The Application and Optimization of a Morphing Airfoil Wing for Lightweight Aircraft
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Poster
Abstract
The Morphing Wing research project explores the optimization of a variable airfoil profile wing for lightweight aircraft with the need for exceptional short takeoff and landing characteristics. With the utilization of XFLR5 and FLOW5 and field testing, this project intends to explore the capabilities of the morphing wing. Furthermore, an examination of wing optimization for high climb performance when in its high lift configuration will be studied. The intention is the modification of the camber length during flight to allow the plane to possess a higher top speed while retaining its short takeoff and landing (STOL) characteristics. To be commercially viable, parameters such as fuel capacity, structural flexibility, and structural weight concerns must be explored. The morphing wing will be developed for the Just Superstol where the airfoil configurations will be alternated between NACA 9420 for an exaggerated camber transformation to a streamlined profile of NACA 0020. The expected outcomes include the optimization for reduced drag and higher top speed when the wing is in streamlined form.
The Application and Optimization of a Morphing Airfoil Wing for Lightweight Aircraft
The Morphing Wing research project explores the optimization of a variable airfoil profile wing for lightweight aircraft with the need for exceptional short takeoff and landing characteristics. With the utilization of XFLR5 and FLOW5 and field testing, this project intends to explore the capabilities of the morphing wing. Furthermore, an examination of wing optimization for high climb performance when in its high lift configuration will be studied. The intention is the modification of the camber length during flight to allow the plane to possess a higher top speed while retaining its short takeoff and landing (STOL) characteristics. To be commercially viable, parameters such as fuel capacity, structural flexibility, and structural weight concerns must be explored. The morphing wing will be developed for the Just Superstol where the airfoil configurations will be alternated between NACA 9420 for an exaggerated camber transformation to a streamlined profile of NACA 0020. The expected outcomes include the optimization for reduced drag and higher top speed when the wing is in streamlined form.