Optimization of planform and cruise conditions of a transport flying wing

Martínez‐Val, Rodrigo; Pérez, Emilio Ortega; Puertas, Jerónimo; Roa, Javier

doi:10.1243/09544100jaero812

Cited by 16 publications

(12 citation statements)

References 16 publications

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“…Actually, for each one of the cases, the pitch angle has opposite signs, whose understanding is justified by the definition of the outer product. Thus, in order to obtain a steering center, the pitch angle must be entirely expressed by equation (8).…”

Section: Mechanism and Blade Position Controlmentioning

confidence: 99%

“…The rotor defined in Table 1 is used to test equation (8). Here, equation (4) is used concurrently in order to counter check equation (8).…”

Section: Mechanism and Blade Position Controlmentioning

confidence: 99%

“…Here, equation (4) is used concurrently in order to counter check equation (8). Let us assume that the pivot point is at 25% from the leading edge, and that the considered phase angle of eccentricity is 45 .…”

Section: Mechanism and Blade Position Controlmentioning

confidence: 99%

“…However, Figure 7 comes up with the slope that the blades would have to assume so that the blades path is a pure cycloidal motion. As previously said, it is got by using equation (8). It is geometrically visible that for all possible dimensions, for the selected mechanical control system one cannot obtain a pure cycloidal motion.…”

Section: Mechanism and Blade Position Controlmentioning

confidence: 99%

“…[5][6][7] The figure-of-merit is a parameter often used as efficiency metric for helicopter rotors and for the optimization study of flying wings. 8 In the case of cyclorotors, this parameter has also been used as a way of measuring efficiency. Several authors have performed research on the efficiency of cyclorotors.…”

Section: Introductionmentioning

confidence: 99%

See 4 more Smart Citations

Analytical modeling of a cyclorotor in hovering state

Leger

Páscoa

Xisto

2015

Proceedings of the Institution of Mechanical Engineers, Part G:

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In the paper it is proposed and described in detail a mathematical model that is able to assist in the design of cycloidal rotors. The method is formulated on a semi-empirical way including unsteady aerodynamic effects that are based on first principles. It is able to predict the overall generated thrust and the power required by the operation of the cycloidal rotor. The model also includes a kinematic package that can provide an instantaneous design and animation of the cycloidal rotor under different regimes of operation. For validation it was addressed three different rotor configurations where it was varied several rotor parameters, namely: pitch amplitude; pitching axis location; blade chord; airfoil thickness; phase angle of eccentricity. It was shown that the proposed model is able to provide a good estimation of thrust and power when compared with the experimental data from these different sources, showing that the semi-empirical approach could be applied in a more general way.

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Section: Mechanism and Blade Position Controlmentioning

confidence: 99%

“…The rotor defined in Table 1 is used to test equation (8). Here, equation (4) is used concurrently in order to counter check equation (8).…”

Section: Mechanism and Blade Position Controlmentioning

confidence: 99%

Section: Mechanism and Blade Position Controlmentioning

confidence: 99%

Section: Mechanism and Blade Position Controlmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Analytical modeling of a cyclorotor in hovering state

Leger

Páscoa

Xisto

2015

Proceedings of the Institution of Mechanical Engineers, Part G:

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Fuel consumption optimization in air transport: a review, classification, critique, simple meta-analysis, and future research implications

Singh

Sharma

2015

Eur. Transp. Res. Rev.

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Objective This paper presents a review, classification schemes, critique, a simple meta-analysis and future research implication of fuel consumption optimization (FCO) literature in the air transport sector. This review is based on 277 articles published in various publication outlets between 1973 and 2014. Methodology A review of 277 articles related to the FCO in air transport was carried out. It provides an academic database of literature between the periods of 1973-2014 covering 69 journals and proposes a classification scheme to classify the articles. Twelve hundred of articles were identified and reviewed for their direct relevance to the FCO in air transport. Two hundred seventy seven articles were subsequently selected, reviewed and classified. Each of the 277 selected articles was categorized on four FCO dimensions (Aircraft technology & design, aviation operations & infrastructure, socioeconomic & policy measures, and alternate fuels & fuel properties). The articles were further classified into six categories of FCO research methodologies (analytical -conceptual, mathematical, statistical, and empirical-experimental, statistical, and case studies) and optimization techniques (linear programming, mixed integer programming, dynamic programming, gradient based algorithms, simulation modeling, and nature based algorithms). In addition, a simple meta-analysis was also carried out to enhance understanding of the development and evolution of research in the FCO. Findings and conclusions This has resulted in the identification of 277 articles from 69 journals by year of publication, journal, and topic area based on the two classification schemes related to FCO research, published between, 1973 to December-2014. In addition, the study has identified the 4 dimensions and 98 decision variables affecting the fuel consumption. Also, this study has explained the six categories of FCO research methodologies (analytical -conceptual, mathematical, statistical, and empirical-experimental, statistical, and case studies) and optimization techniques (linear programming, mixed integer programming, dynamic programming, gradient based algorithms, simulation modeling, and nature based algorithms). The findings of this study indicate that the analytical-mathematical research methodologies represent the 47 % of FCO research. The results show that there is an increasing trend in research of the FCO. It is observed that the number of published articles between the period 1973 and 2000 is less (90 articles), so we can say that there are 187 articles which appeared in various journals and other publication sources in the area of FCO since 2000. Furthermore there is increased trend in research on FCO from 2000 onward. This is due to the fact that continuously new researchers are commencing their research activities in FCO research. This shows clearly that FCO research is a current research area among many research groups across the world. Lastly, the prices of jet fuel have significantly increased since the 2005. The aviatio...

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Study on a Rapid Aerodynamic Optimization Method of Flying Wing Aircraft for Conceptual Design

Wei

Huang

Song

2022

International Journal of Aerospace Engineering

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Searching for a design scheme satisfying the requirements in aircraft conceptual design can be a time-consuming work because of the multipeak and nonlinearity of the design space. This paper proposed a rapid aerodynamic optimization method for flying wing aircraft conceptual design. This method is aimed at reducing the induced drag at the design point by adjusting the camber and twist angle of spanwise airfoil. Firstly, the mean camber surface of the flying wing aircraft was parameterized. Secondly, the surrogate model was constructed based on the points selected by the optimization Latin square method. Thirdly, the surrogate model combined with a multi-island genetic algorithm was used for the preliminary solution of global optimum, and then, the Nonlinear Programming by Quadratic Lagrangian method combined with a vortex lattice method was used for searching the nearest exact best point from the initial best point. Finally, connecting with manual selection, the optimized flying wing layout scheme was obtained. The optimized results show that the induced drag coefficient is reduced by 10%, the pitching moment coefficient is reduced by an order of magnitude, and the lift drag ratio is increased from 26.3 to 27.3. The proposed optimization method decreases the time cost in aircraft conceptual design while achieving sufficient calculation accuracy. By using this method, the design space can be explored rapidly to search for the best design scheme satisfying the constraints.

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Optimization of planform and cruise conditions of a transport flying wing

Cited by 16 publications

References 16 publications

Analytical modeling of a cyclorotor in hovering state

Analytical modeling of a cyclorotor in hovering state

Fuel consumption optimization in air transport: a review, classification, critique, simple meta-analysis, and future research implications

Study on a Rapid Aerodynamic Optimization Method of Flying Wing Aircraft for Conceptual Design

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