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STUDY OF IMPORTANT VARIABLES OF AERODYNAMICS FOR SUBSONIC AIRCRAFT USING ADVANCED AIRCRAFT ANALYSIS SOFTWARE
دراسة أهم المتغيرات الأيرودينامية لطائرة ذات سرعة تحت صوتية باستخدام برنامج AAA

Authors: Israa Yheaa Daood --- Sattar J. Habeeb --- Asaad T. Al-Omran
Journal: Journal of Engineering مجلة الهندسة ISSN: 17264073 25203339 Year: 2010 Volume: 16 Issue: 1 Pages: 877-893
Publisher: Baghdad University جامعة بغداد

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Abstract

This study presents the important variables of aerodynamics of subsonic aircraft using AAA software, moreover to comprehensive preview of some imperical and mathematical equations where needs in this analysis process. Cruise mission chose for this study comparing with another mission of flight such as Take-off, Climb, Dive & Descent, and Landing according to important of the mission and cruise mission has large rung during the flight mission. These analyses of process submit to more and complex iteration process until we access to correct solution. Lift, drag, and moment coefficients along the lift surfaces such as wing, and horizontal tail were showed. Also this paper explain the effect of flight level, aircraft speed, aspect ratio of lift surfaces on lift curve. Results show that, increase the value of altitude, load factor, aspect ratio leads to increase the value of lift coofficent and decrease the airplane velocity.

الدراسة توضح أهم المتغيرات الأيرودينامية لطائرة ذات سرعة تحت صوتية باستخدام برنامج AAA بالإضافة إلى استعراض شامل لبعض المعادلات التجريبية والرياضية الخاصة في عملية التحليل. الدراسة تمت في مرحلة التحليق للطائرة بسبب أهمية هذه المرحلة, فترة بقاء الطائرة فيها تكون كبيرة مقارنة مع الإقلاع, التسلق, الانحدار, والهبوط حيث تخضع عملية التحليل هذه إلى العديد من الحالات التكرارية المستمرة إلى أن نصل إلى الحل الدقيق. أهم المتغيرات المدروسة كانت توزيع معاملات الرفع, الكبح, العزم على أسطح الرفع المتمثلة بالجناح والذنب الأفقي, بالإضافة إلى دراسة تأثير سقف الطيران, سرعة الطائرة, النسب الباعية لأسطح الرفع على منحني الرفع. أخيرا تم دراسة شكل العلاقة بين معامل الرفع, معامل الكبح عند قيم رقم ماخ مختلفة. النتائج اظهرت أن زيادة مستوي الطيران, معامل الحمل, النسبة الباعية لأسطح الرفع يؤدي إلى زيادة قيم معامل الرفع بينما يحدث العكس في حالة زيادة سرعة الطائرة.


Article
Improvement of Micro UAV Performance using Tandem-Wing Design

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Abstract

The main objective for the present work is related with design of MAV to get high performance and long endurance used for surveillance and monitoring in military and civilian. The most important problem that faced the MAV is flying with low Reynolds numbers (Mach number is too law) and high lift with avoid high drag, the tandem-wing design is sucseceful and more reliable for this purpose because it reduced the drag to a half and gives good aerodynamic chractrastices when it’s compared with the conventional wing design. The dimensions of a MAV are 120mm length, wing span 130mm ( from tip to tip) and 12g in weight (the standard weight of MAV about 5- 20 g) with rang 50m (is the distance that the aircraft cut from point to another). The softwares that used in the present work are (Java foil, Soled works, ANSYS, J2) to prove the results.For the aerodynamic coefficients (CL, CD) were checked for two models (Tandem wing and conventional wing) by using ANSYS. To ensure that the design is successful we made a Simulation for the design by using (The J2 Universal Tool-Kit for Aircraft Dynamics) software and used to testing the aerodynamic characteristic and performers, stability and control. The major benefits of the tandem wings are to reduce drag to half and increase the lift rather than conventional wing by separating the two wings. Java foil was used to calculate the aerodynamics coefficients for the airfoil.

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