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The effect of winglet on wing performance / Eslam Mansour Mohamed Abo Seria ; Supervised Mohamed Madbouli Abdelrahman

By: Contributor(s): Material type: TextTextLanguage: English Publication details: Cairo : Eslam Mansour Mohamed Aboseria , 2016Description: 70 P. : facsimiles ; 30cmOther title:
  • تأثير الجنيحات الجانبية على أداء الجناح [Added title page title]
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  • Issued also as CD
Dissertation note: Thesis (M.Sc.) - Cairo University - Faculty of Engineering - Department of Aerospace Engineering Summary: This work aims to increase wing aerodynamic performance by reducing the induced drag by using the winglet, hence increase airplane range. This is done by study the effect of different winglet geometric parameters on wing aerodynamic performance. Then generate the optimum winglet which gives maximum lift to drag ratio. To reach this, two optimization and parametric studies on four geometric parameters of winglet were conducted. The first was low fidelity using Matlab code to solve potential flow, and the second was high fidelity using commercial code ANSYS Fluent to solve real flow. The low fidelity optimization was used to provide an initial guess to start the high fidelity optimization from it. The winglet four geometric parameters are: the cant angle, the sitting angle, the sweep back angle, and the tapered ratio
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Item type Current library Home library Call number Copy number Status Date due Barcode
Thesis Thesis قاعة الرسائل الجامعية - الدور الاول المكتبة المركزبة الجديدة - جامعة القاهرة Cai01.13.01.M.Sc.2016.Es.E (Browse shelf(Opens below)) Not for loan 01010110071074000
CD - Rom CD - Rom مخـــزن الرســائل الجـــامعية - البدروم المكتبة المركزبة الجديدة - جامعة القاهرة Cai01.13.01.M.Sc.2016.Es.E (Browse shelf(Opens below)) 71074.CD Not for loan 01020110071074000

Thesis (M.Sc.) - Cairo University - Faculty of Engineering - Department of Aerospace Engineering

This work aims to increase wing aerodynamic performance by reducing the induced drag by using the winglet, hence increase airplane range. This is done by study the effect of different winglet geometric parameters on wing aerodynamic performance. Then generate the optimum winglet which gives maximum lift to drag ratio. To reach this, two optimization and parametric studies on four geometric parameters of winglet were conducted. The first was low fidelity using Matlab code to solve potential flow, and the second was high fidelity using commercial code ANSYS Fluent to solve real flow. The low fidelity optimization was used to provide an initial guess to start the high fidelity optimization from it. The winglet four geometric parameters are: the cant angle, the sitting angle, the sweep back angle, and the tapered ratio

Issued also as CD

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