The results of this study indicate that the Selig S1223 airfoil profile, due to its superior performance at low Reynolds numbers, high-lift, and reduced noise characteristics at low angles of attack, combined with the use of the high strength carbon fiber, proves to be an excellent choice for this RA-driven aircraft application. AIRFOIL Engineering Engineering, Aerospace S1223 Science & Technology Technology VERTICAL TAKE-OFF. Overview Research Identifiers Additional Document Info. The structural stress and strain determined under the loading conditions were satisfactory and the designed wing could sustain the high reciprocating inertia forces in the RA-driven VTOL UAV module. Design and Structural Analyses of a Reciprocating S1223 High-Lift Wing for an RA-Driven VTOL UAV. Currently, I am running the case of the flow around a sd7003 airfoil presented in your paper (On the utility of GPU accelerated high-order methods for unsteady flow. The span and chord lengths of the LEAD are 67.5 mm and 18.7 mm, respectively, with the span being 15 of the total wing span. It has maximum thickness of 12.1 at 19.8 chord and maximum camber of 8.1 at 49 chord. The wing was designed in SolidWorks, while finite element analysis was performed with ANSYS mechanical in conjunction with the inertia forces due to the reciprocating motion of the wing and the lift and drag forces that were derived from the aerodynamic wing analyses. The SD7003 airfoil was used as a baseline and modified airfoils were derived by altering the leading edge radius, keeping maximum thickness unchanged. The S1223 airfoil is commonly used for high lift RC competition airplanes. The material selected for the wing structures including ribs, spars, and skin, was high-strength carbon fiber. The research findings from the structural analysis of the S1223 high-lift airfoil indicated that it is applicable for use in an unmanned aerial vehicle as well. This research focused on the structural design and analysis of a high-lift, low Reynolds number airfoil profile, the Selig S1223, under reciprocating inertial force loading, to determine the feasibility of its use in a new reciprocating airfoil (RA) driven VTOL UAV. The airfoil will be used for a small UAV with a chord of 23.4. In the design stage of an aircraft, structural analyses are commonly employed to test the integrity of the aircraft components to demonstrate the capability of the structural elements to withstand what they are designed for, as well as predict potential failure of the components. Transcribed image text: Enter the website and search for the S1223 airfoil.
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