![]() ![]() In recent decades, several tools and software have been developed based on aerodynamics and numerical methods. Thus, the blade designed for high altitude SAR UAV is structurally safe to operate in 0-5,000 RPM range, and its use in search missions could save many lives in the Himalayas.Īn aerodynamic technique for calculating lift and drag coefficients is one of the required instruments in the wing design process. The CFD analysis was performed in ANSYS CFX which gave a thrust value of 2.27 N for the same boundary conditions. The validation of experimental results has been done by the CFD analysis. The analytical solution for thrust with the same conditions was 1.7 N with 85.6% efficiency. Experimental analysis of the blade gave a thrust of 0.92 N at 2,697 RPM at 1,400 m. The modal analysis shows the first natural frequency occurs at around 12,000 RPM which is safe for operating the blade at 0-5,000 RPM. This stress is within the limit of yield strength of the aluminum alloy, 28 MPa. The geometry designed for an altitude range of 3,000-5,000 m faced the total stress of 6.0 MPa which was at 70% of the blade span. The blade element theory-based design and analysis code was developed, and user-friendly aerodynamic inputs were used to obtain the desired outputs. The property of aluminum alloy 1,060 being lightweight is chosen for designing and testing of blade. The objective of this research work is to design thrust optimized blade for an altitude range of 3,000–5,000 m with a density of air 0.7364 kg/m3, respectively, and perform thrust analysis. This is because as the altitude increases, the density of air decreases which affects the thrust generation of the UAV. The commercially available unmanned aerial vehicles are not good enough for search and rescue flight at high altitudes. The experimental results were compared with CFD results and an average relative error of 18% was observed which may be due to assumption of 2-D airfoil in CFD analysis. However, in the numerical results the stalling was observed little earlier than 18° angle of attack. From the experiments it was found that value of lift coefficient increases with angle of attack and stalling occurs at 18° for all the air speeds. The results are presented in terms of pressure contours, velocity contours, pressure coefficient and lift coefficient. The experimental and numerical investigations were done in the wide range of Reynolds number (range: 0.55 to 1.12 lakh) and angle of attack (range: -6° to 20°). The spring balances are used to obtain lift force readings at different angles and air speeds. a traverse mechanism that can hold the model in the test section at different angles of attack and air speeds and a supporting frame to hold the traverse mechanism over it. It mainly consists of two components viz. The setup was developed indigenously and installed in an open circuit low-speed wind tunnel. This paper presents a design of force balance setup that can measure lift force acting on the aircraft model. The results show that the airfoil GOE 652 has the most effective surface area among the four airfoils. The highest down force was 1906.847 N at 15 degree by GOE 652 airfoil. The results observe that the highest lift coefficient value was achieved by GOE 652 which was equal to CL=1.9310 at 7 degree angle while the highest lift-to-drag ratio achieved by NACA 4415 which was equal to 100.8359. The main objective in this paper is finding the effect of airfoil surface specification as a part of airfoil geometry features. In addition, the drag and down forces have been calculated with respect to airfoil geometry features. The numerical simulation has been done using ANSYS Fluent to obtain drag coefficient, lift coefficient and lift-to-drag ratio of all cases. The present paper investigate airfoil NACA 0012, NACA 4415, GOE 528 and GOE 652 to estimate the effectiveness of airfoil shape based on different angles of attack. ![]() ![]() The influence of aerodynamic forces will produce a down force to the bottom of the vehicle. The development of car modification using rear wings or spoilers, underlies the research on the aerodynamic performance of airfoil. ![]()
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