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Airfoil group4/16/2023 ![]() ![]() His CEO duties will include day-to-day management of the agency’s professional operations, including oversight of the firm’s four practice areas and directing Airfoil’s strategic planning, client services and satisfaction, agency growth, and staff development initiatives. He most recently served as president of Airfoil Communications. The results obtained by this study are significant for the design of tailsitter UAVs.Donovan has been with Airfoil for more than 15 years. Compared with the original layout and size, the time coefficient of the new design of the tailsitter UAV improved by 19.5%, while the air resistance reduced by 34.78%. The optimal structural parameters were wing root chord length at 315 mm, wingtip chord length at 182 mm, wingspan length at 1198 mm, and sweep angle at 16°. A multi-objective genetic algorithm (MOGA) was used to optimize the parameters with regard to the maximum time coefficient and minimum air resistance. The response surface methodology (RSM) for the time coefficient and air resistance was established using a genetic aggregation method. ![]() CFD simulation was verified by carrying out a wind tunnel test, and the results revealed that the aerodynamic coefficient error was less than 5%, while the air resistance error was less than 6%. The time coefficient and air resistance were simulated under different structural parameter combinations using the CFD method. By carrying out a central composite design (CCD) test, 25 sample points of the four particular factors were constructed. The analysis of variance determined that the specific factors influencing the time coefficient and air resistance were the root chord, wingtip chord, wingspan, and sweep angle. The time coefficient and air resistance were calculated using the computational fluid dynamics (CFD) method under different parameter combinations. Using a 2k full factorial test, 512 experiments on the nine parameters were conducted at their maximum and minimum values. Nine parameters of the tailsitter UAV were investigated. ![]() This study designed a vertical take-off and landing tailsitter unmanned aerial vehicle (UAV) with a long endurance time. The influence from upstream components is proved to improve the aerodynamic characteristics of the rear wing, especially at α=8°. The increase of the angle of attack, incoming flow velocity, and distance between the front and rear wings can reduce the interference between front and rear wings. Meanwhile, the flow field characteristics and interference characteristics of the front and rear wings are studied. The lift ratio of the front and rear wings shows a good similarity at different Mach numbers, especially for the 15° model, and the value eventually tends to 1.3 at α=12°. Compared with traditional morphing aircraft, the main advantages of this configuration include better transonic and supersonic performance, better lift characteristics in the state of high-aspect ratio, and lower zero-lift drag in the supersonic state. The compressible Navier-Stokes equations in the conservative form are solved to analyze the configuration characteristics and the aerodynamic benefits of this aircraft with different values of sweep angle (15°, 60°) and Mach number. This paper presents a new concept aircraft with a diamond joined-wing morphing configuration, which simultaneously adjusts the sweep angles of both the front wing and rear wings by a telescopic support rod. ![]()
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