Abstract This chapter describes the possible application of Rod Vortex Generators (RVGs) on helicopter rotor blades. Two different flight conditions are considered: hover and forward flight. The numerical model is validated with the available experimental data of the Caradonna–Tung model helicopter rotor blade (hover conditions) and the AH-1G helicopter (forward flight conditions). The application of RVGs on both rotor blades leads to an increment of the thrust coefficient with a power consumption penalty
Implementation of Rod Vortex Generators on Helicopter Rotor Blades in Hover and Forward Flight Conditions
2017-01-01
19 pages
Aufsatz/Kapitel (Buch)
Elektronische Ressource
Englisch
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