The Experts below are selected from a list of 42 Experts worldwide ranked by ideXlab platform
Jean-yves J.-y. Trépanier - One of the best experts on this subject based on the ideXlab platform.
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Conceptual design, performance and stability analysis of a 200 passengers Blended Wing Body Aircraft
Aerospace Science and Technology, 2017Co-Authors: Sami Ammar, Jean-yves J.-y. Trépanier, Clément LegrosAbstract:The Blended Wing Body (BWB) is a type of innovative Aircraft, based on the flying wing concept. For this Aircraft, the literature has reported performance improvements compared to conventional Aircraft: economy of fuel, reduction of the weight of the structure, increased payload capacity and less impact on the environment. However, most BWB studies have focused on large Aircraft and it is not sure whether the gains are the same for smaller Aircraft. The main objective of this study is to perform the conceptual design of a 200 passengers BWB and compare its performance against an equivalent conventional A320 Aircraft in terms of payload and range. Moreover, an emphasis will be placed on obtaining a Stable Aircraft, with the analysis of static and dynamic stability over its flight envelope. This kind of Aircraft has a lack of stability due to the absence of vertical tail. Most studies of stability were already realized on reduced size models of BWB, but there is no study on a 200 passengers BWB. The design of the BWB was realized with the platform called Computerized Environment for Aircraft Synthesis and Integrated Optimization Methods (CEASIOM). The airplane, the engines and the control surfaces were obtained in the geometrical module AcBuilder. This design platform, suitable for conventional Aircraft design, has been modified and additional tools have been integrated in order to achieve the aerodynamic, performance and stability analysis of the BWB Aircraft. The aerodynamic coefficients are calculated from Tornado program. The BWB flight envelope was created based on aeronautical data of A320 Aircraft. From this flight envelope, we have got back several thousand possible points of flight. The static and dynamic stability was studied using the longitudinal and lateral matrices of stability and the Flying Qualities Requirements for every flight point.
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Conceptual Design of a 200 Passenger Blended Wing Body Aircraft
ASME International Mechanical Engineering Congress and Exposition 2014, 2014Co-Authors: Sami Ammar, Jean-yves J.-y. TrépanierAbstract:The Blended Wing Body (BWB) Aircraft is based on the flying wing concept. For this Aircraft the literature has reported performance improvements compared to conventional Aircraft. However, most BWB studies have focused on large Aircraft and it is not sure whether the gains are the same for smaller Aircraft. The main objective of this work is to perform the conceptual design of a 200 passengers BWB and compare its performance against an equivalent conventional A320 Aircraft in terms of payload and range. Moreover, an emphasis will be placed on obtaining a Stable Aircraft, with the analysis of static and dynamic stability. The design of BWB was carried out under the platform called Computerized Environment for Aircraft Synthesis and Integrated Optimization Methods (CEASIOM). This design platform, suitable for conventional Aircraft design, has been modified and additional tools have been integrated in order to achieve the aerodynamic analysis, performance and stability of the BWB Aircraft.
Sami Ammar - One of the best experts on this subject based on the ideXlab platform.
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Conceptual design, performance and stability analysis of a 200 passengers Blended Wing Body Aircraft
Aerospace Science and Technology, 2017Co-Authors: Sami Ammar, Jean-yves J.-y. Trépanier, Clément LegrosAbstract:The Blended Wing Body (BWB) is a type of innovative Aircraft, based on the flying wing concept. For this Aircraft, the literature has reported performance improvements compared to conventional Aircraft: economy of fuel, reduction of the weight of the structure, increased payload capacity and less impact on the environment. However, most BWB studies have focused on large Aircraft and it is not sure whether the gains are the same for smaller Aircraft. The main objective of this study is to perform the conceptual design of a 200 passengers BWB and compare its performance against an equivalent conventional A320 Aircraft in terms of payload and range. Moreover, an emphasis will be placed on obtaining a Stable Aircraft, with the analysis of static and dynamic stability over its flight envelope. This kind of Aircraft has a lack of stability due to the absence of vertical tail. Most studies of stability were already realized on reduced size models of BWB, but there is no study on a 200 passengers BWB. The design of the BWB was realized with the platform called Computerized Environment for Aircraft Synthesis and Integrated Optimization Methods (CEASIOM). The airplane, the engines and the control surfaces were obtained in the geometrical module AcBuilder. This design platform, suitable for conventional Aircraft design, has been modified and additional tools have been integrated in order to achieve the aerodynamic, performance and stability analysis of the BWB Aircraft. The aerodynamic coefficients are calculated from Tornado program. The BWB flight envelope was created based on aeronautical data of A320 Aircraft. From this flight envelope, we have got back several thousand possible points of flight. The static and dynamic stability was studied using the longitudinal and lateral matrices of stability and the Flying Qualities Requirements for every flight point.
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Conceptual Design of a 200 Passenger Blended Wing Body Aircraft
ASME International Mechanical Engineering Congress and Exposition 2014, 2014Co-Authors: Sami Ammar, Jean-yves J.-y. TrépanierAbstract:The Blended Wing Body (BWB) Aircraft is based on the flying wing concept. For this Aircraft the literature has reported performance improvements compared to conventional Aircraft. However, most BWB studies have focused on large Aircraft and it is not sure whether the gains are the same for smaller Aircraft. The main objective of this work is to perform the conceptual design of a 200 passengers BWB and compare its performance against an equivalent conventional A320 Aircraft in terms of payload and range. Moreover, an emphasis will be placed on obtaining a Stable Aircraft, with the analysis of static and dynamic stability. The design of BWB was carried out under the platform called Computerized Environment for Aircraft Synthesis and Integrated Optimization Methods (CEASIOM). This design platform, suitable for conventional Aircraft design, has been modified and additional tools have been integrated in order to achieve the aerodynamic analysis, performance and stability of the BWB Aircraft.
R. Hageman - One of the best experts on this subject based on the ideXlab platform.
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Rudder Incorporated Winglet Design for Blended Wing Body Aircraft
2016Co-Authors: R. HagemanAbstract:Concern about the environmental footprint of aviation has re-sparked the interest in unconventional configurations, such as the blended wing body Aircraft, BWB. While most research studies recognize the potential of the hybrid-body, they also list a number of challenges. Amongst these challenges is the need for adequate lateral-directional stability and control, which is complicated due to the concept's relative short moment arm and limited available control-volume. To refrain from further straining the trailing edge for directional control, most BWB employ either a conventional vertical tail or resort to yaw-control incorporated winglets. By combining the functionality of the vertical fin with the aerodynamic benefits of a winglet, the required control surface could be obtained without the drag penalty associated with a vertical tail. Although a number of BWB, such as the X-48B, operate these active winglets, limited information is available on the design of such a non-planar component and its influence on the stability and control characteristics. The presented research investigates these aspects aiming to provide a better understanding of the influence of the individual winglet design variables. A design methodology was devised that implements a first order panel method connected to a virtual flight test program. The information collected from the analysis of 400 configurations was used to construct response surfaces that span the entire design space. The generated winglet design program also monitors the impact of the non-planar component on the aerodynamic performance, weight, and operating cost. This enables the user to optimize the tip device, given specified stability and control requirements. It was found that implementing yaw-control incorporated winglets resulted in a statically Stable Aircraft that meets the requirements for crosswind landing. However, none of the tested configurations meet the dutch roll frequency criterion, corresponding to a satisfactory handling quality level. Research indicates that the tip device has little influence on ωdr, indicating the need to modify the baseline Aircraft. Analysis of the response surface estimates for the asymmetric eigenmodes yields a significantly large average error and standard deviation for the spiral. Therefore, it is omitted from the study. Similar errors can be found for a number of other parameters. These parameters can generally be characterized by values that approach zero. The error and standard deviation is amplified when the parameter also changes sign. Normalization of these stability and control characteristics had little influence on the accuracy of the response surface. In recognition of the demonstrated inability of the response surface to accurately capture the behaviour of these parameters, it is concluded that further research is required to reduce the error of the estimates. Despite the indicated challenges, the system is able to explore various control surface configurations. This provides valuable insight into the behaviour of the stability and control characteristics and takes the first step towards the generation of less computational intensive models.
Zoltan Spakovszky - One of the best experts on this subject based on the ideXlab platform.
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Stability of Hybrid-Wing-Body-Type Aircraft with Centerbody Leading-Edge Carving
Journal of Aircraft, 2010Co-Authors: M. A. Sargeant, Tom Hynes, Wr Graham, James I. Hileman, M. Drela, Zoltan SpakovszkyAbstract:The silent-Aircraft experimental Aircraft are balanced by generating lift near the Aircraft nose through leading-edge carving of the centerbody. The use of leading-edge carving over the centerbody is novel, in that previous blended-wing-body Aircraft have balanced the Aircraft by downloading the centerbody (via reflex camber) to achieve the effect of a tail. This paper decomposes the aerodynamic forces into contributions from spanwise sections to explain how three-dimensional flow effects are beneficial in allowing the silent-Aircraft experimental Aircraft to be both statically Stable and to have an elliptical lift distribution over a large range of angles of attack. By analyzing the results in this manner, rationale is also given as to why, unlike other blended-wing-body-type configurations, the silent-Aircraft-experimental design can use supercritical unStable-outer-wing airfoil profiles to generate a balanced and Stable Aircraft. The results are then used to develop a methodology to aid the Aircraft designer in determining the amount of leading-edge carving that is necessary to achieve static stability for blended-wing-body-type Aircraft.
Clément Legros - One of the best experts on this subject based on the ideXlab platform.
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Conceptual design, performance and stability analysis of a 200 passengers Blended Wing Body Aircraft
Aerospace Science and Technology, 2017Co-Authors: Sami Ammar, Jean-yves J.-y. Trépanier, Clément LegrosAbstract:The Blended Wing Body (BWB) is a type of innovative Aircraft, based on the flying wing concept. For this Aircraft, the literature has reported performance improvements compared to conventional Aircraft: economy of fuel, reduction of the weight of the structure, increased payload capacity and less impact on the environment. However, most BWB studies have focused on large Aircraft and it is not sure whether the gains are the same for smaller Aircraft. The main objective of this study is to perform the conceptual design of a 200 passengers BWB and compare its performance against an equivalent conventional A320 Aircraft in terms of payload and range. Moreover, an emphasis will be placed on obtaining a Stable Aircraft, with the analysis of static and dynamic stability over its flight envelope. This kind of Aircraft has a lack of stability due to the absence of vertical tail. Most studies of stability were already realized on reduced size models of BWB, but there is no study on a 200 passengers BWB. The design of the BWB was realized with the platform called Computerized Environment for Aircraft Synthesis and Integrated Optimization Methods (CEASIOM). The airplane, the engines and the control surfaces were obtained in the geometrical module AcBuilder. This design platform, suitable for conventional Aircraft design, has been modified and additional tools have been integrated in order to achieve the aerodynamic, performance and stability analysis of the BWB Aircraft. The aerodynamic coefficients are calculated from Tornado program. The BWB flight envelope was created based on aeronautical data of A320 Aircraft. From this flight envelope, we have got back several thousand possible points of flight. The static and dynamic stability was studied using the longitudinal and lateral matrices of stability and the Flying Qualities Requirements for every flight point.