PENGEMBANGAN METODE DESAIN DAN ANALISIS TAIL ROTOR PADA HELIKOPTER SINGLE ROTOR DENGAN PENDEKATAN METODE LARRABEE YANG DIMODIFIKASI DAN CFD
Helicopter is a type of aircraft where lift and thrust are produced by the rotor. Single rotor helicopter has two rotors, the main rotor and the anti-torque system called tail rotor. These two rotors make it possible for the helicopter to take off and land vertically, also to hover and fly forward...
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| Format: | Final Project |
| Language: | Indonesia |
| Online Access: | https://digilib.itb.ac.id/gdl/view/33951 |
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| Institution: | Institut Teknologi Bandung |
| Language: | Indonesia |
| Summary: | Helicopter is a type of aircraft where lift and thrust are produced by the rotor. Single rotor helicopter has two rotors, the main rotor and the anti-torque system called tail rotor. These two rotors make it possible for the helicopter to take off and land vertically, also to hover and fly forward, backward, and laterally. The development of the helicopter rotor design, as one of the most important process in making of helicopter, has always been developed day by days. However, the analytical design method for the tail rotor, in both, manned and unmanned helicopter, have generally not got much attention in the developments. This research focuses on helicopter tail rotor design analytical method based on the Larrabee method, this method is based on general momentum theory and the blade element theory. In the development of this method, geometric data of UAV Helicopter Optera used as supporting data. This research is also analyzing the impact of residual torque generated from main rotor, in which the angular velocity, distance between rotor’s shafts, and the radius of the tail rotor as parameters of torque are included toward the design of the tail rotor to reach the performance target, in the form of thrust and power, at the hovering condition. The development method for the design of tail rotor from the helicopter results in tail rotor geometry, that includes chord and twist distribution. Performance analysis, thrust and power resulted from that geometry, is validated through CFD numerical method. The results from the 4 factors, which impacts the design of the tail rotor to thrust and power, is earned with 17.5% maximum error using this design method. Interraction between main rotor and tail rotor was also analyzed, where the wake effect arises which makes the thrust of each rotor decrease.
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