| Abstract [eng] |
The scope of this project is to review computational fluid dynamics analysis principles and perform such analysis on a tiltwing to determine its aerodynamic properties using “SolidWorks Flow Simulation” software. Results from afore-mentioned analysis are going to be compared with an experimental data acquired from the tests in the wind tunnel. For such analysis a 3D model of tiltwing was designed by using computer-aided design software “SolidWorks”. The model consists of three main parts – central part and two wings on both sides. Wingspan of the model – 260 mm. To determine propellers’ influence on the tiltwing aerodynamic properties, a 3D model of a three-blade propeller with a diameter of 78 mm was designed. In a “SolidWorks Flow Simulation” environment a global and a local meshes are created for both the propeller and the tiltwing. As the computational fluid dynamics analysis is hardware demanding, a sensitivity analysis of the mesh is required to determine the best computational time with respect to results accuracy. Computational fluid dynamics analysis done in this project can be split in three main configurations: propeller analysis, tiltwing without propeller analysis and tiltwing with propellers analysis. For the analysis of the propeller there is a rotating air region modelled around the part, which simulates the thrust force created by the propeller. For the tiltwing analysis, the 3D model is placed in a computational domain which imitates the test section of a wind tunnel where a physical model of the tiltwing was tested. For the third configuration the tiltwing 3D model in computational domain is placed in a same manner and for both propellers there are corresponding rotating air regions modelled. This setup allows to determine propellers’ influence on tiltwing aerodynamic properties. Besides the afore-mentioned configurations there were other parameters that changed during the analysis. Angle of attack for the central part was either 0° or 15° and angle of the side wings was changed in the range from -5° to 100° with an increment of 5°. The data acquired from the computational fluid dynamics analysis was then compared with the experimental data from wind tunnel tests. The maximum difference for lift force values was 31,96 % and for aerodynamic drag force values the difference reached 40,66 %. |
