thus increasing their aerodynamic performance. This particular model forms a new subclass within the BWA family, which includes conventional wing boxes, articulated wings, ring wings, etc. Needless to say, however, BWA raises even more questions than such a destructive concept. A typical two-wing BWA, whether in terms of commercial exploitation, aerodynamic performance, structural performance, stability and control characteristics, etc. As a first step in evaluating the BWA/SL aircraft concept, its aerodynamic qualities were here. Studies using computational methods. The results are summarized in this article, which is organized as follows: Section 2 presents the computational method used throughout the study, which is Computational Fluid Dynamics (CFD) and Fluid-Structure Interaction (FSI). In Section 3, the computational approach is applied for the first time to a classic aircraft, namely the NASA Common Research Model (CRM) configuration, thus providing method validation and a reference solution compared to the BWA/ SL.The concept must be compared. The latter is explored quantitatively against its CRM counterpart in Section 4, before conclusions and perspectives are drawn in Section 5.
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Whether it is the reference plane (CRM) or BWA (SL), the numerical investigation is carried out using the same computational strategy and tools; Aerodynamic performance is investigated for the first time using a computational fluid dynamics (CFD) method based on a stable Reynolds mean Navier-Stokes (RANS) method. Structural properties are then explored using fluid-structure interaction (FSI) simulations, which depend on the obtained CFD results.
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