Unsteady Aerodynamics of Rotorcraft in Ground Effect - Aerospace ...

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$(Performance \226 Class 1 Airplane Motions)$

Figure 5: Coordinate System of the Rotor. Figure 6: Recirculation (IGE, y/r = 0, µ=0.03) - 10 - American Institute of Aeronautics and Astronautics Note: Inflow fluctuations IGE ~ 5-10%
x 10 6 Hotwire IGE Adv 0.03 Peak freq =70.0 6 12 x 106 Hotwire IGE Adv 0.04. Peak freq =1.7 Fourier Power Spectral Density 5 4 3 2 1 Fourier Power Spectral Density 10 8 6 4 2 0 0 10 20 30 40 50 60 70 80 Frequency 0 0 10 20 30 40 50 60 70 80 Frequency Fourier Power Spectral Density x 10 6 9 8 7 6 5 4 3 2 Hotwire- IGE Adv 0.05. Peak freq= 1.1 Fourier Power Spectral Density x 10 4 Hotwire OGE Adv 0.03 Peak freq =70.0 4 3.5 3 2.5 2 1.5 1 1 0.5 0 0 10 20 30 40 50 60 70 80 Frequency 0 0 10 20 30 40 50 60 70 80 Frequency 4 x 10 4 Hotwire OGE Adv 0.04 Peak freq =70.0 x 10 4 Hotwire OGE Adv 0.05 Maxfreq 70.0 6 Fourier Power Spectral Density 3.5 3 2.5 2 1.5 1 0.5 Fourier Power Spectral Density 5 4 3 2 1 0 0 10 20 30 40 50 60 70 80 Frequency 0 0 10 20 30 40 50 60 70 80 Frequency Figure 9: Comparison of Hotwire Frequencies. IGE vs OGE. Advance Ratios 0.03, 0.04, and 0.05 - 11 - American Institute of Aeronautics and Astronautics
Page 1 and 2: AIAA Paper 2004-2431, Fluid Dynamic
Page 3 and 4: III. Experiment description The exp
Page 5 and 6: 1. Experiment Setup The fuselage wa
Page 7 and 8: moments, with large intervals possi
Page 9: Figure 3: Rotor and Test Section Fi
Page 13 and 14: Figure 12: Experimental Setup: Fuse
Page 15 and 16: Figure 17: Variation of Side Force
Page 17 and 18: Figure 20: Variation of Side Force

Unsteady Aerodynamics of Rotorcraft in Ground Effect - Aerospace ...

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