High-Lift Wing Design in Consideration of Sweep Angle Effect Using Kriging Model

2008 ◽  
Author(s):  
Masahiro Kanazaki ◽  
Taro Imamura ◽  
Shinkyu Jeong ◽  
Kazuomi Yamamoto
Keyword(s):  
Kriging Model ◽  
Wing Design ◽  
Sweep Angle ◽  
High Lift ◽  
Angle Effect

Esso Energy Award Lecture, 1987 - Application of aerodynamic research and development to civil aircraft wing design

1988 ◽  
Vol 416 (1850) ◽  
pp. 43-62
Keyword(s):  
Technological Progress ◽  
Computational Fluid Mechanics ◽  
Aerodynamic Design ◽  
Wing Design ◽  
High Lift ◽  
Business Jet ◽  
Civil Aircraft ◽  
Research Programmes ◽  
The Government

In the late 1950s the aerodynamicists at what is now the Hatfield site of British Aerospace accepted the challenge and met British European Airways’ demand for a 600 m. p. h. ( ca . 966 km h -1 ) short-haul jet airliner (the Trident). The experience and organization resulting from that project was the cornerstone on which the subsequent success story of civil wing design has been built. The substantial advances in efficiency achieved by the Hatfield team in the following designs for the 125 Business Jet, the 146 Feederliner and for the Airbus Industrie family of Wide-Body Mainline aircraft, has been supported by research programmes in the government establishments and universities as well as industry itself. Each project had its individual demands for fuel economy, high lift capability and structural efficiency, with commercial competition continually driving technological progress. The major highlights and achievements of the aerodynamic development programmes for these projects are reviewed. Turning to the present, the Hatfield team are currently working on the aerodynamic design for the combined Airbus A330/340 project. Technological progress continues apace with major investment in computational fluid mechanics, but the still essential role of experimental test techniques and facilities is emphasized.

A computational fluid dynamics investigation of subsonic wing designs for unmanned aerial vehicle application

2019 ◽  
Vol 233 (15) ◽  
pp. 5543-5552
Author(s):  
Z Siddiqi ◽  
JW Lee
Keyword(s):  
Fluid Dynamics ◽  
Computational Fluid Dynamics ◽  
Aspect Ratio ◽  
Unmanned Aerial Vehicle ◽  
Wing Design ◽  
Ansys Fluent ◽  
High Lift ◽  
Aerial Vehicle ◽  
Computational Fluid Dynamics Simulations ◽  
Dynamics Simulations

The wing of an unmanned aerial vehicle, RQ-7 Shadow, is modified to study the changes in the aerodynamics of the wing. The main focus is to investigate the effects of changing the components of wing design when the aircraft climbs and accelerates. These component modifications included changing the airfoil, planform, aspect ratio, and adding a winglet. Another objective is to study the efficacy of employing high-lift airfoils like the EPPLER 559 for subsonic unmanned aerial vehicle applications. For this, five wing designs are considered in this paper. Computational fluid dynamics simulations using ANSYS FLUENT® are conducted for each wing design. The C L /C D ratios for all the wings are calculated at increasing angles of attack (simulating Climbing) and increasing speed (simulating Acceleration). Compared to the NACA 4415 airfoil, which is utilized by the RQ-7 Shadow, the EPPLER 559 provides an increase in lift at the low angles of attack, but yields less of these benefits as the angle of attack increases. The tapered planform significantly reduces the high drag associated with the EPPLER 559 airfoil. The generation of higher lift forces with lower drag is further achieved by increasing the aspect ratio and through the addition of a winglet. When compared to the NACA 4415 airfoil, it is concluded that the EPPLER 559 airfoil is a viable candidate for subsonic unmanned aerial vehicle applications only when the components of wing design are altered. The performance of the wings that employ the EPPLER 559 airfoil improves when the planform is changed from rectangular to tapered, when the aspect ratio is increased and when a winglet is added.

Experimental and numerical investigation of the leading edge sweep angle effect on the performance of a delta blades hydrokinetic turbine

2020 ◽  
Vol 162 ◽  
pp. 1087-1103
Author(s):  
Mabrouk Mosbahi ◽  
Ahmed Ayadi ◽  
Youssef Chouaibi ◽  
Zied Driss ◽  
Tullio Tucciarelli
Keyword(s):  
Numerical Investigation ◽  
Leading Edge ◽  
Sweep Angle ◽  
Hydrokinetic Turbine ◽  
Angle Effect

scholarly journals Multi-Objective Aerodynamic Exploration of Elements’ Setting for High-Lift Airfoil Using Kriging Model

2006 ◽  
Vol 54 (632) ◽  
pp. 419-426 ◽  
Author(s):  
Masahiro Kanazaki ◽  
Shinkyu Jeong ◽  
Kentaro Tanaka ◽  
Kazuomi Yamamoto
Keyword(s):  
Kriging Model ◽  
High Lift ◽  
Multi Objective

scholarly journals Design Exploration of High-Lift Airfoil Using Kriging Model and Data Mining Technique

2007 ◽  
Vol 8 (2) ◽  
pp. 28-36 ◽  
Author(s):  
Masahiro Kanazaki ◽  
Kazuomi Yamamoto ◽  
Kentaro Tanaka ◽  
Shin-Kyu Jeong
Keyword(s):  
Data Mining ◽  
Kriging Model ◽  
Data Mining Technique ◽  
High Lift ◽  
Design Exploration ◽  
Mining Technique

scholarly journals АНАЛІЗ СИЛ ФУНКЦІОНУВАННЯ ВІД’ЄМНОЇ ЧАСТИНИ КРИЛА ЛІТАКА ТРАНСПОРТНОЇ КАТЕГОРІЇ

2021 ◽  
pp. 4-20
Author(s):  
А. Г. Гребеников ◽  
Д. Ю. Жиряков
Keyword(s):  
Fatigue Life ◽  
Strain State ◽  
Integrated Design ◽  
Complex Stressed State ◽  
Design Element ◽  
Structural Elements ◽  
Wing Design ◽  
Stress Strain ◽  
High Lift ◽  
Stress Strain State

Each experimental design department has experience in determining design and operational loads for a given type of aircraft. The reliability of the data on the loading of a particular structural element determines the success of the aircraft being created. This is often confidential information. Much work has been investigated to improve the fatigue life of wing structural elements. With the development of integrated design methods, aircraft structure design can be performed in the shortest time, and with high technical excellence. In most cases, the fatigue life of wing elements is determined from the nominal stresses in the element. For a longitudinal structure set, it is customary to perform fatigue calculations directly using normal stresses in the element. For a more detailed specification of the fatigue life, it is necessary to have a general and local stress-strain state of a given structure. A feature of the work is to analyze the spectrum of loads acting on the wing console during a typical flight. The influence of high-lift devises (slats, flaps) on the shear forces and torque moment of the wing was analyzed. It has been shown that with the extensions high-lift devices, there is a significant increase in torque. These articles will make it possible to obtain the stress distribution of the detachable part of the wing under all operating modes. This, in turn, leads to a more thorough prediction of fatigue life. Since some operating loads can significantly change the distribution of the stress-strain state in the design element, and in turn change the fatigue life. The structural elements of the wing, in particular the attachment points for the high-lift devices, operate in a complex-stressed state. This complicates the process of predicting the fatigue life of these elements. To obtain a competitive aircraft, it is necessary to develop new methods of wing design with widespread use of integrated systems. This will contribute to obtaining a more optimal and perfect wing design

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