Abstract
Experimental tests regarding the M-346 aircraft model made via 3D printing were carried out in order to obtain numerical data and characteristics in the form of graphs of basic aerodynamic forces and coefficients. The tests were carried out for the left side of the airframe model in a clean configuration, without additional suspension equipment; the flight control surfaces and the aerodynamic brake were in neutral positions. Based on the scan of the base model in 1:48 scale using a Nikon Model Maker MMDx laser scanning head, followed by the generation and optimization of some of the airframe elements in SolidWorks software, a test model ready for printing was prepared. Using the MakerBot Print program, the printing parameters were set, and the process itself was completed using a MakerBot Replicator Z18 3D printer. The next step was manual treatment in order to remove the material excess from the melted thermoplastic material, join the elements and appropriately polish the surface of the tested model in order to obtain the desired quality. The test was carried out using a Gunt HM 170 wind tunnel for fixed airflow velocities at variable angles of attack. On this basis, the numerical values of lift force, Pz, and drag force, Px, were obtained; then, the lift force indices, Cz, and drag force indices, Cx, were computed for the steady states, which were for angle α from −12 to 16°. The use of 3D printing contributed to the generation of geometry, which, for research purposes, was scaled down in order to fully use the available measurement space of the wind tunnel. The final stage of the work was to compare the obtained curves of particular characteristics with the literature data.
Highlights
Throughout the history of aviation, aircraft manufacturers have always tried to produce better and stronger designs for their aircrafts
Despite the apparent irregularities at the limit values of the angle of attack and the significantly irregular curves obtained for air flow velocities of V = 25 and 27 m s−1, it can be concluded that they fell within the error limits
HM 170 wind tunnel enabled the analysis of the results obtained for the lift force, Pz; drag force, Px; computed lift force coefficient, Cz; and drag force coefficient, Cx, as well as polar and aerodynamic efficiency coefficients for selected constant airflow velocities (V = 15, 20, 25 and 27 m s−1 ) with a change in the angle of attack in the range of α = −12◦ ÷ 16◦
Summary
Throughout the history of aviation, aircraft manufacturers have always tried to produce better and stronger designs for their aircrafts. All parts of an aircraft must be strong enough to carry heavy loads in all directions, so construction is of key importance. Aircrafts designed for long-distance travel have a different internal structure than aircrafts designed for agriculture or search and rescue missions [1,2,3]. The primary factors to consider in aircraft structures are strength, weight and reliability. The factors determine the requirements to be met by any material used to construct or repair the aircraft.
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