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Simulation of a Light Aircraft Encountering a Helicopter Wake

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Figure

Figure 1.Wake vorticity plots (a) and (b), wake stream-lines plots (c) and (d). Four-bladed rotor,and Ct=0.013 ;µ=0.1 αT P P =-4o.
Figure 3.Comparison of three wake models against Heyson’s experimentsC12 at (a) x/R=2 and (b) x/R = 3 planes.t=0.0064 and µ=0.095.
Figure 4.Measured velocity versus vortex age.6 Puma helicopter at speeds of 65 kt and 70 kt.
Figure 5.Velocity distributions predicted by (a) CFD actuator disk and (b) Beddoes wake model with the measureddecay relation
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