Abstract
Drag reduction is significant research in aircraft design due to its effect on the cost of operation and carbon footprint reduction. Aircraft currently use conventional solid winglets to reduce the induced drag, adding extra structural weight. Fluidic on-demand winglets can effectively reduce drag for low-speed flight regimes without adding any extra weight. These utilize the spanwise airflow from the wingtips using hydraulic actuators to create jets that negate tip vortices. This study develops a computational model to investigate fluidic on-demand winglets. The well-validated computational model is applied to investigate the effect of injection velocity and angle on the aerodynamic coefficients of a rectangular wing. Further, the turbulence parameters such as turbulent kinetic energy (TKE) and turbulent dissipation rate are studied in detail at various velocity injections and at an angle of 30
Address
A. Mondal, S. Chatterjee, A. McDonald Tariang, L. Prince Raj and K. Debnath: Department of Aerospace Engineering and Applied Mechanics, Indian Institute of Engineering Science & Technology, Shibpur, Howrah 711103, India
Abstract
The present article focuses on the thermoelastic deformation behavior of inhomogeneous functionally graded metal/ceramic cylindrical shell structure with multiple perforations using 2D finite element approximation. Here, cylindrical shell structure is considered with single (1x1) and multiple (2x2, 3x3 and 4x4) perforations. The temperature-dependent elastic and thermal properties of functionally graded material are evaluated using Voigt's micromechanical material scheme via power-law function. The kinematics of the proposed model is based on the equivalent single-layer first-order shear deformation mid-plane theory with five degrees-of-freedom. Here, 2D isoparametric finite element solutions are obtained using eight-node quadrilateral elements. The mesh refinement of present finite element model is performed to confirm the appropriate number of elements and nodes for the analysis purpose. Subsequently, a comparison test is conducted to demonstrate the accuracy of present results. In later section, numerous numerical illustrations are demonstrated at different set of conditions by varying structural, material and loading parameters and that confirms the significance of various parameters such as power-law index, aspect ratio, thickness ratio, curvature ratio, number of perforations and temperature on the deformation characteristics of functionally graded cylindrical shell structure.
Key Words
2D-FEM; cylindrical; deformation; FGM; perforations; temperature-dependent; thermoelastic
Address
Shyam K. Chaudhary, Vishesh R. Kar: Department of Mechanical Engineering, National Institute of Technology Jamshedpur, 831014, India
Karunesh K. Shukla: Department of Civil Engineering, National Institute of Technology Jamshedpur, 831014, India
Abstract
In current research work, the aerodynamics performance of a newly designed large flying V aircraft is numerically investigated. Three Flying V configurations, with V-angles of 50o, 70o and 90o that represent the minimum, moderate, and maximum configurations respectively, were designed and modeled to assess their aerodynamic performance at cruise flight conditions. The unstructured mesh was developed using ICEM CFD and Ansys-Fluent was used as an aerodynamic solver. The developed models were numerically simulated at cruise flight conditions with a Mach number equal to 0.15. K-w SST turbulence model was chosen to account for flow turbulence. The authors performed steady flow simulations. The results obtained from the experimentation reveal that the maximum main angle configuration of 90o had the highest CLmax value of 0.46 compared to other configurations. While the drag coefficient remained the same for all three configurations, the 50o V-angle configuration achieved the maximum stall angle of 35o. With limited stall delay benefits, the flying V possesses no sufficient stability, due to the flow separation detected at whole elevon and winglet suction side areas at AoA equal and higher than 30o.
Address
Zahir Amine: Aerospace Engineer, Brussels, Belgium
Omer Elsayed: International University of Rabat, School of Aerospace Engineering, LERMA Lab., Campus UIR Parc Technopolis, Rocade, Rabat-Sale, 11100-Sala Al Jadida, Maroc
Abstract
In this paper we proposed the aerodynamic numerical analysis with linear matrix inequality theorem of
intelligent control, which is believed to be applicable in the application not only a function of the block size and
reduced wind speed but itself depends on both the size and the aspect ratio of the structure, not on the total scruton
number. In order to improve the accuracy of the results, the optimization curve was optimized for the test to evaluate
the response in the time of achieving the results and we focus on the results that found a significant influence from the
assumptions used for damage propagation for aircraft structural analysis of composite materials. Finally, the
numerical simulations confirmed the effectiveness of the method.
Address
C.C. Hung: Faculty of National Hsin Hua Senior High School, Tainan, Taiwan
T. Nguyễn: Ha Tinh University, Dai Nai Campus: No. 447, Street 26/3, Dai Nai Ward, Ha Tinh City, Vietnam
Abstract
This article presents a numerical analysis to investigate the natural frequencies and harmonic response of a perforated cantilever beam attached to two layers of piezoelectric materials by using the finite element method for the first time. The bimorph piezoelectric is composed of 3 layers; two of them at the outer are piezoelectric, and the inner isotropic material. A higher order 3-D 20-node solid element that exhibits quadratic displacement behavior is exploited to discretize the isotropic layer, and coupled piezoelectric 3D element with twenty nodes is used to mesh
the top and bottom layers. CIRCU94 element is added to act as a resistor part of the model. The proposed model is
validated with previous works. The numerical parametric studies are presented to illustrate the effects of perforation geometry, the number of rows, the resistance on the natural frequencies, frequency response, and power. It is found that the thickness has a positive relationship with the natural frequency. Perforations help in producing higher voltage, and the best shape is rectangular perforations, and to produce higher voltage, two rows of rectangular perforations should be applied.
Key Words
energy harvester; finite element analysis; perforated structures; piezoelectric bimorph
Address
Yousef A. Alessi, Ibrahim Ali, Mashhour A. Alazwari, Khalid Almitani: Mechanical Engineering Department, Faculty of Engineering, King Abdulaziz University, P.O. Box 80204, Jeddah 21589, Saudi Arabia
Alaa A Abdelrahman: Mechanical Design & Production Department, Faculty of Engineering, Zagazig University, P.O. Box 44519, Zagazig 44519, Egypt
Mohamed A. Eltaher: Mechanical Engineering Department, Faculty of Engineering, King Abdulaziz University, P.O. Box 80204, Jeddah 21589, Saudi Arabia; Mechanical Design & Production Department, Faculty of Engineering, Zagazig University, P.O. Box 44519, Zagazig 44519, Egypt
