THE EFFECT OF SLIPSTREAM FLOW BY PROPELLER ON WINGS AERODYNAMIC CHARACTERISTICS OF UAV HALE AIRCRAFT
Research on the effect of slipstream flow by propellers has been carried out using simulation and experimental methods. The simulation method used is CFD while the experimental method is carried out in the LAPAN Subsonic Wind Tunnel. The research was conducted on a HALE UAV aircraft which has a span...
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| Format: | Theses |
| Language: | Indonesia |
| Online Access: | https://digilib.itb.ac.id/gdl/view/62032 |
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| Institution: | Institut Teknologi Bandung |
| Language: | Indonesia |
| Summary: | Research on the effect of slipstream flow by propellers has been carried out using simulation and experimental methods. The simulation method used is CFD while the experimental method is carried out in the LAPAN Subsonic Wind Tunnel. The research was conducted on a HALE UAV aircraft which has a span length of about
20 m and operates at a speed of 16.67 m/s. The test model to be tested in the wind tunnel is 1:10 scale down. The propeller is used as a tractor because it is positioned in front of the wing. The results show that the accuracy of the modeling results with the number of elements 3 to 4 million is quite stable and there are no significant fluctuations seen from the results of the lift and drag simulation data. The SST turbulent model was chosen because the parameter conditions were close to the actual conditions. The thrust generated by the propeller with increasing speed and RPM variations. The velocity vector of the propeller rotation rotates counterclockwise and results in a streamlined backward flow.
As the simulation results, it can be seen that the slipstream flow through the wing surface can delay separation, thereby increasing the lift coefficient and the drag coefficient, the difference in speed for cases of power off and power on occurs at an angle of attack of 12?. The difference in the simulation results from the CL curve for the speed of 30 m / s is about 3.8% and the CD curve is about 2.8%. For the experimental results, there is a slipstream phenomenon that occurs at an angle of attack of 12?. The difference in the CL curve for the speed of 30 m / s is about 8.4%. The comparison between simulation and experiment results is known to be 5.8% for power off and power on at 0.9%.
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