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Abstract
This paper presents the aerodynamic modelling and analysis of surfaces created by a novel deployable mechanism, which is composed of a four-bar linkage and a scissor-structural mechanism (SSM) which contains several scissor-like elements (SLEs). With the help of that mechanism, which is located inside the trailing portion of wing section, continuous adjustment of the airfoil is possible. In order to highlight the advantageous aerodynamic characteristics of newly created airfoil geometries via proposed SSM, several aerodynamic analyses have been performed. The flow characteristics used for the analyses are determined by the flight envelope of an intended generic UAV. Since the maximum speed range of the sample aircraft is well below Mach 0.3, incompressible flow assumption is made throughout the solutions and conservation laws of Reynolds Transport Theorem are employed.
Highlights
From the Wright brothers, man has gone through several structural changes to increase the efficiency of aircraft
Most of modern aircrafts use conventional control surfaces such as flaps, ailerons, or slats, which allow the aircrafts to fly at a range of flight conditions; their performance are not optimal since such a design of control surfaces does not provide a smooth transition of camber in the chord-wise direction [1]
In order provide a solution to the problem of lacking viscous contribution, XFOIL is developed with a viscous coupling formulation where the entire viscous solution is strongly interacted with the incompressible potential flow via the surface transpiration model
Summary
From the Wright brothers, man has gone through several structural changes to increase the efficiency of aircraft. Most of modern aircrafts use conventional control surfaces such as flaps, ailerons, or slats, which allow the aircrafts to fly at a range of flight conditions; their performance are not optimal since such a design of control surfaces does not provide a smooth transition of camber in the chord-wise direction [1] This phenomenon causes a sudden change in the pressure distribution at the hinge line of the control surfaces, and it is usually associated with a drag penalty and the possibility of separation [2, 3]. In civil aviation, most of aircrafts have trailing edges with a honeycomb sandwich structure which are actuated by concentrated hydraulic servo mechanisms Such designs have the advantage in terms of stiffness and a large & fast-respond driving force, from a morphing wing standpoint, such designs have a discontinuity at joint position, insufficient in-plane deformability, and a large driving system weight [7]. As a summary, increasing the number of SLEs does not affect the mean structural error but increases the stiffness of the structure and smooths the surface
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