The effect of vortex trap on helicopter blade lift
The 5-seater Aerospatiale AS350B helicopter has been chosen in this analysis in order to investigate the capabilities of the vortex trap in increasing the helicopter blade lift. Blade Element Theory (BET) was applied to scrutinize the lift force and angle of attack distribution along the helicopt...
Saved in:
| 主要作者: | |
|---|---|
| 格式: | Thesis |
| 語言: | English |
| 出版: |
2011
|
| 主題: | |
| 在線閱讀: | http://eprints.uthm.edu.my/2694/1/24p%20MOHD%20FAUZI%20YAAKUB.pdf |
| 標簽: |
添加標簽
沒有標簽, 成為第一個標記此記錄!
|
| 總結: | The 5-seater Aerospatiale AS350B helicopter has been chosen in this analysis
in order to investigate the capabilities of the vortex trap in increasing the helicopter
blade lift. Blade Element Theory (BET) was applied to scrutinize the lift force and
angle of attack distribution along the helicopter blade. From BET, the retreating
blade must operate at a higher coefficient of lift for the purpose to balance the lift
force on both sides of the rotor. In the process of designing and analyzing the grooyer, ,
commercial CFD, Fluent 6.3 and pre-processor Gambit were utilised in order to
investigate the effect of groove which was applied on the upper surface of the
helicopter airfoil. The Shear-Stress Transport (SST) k - o turbulence model was
utilized in this analysis because of its capability in producing the flow inside the
groove and the ability on predicting the separation of the airfoil. The mesh sensitivity
analysis had also been accounted in the numerical study. The optimization of the
groove was done by analyzing the numbers and locations of the grooves, the design
depth and length of the groove and modification of the groove shape to smoothen the
velocities flow. Finally, the data from BET was used with data from numerical
analysis to obtain the lift force achieved by the vortex trap method to increase the lift
of helicopter blade. Thus, the small increment of lift was achieved when applying
groove on the upper surface of the retreating blade due to the small area contribution
at high angle of attack |
|---|