BOEING-VERTOL VR-8 AIRFOIL WITH TAB (vr8b-il)
BOEING-VERTOL VR-8 AIRFOIL WITH TAB - Boeing-Vertol VR-8 rotorcraft airfoil with tab
Details | Dat file | Parser | |
(vr8b-il) BOEING-VERTOL VR-8 AIRFOIL WITH TAB Boeing-Vertol VR-8 rotorcraft airfoil with tab Max thickness 8.2% at 35% chord. Max camber 1.2% at 35% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
BOEING-VERTOL VR-8 AIRFOIL WITH TAB 30. 30. 0. 0. .005 0.0085 .01 0.01175 .02 0.01425 .025 0.0183 .035 0.0217 .05 0.0261 .07 0.0309 .095 0.0357 .125 0.0402 .16 0.0444 .20 0.0480 .25 0.0510 .30 0.0530 .35 0.0535 .40 0.0525 .45 0.0502 .50 0.0467 .55 0.0426 .60 0.0380 .65 0.0333 .70 0.0285 .75 0.0237 .80 0.0190 .85 0.01428 .89 0.01048 .92 0.00761 .945 0.00524 .96 0.003404 1.01 0.003404 0. 0. .005 -.00535 .01 -.00737 .02 -.00880 .025 -.01090 .035 -.01255 .05 -.01465 .07 -.01685 .095 -.0190 .125 -.0212 .16 -.0232 .20 -.0250 .25 -.0266 .30 -.0277 .35 -.0280 .40 -.0276 .45 -.0265 .50 -.0247 .55 -.0225 .60 -.0200 .65 -.0175 .70 -.0150 .75 -.0125 .80 -.0100 .85 -.0075 .89 -.0055 .92 -.0040 .945 -.00275 .96 -.001596 1.01 -.001596 |
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Polars for BOEING-VERTOL VR-8 AIRFOIL WITH TAB (vr8b-il)
Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
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vr8b-il | 50,000 | 9 | 32.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
vr8b-il | 50,000 | 5 | 31.7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
vr8b-il | 100,000 | 9 | 41.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
vr8b-il | 100,000 | 5 | 37.1 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
vr8b-il | 200,000 | 9 | 47 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
vr8b-il | 200,000 | 5 | 44.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
vr8b-il | 500,000 | 9 | 84.8 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
vr8b-il | 500,000 | 5 | 50.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
vr8b-il | 1,000,000 | 9 | 64.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
vr8b-il | 1,000,000 | 5 | 62 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
Reynolds number calculator |