BOEING-VERTOL VR-7 AIRFOIL (vr7-il)
BOEING-VERTOL VR-7 AIRFOIL - Boeing-Vertol VR-7 rotorcraft airfoil
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(vr7-il) BOEING-VERTOL VR-7 AIRFOIL Boeing-Vertol VR-7 rotorcraft airfoil Max thickness 12% at 33% chord. Max camber 3.1% at 33% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
BOEING-VERTOL VR-7 AIRFOIL 39. 39. 0. 0. .005 .0165 .01 .0218 .02 .0298 .03 .03615 .04 .0415 .05 .04605 .06 .05025 .07 .0541 .085 .0593 .102 .0645 .12 .0691 .14 .0737 .16 .0775 .18 .0808 .20 .0838 .225 .0867 .255 .0892 .29 .0909 .33 .0914 .37 .0905 .41 .0887 .45 .0856 .49 .0816 .53 .0767 .57 .0710 .61 .0646 .65 .0580 .69 .0514 .73 .0447 .77 .0381 .81 .0315 .845 .0257 .88 .0199 .91 .0149 .935 .01078 .955 .00745 .98 .00331 1.0 0.0 0. 0. .005 -.00575 .01 -.0081 .02 -.0109 .03 -.0129 .04 -.01445 .05 -.01585 .06 -.01710 .07 -.01805 .085 -.01985 .102 -.02145 .12 -.02285 .14 -.0241 .16 -.0251 .18 -.0260 .20 -.0266 .225 -.0273 .255 -.0280 .29 -.0285 .33 -.0289 .37 -.0290 .41 -.0285 .45 -.0275 .49 -.0260 .53 -.0240 .57 -.0220 .61 -.0199 .65 -.0179 .69 -.0158 .73 -.0138 .77 -.0117 .81 -.0097 .845 -.00791 .88 -.00613 .91 -.00459 .935 -.00332 .955 -.00230 .98 -.00102 1.0 0. |
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Polars for BOEING-VERTOL VR-7 AIRFOIL (vr7-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| vr7-il | 50,000 | 9 | 29 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr7-il | 50,000 | 5 | 32.1 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr7-il | 100,000 | 9 | 51.7 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr7-il | 100,000 | 5 | 53.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr7-il | 200,000 | 9 | 73.7 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr7-il | 200,000 | 5 | 72.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr7-il | 500,000 | 9 | 103 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr7-il | 500,000 | 5 | 96.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr7-il | 1,000,000 | 9 | 125 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr7-il | 1,000,000 | 5 | 113.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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