Estimation of load and pressure distribution on low speed aircraft wing with wake rollup

مقدم أطروحة جامعية

Hadi, Basil Mahdi

الجامعة

الجامعة التكنولوجية

الكلية

-

القسم الأكاديمي

قسم الهندسة الكهروميكانيكية

دولة الجامعة

العراق

الدرجة العلمية

ماجستير

تاريخ الدرجة العلمية

2004

الملخص الإنجليزي

An analytic method for estimation of load and pressure distributions on low speed wings with flow separation and wake rollup is developed in this study.

The method is a combination of several approaches.

A higher order vortex panel method is coupled with the numerical lifting line theory by means of a special iterative procedure including a model of separation and a model of wake rollup.

The mutual influences of various flow regions are introduced by a direct viscous-in viscid interaction technique, which includes an integral boundary layer calculation method.

The computer programs are written in FORTRAN (90).

The convergence characteristics are stable and allow efficient computation.

The capability of the present method is investigated through a number of test cases with different types of wing sections (N AC A 0012, N AC A 4415, GA(W)-l) for different aspect ratios and angles of attack.

The results include the lift and drag curves, lift and pressure distributions along the wing span, and the effect of the angle of attack and the aspect ratio on the wake rollup.

Where that the lift curve slope and the lift coefficient are increased with increasing aspect ratios.

The drag coefficient is inversely proportional to aspect ratios.

For small aspect ratios the lift distribution along the wing is elliptic and approaches more and more rectangular distribution with increasing aspect ratios.

The calculations of pressure distribution on the wings shows that there is a region of constant pressure on the upper surface of the wings near the trailing edge in the middle of the wings.

This indicates that there is a region of separated flow on the upper surface of the wings.

The vortex core rollup is increased with increasing of the angle of attack and decreased when the aspect ratio is increased.

The theoretical results in the present method are approximately gives compare reasonably well with the previous researches results.

These results show that the present theoretical method is able to capture much of flow over wings feature like separation and wake rollup.

التخصصات الرئيسية

الهندسة الميكانيكية

الموضوعات

• الطائرات
• الحمل الديناميكي الهوائي

• APA
• MLA
• AMA

لغة النص

الإنجليزية

نوع البيانات

رسائل جامعية

رقم السجل

BIM-305682