BOEING-VERTOL VR-7 AIRFOIL WITH TAB (vr7b-il)
BOEING-VERTOL VR-7 AIRFOIL WITH TAB - Boeing-Vertol VR-7 rotorcraft airfoil with tab
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(vr7b-il) BOEING-VERTOL VR-7 AIRFOIL WITH TAB Boeing-Vertol VR-7 rotorcraft airfoil with tab Max thickness 12% at 33% chord. Max camber 3% at 29% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
BOEING-VERTOL VR-7 AIRFOIL WITH TAB 38. 38. 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 .0374 .81 .0301 .845 .0235 .88 .0167 .91 .0105 .935 .0062 .96 .0050 1.0 .0050 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 -.01075 .81 -.00845 .845 -.0064 .88 -.00425 .91 -.00235 .935 -.0006 .96 0. 1.0 0. |
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Polars for BOEING-VERTOL VR-7 AIRFOIL WITH TAB (vr7b-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| vr7b-il | 50,000 | 9 | 30.7 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr7b-il | 50,000 | 5 | 33.3 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr7b-il | 100,000 | 9 | 52.1 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr7b-il | 100,000 | 5 | 53.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr7b-il | 200,000 | 9 | 72.9 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr7b-il | 200,000 | 5 | 71.4 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr7b-il | 500,000 | 9 | 99.5 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr7b-il | 500,000 | 5 | 92.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr7b-il | 1,000,000 | 9 | 118.1 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr7b-il | 1,000,000 | 5 | 105.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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