Wing design is one of the most important tasks for a designer to overcome during an aircraft design process. Therefore, a designer need to optimize so many wing geometrical parameters with the aim of obtaining an efficient wing geometry complying with requirements of the design. Taper ratio is one of these parameters, which is the ratio of root and tip chord lengths of a wing. In this study, firstly, a high aspect ratio rectangular aircraft wing was numerically investigated in terms of some aerodynamic parameters including induced drag coefficient, Oswald efficiency factor and lift coefficient together with its span-wise distribution by means of XFLR5 computational fluid dynamics program. The assessment of mesh accuracy of the program was done at the beginning of the analyses. Later on, with the aim of observing the effects of taper ratio on aircraft wing aerodynamic parameters, the revised versions of the wing, which have the taper ratios from 0.2 to 1.2 (with the increment of 0.2) were analyzed. In conclusion, depending on the analyses results, the wings having different taper ratios were compared in terms of obtained aerodynamic parameters and span-wise lift distributions. Moreover, tip vortices of each wing, together with their sizes, were obtained and also compared.
In this study, a new algorithm has been developed for Design Optimization of composite plates using Tsai-Wu criteria. Von-Mises stress criteria is used as design variable for the stress based Design Optimization problems. It is used to understand the effect of combined stresses on the isotropic materials. However, Von-Mises stress analysis is not appropriate for anisotropic composite materials. To define the strength of composite materials, maximum stress, maximum strain, Azzi Tasi Hill and Tsai-Wu criterias are used. In this study, failure index was used as design criteria and Tsai-Wu criteria was used to calculate this value in the optimization algorithm. Topology optimization, which is used for mass and shape optimization on structures, is a design tool. In this study, a new algorithm has been developed for topology optimization of composite materials. By using this algorithm, common geometric models and different fiber angles have been investigated. Nearly 50% mass reduction have been obtained by using the developed algorithm.
Kanat tasarımı, tüm hava araçları için olduğu gibi, planörler için de aerodinamik performans açısından kritik öneme sahiptir. Aerodinamik olarak verimli bir planör kanadı tasarımının en önemli aşamalarından biri de uygun kanat kesit geometrisi (kanat profili) seçimidir. Bir kanat tasarımının kanat kesit geometrisi seçimi, öncelikle belirlenen gerekliliklere dayanarak karşılaştırmak üzere, farklı kanat kesit geometrilerinin aerodinamik performans analizlerini gerektirir. Bu çalışmada, dokuz farklı kanat kesit geometrisi planör aerodinamik performansı açısından karşılaştırmak üzere genel kamu lisanslı XFLR5 programı kullanılarak nümerik olarak incelenmiştir. Öncelikle karşılaştırılacak geometriler Eppler, Goettingen, NACA ve Wortmann kanat kesit geometrisi ailelerinden seçilmiştir. Karşılaştırma için programın deneysel verilerle iki boyutlu doğrulaması yapılmış ve seçilen kanat kesit geometrileri aynı koşullar altında analiz edilmiştir. Analizler 2x10 5 Reynolds sayısında ve-5 ile 20 derece arasındaki hücum açılarında gerçekleştirilmiştir. Analizlerden elde edilen sonuçlara göre kanat kesit geometrileri belirlenen gereklilikler olan kalınlık, maksimum kaldırma katsayısı ve hücum açısı, maksimum kaldırma durumundaki sürüklenme katsayısı, maksimum süzülme oranı, sıfır kaldırma durumundaki yunuslama momenti ve güç faktörüne göre karşılaştırılmıştır.
In design stage, weight-strength balance is the most important factor to obtain minimum weight value. Try and error method is used to obtain this balance in the conventional design applications. In the last decades, topology optimization methods are used to calculate this balance. The main objective of topology optimization is to obtain strong and lightweight parts with the same characteristics as well as to reduce the amount of material in the parts. Weight of the vehicles is one of the main effective parameters in terms of fuel consumption for the structural engineering applications. Vehicles are subjected to weight load, brake load and centrifugal load when driving mode. Hence, within this study, topology optimization of truck chassis was investigated under the these loading conditions. ANSYS workbench program was used to perform the proposed study. Deformation and stress values of the chassis were investigated. Optimized model was compared with the conventional model. As a result of the study, nearly 14% mass reduction was obtained without exceed permissible stress values.
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