BOEING-VERTOL VR-9 AIRFOIL (vr9-il)
BOEING-VERTOL VR-9 AIRFOIL - Boeing-Vertol VR-9 rotorcraft airfoil
| Details | Dat file | Parser | |
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(vr9-il) BOEING-VERTOL VR-9 AIRFOIL Boeing-Vertol VR-9 rotorcraft airfoil Max thickness 6.1% at 35% chord. Max camber 0.3% at 35% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
BOEING-VERTOL VR-9 AIRFOIL 31. 31. 0. 0. .005 0.00548 .01 0.00759 .02 0.00919 .025 0.01178 .035 0.01400 .05 0.01660 .07 0.01970 .095 0.02250 .125 0.02535 .16 0.02790 .20 0.03010 .25 0.03220 .30 0.03335 .35 0.03360 .40 0.03280 .45 0.03170 .50 0.02975 .55 0.02730 .60 0.02443 .65 0.02138 .70 0.01832 .75 0.01527 .80 0.01222 .85 0.00916 .89 0.00672 .92 0.00489 .945 0.00336 .965 0.00214 .98 0.00122 1.00 0.00 0. 0. .005 -.00480 .01 -.00661 .02 -.00801 .025 -.01020 .035 -.01185 .05 -.01400 .07 -.01610 .095 -.01825 .125 -.02080 .16 -.02285 .20 -.02455 .25 -.02610 .30 -.02690 .35 -.02700 .40 -.02650 .45 -.02550 .50 -.02400 .55 -.02220 .60 -.01984 .65 -.01736 .70 -.01488 .75 -.01240 .80 -.00992 .85 -.00744 .89 -.00546 .92 -.00397 .945 -.00273 .965 -.00174 .98 -.00099 1.00 0.0 |
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Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
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Polars for BOEING-VERTOL VR-9 AIRFOIL (vr9-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| vr9-il | 50,000 | 9 | 24.3 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr9-il | 50,000 | 5 | 23.8 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr9-il | 100,000 | 9 | 31.2 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr9-il | 100,000 | 5 | 27.4 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr9-il | 200,000 | 9 | 34.2 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr9-il | 200,000 | 5 | 32.5 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr9-il | 500,000 | 9 | 39.8 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr9-il | 500,000 | 5 | 42.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr9-il | 1,000,000 | 9 | 52.8 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr9-il | 1,000,000 | 5 | 55.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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