BOEING-VERTOL VR-8 AIRFOIL (vr8-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-8 AIRFOIL (vr8-il) Reynolds number: 200,000 Max Cl/Cd: 51.33 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-vr8-il-200000.txt Download as CSV file: xf-vr8-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: BOEING-VERTOL VR-8 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4626 0.08565 0.08239 -0.0086 1.0000 0.0413
-8.750 -0.4656 0.08106 0.07784 -0.0106 1.0000 0.0427
-8.500 -0.5585 0.08287 0.07950 -0.0149 1.0000 0.0374
-8.250 -0.5595 0.07898 0.07566 -0.0171 1.0000 0.0380
-8.000 -0.5637 0.07484 0.07152 -0.0200 1.0000 0.0389
-7.750 -0.5643 0.07055 0.06721 -0.0225 1.0000 0.0398
-7.500 -0.5634 0.06629 0.06288 -0.0247 1.0000 0.0412
-7.250 -0.5234 0.05216 0.04852 -0.0287 1.0000 0.0462
-7.000 -0.5280 0.04517 0.04135 -0.0293 1.0000 0.0470
-6.750 -0.5158 0.04056 0.03697 -0.0289 1.0000 0.0490
-6.500 -0.5057 0.03733 0.03371 -0.0285 1.0000 0.0519
-5.750 -0.5038 0.04029 0.03569 -0.0263 1.0000 0.0640
-5.500 -0.4903 0.03803 0.03290 -0.0249 1.0000 0.0740
-5.250 -0.4737 0.03499 0.02997 -0.0241 1.0000 0.0780
-5.000 -0.4583 0.03271 0.02742 -0.0228 1.0000 0.0900
-4.750 -0.4419 0.03069 0.02519 -0.0215 1.0000 0.1035
-4.500 -0.4245 0.02870 0.02305 -0.0203 1.0000 0.1175
-4.250 -0.3882 0.02268 0.01560 -0.0158 1.0000 0.0472
-4.000 -0.3658 0.01988 0.01267 -0.0144 1.0000 0.0432
-3.750 -0.3435 0.01830 0.01086 -0.0129 1.0000 0.0435
-3.500 -0.3216 0.01716 0.00954 -0.0115 1.0000 0.0448
-3.250 -0.3005 0.01590 0.00818 -0.0100 1.0000 0.0447
-3.000 -0.2811 0.01499 0.00724 -0.0085 1.0000 0.0451
-2.750 -0.2468 0.01402 0.00624 -0.0100 0.9951 0.0474
-2.500 -0.2036 0.01295 0.00516 -0.0134 0.9858 0.0483
-2.250 -0.1570 0.01212 0.00431 -0.0173 0.9730 0.0509
-2.000 -0.1103 0.01153 0.00365 -0.0210 0.9567 0.0571
-1.750 -0.0730 0.00954 0.00295 -0.0236 0.9306 0.3771
-1.500 -0.0492 0.00817 0.00293 -0.0222 0.9033 0.7289
-1.250 -0.0230 0.00788 0.00286 -0.0195 0.8505 0.8596
-1.000 0.0133 0.00810 0.00273 -0.0194 0.7794 0.9202
-0.750 0.0517 0.00825 0.00263 -0.0211 0.7526 0.9412
-0.500 0.0865 0.00839 0.00259 -0.0223 0.7309 0.9619
-0.250 0.1265 0.00848 0.00250 -0.0248 0.7132 0.9790
0.000 0.1757 0.00847 0.00236 -0.0293 0.6983 0.9916
0.250 0.2179 0.00844 0.00223 -0.0326 0.6850 1.0000
0.500 0.2408 0.00847 0.00217 -0.0318 0.6732 1.0000
0.750 0.2633 0.00854 0.00211 -0.0308 0.6533 1.0000
1.000 0.2864 0.00862 0.00208 -0.0299 0.6373 1.0000
1.250 0.3101 0.00868 0.00210 -0.0291 0.6257 1.0000
1.500 0.3341 0.00876 0.00213 -0.0284 0.6137 1.0000
1.750 0.3581 0.00885 0.00217 -0.0277 0.6014 1.0000
2.000 0.3823 0.00894 0.00223 -0.0270 0.5893 1.0000
2.250 0.4065 0.00904 0.00233 -0.0262 0.5766 1.0000
2.500 0.4307 0.00914 0.00242 -0.0255 0.5599 1.0000
2.750 0.4542 0.00928 0.00251 -0.0246 0.5353 1.0000
3.000 0.4769 0.00948 0.00258 -0.0235 0.4929 1.0000
3.250 0.4994 0.00973 0.00270 -0.0224 0.4378 1.0000
3.500 0.5199 0.01025 0.00291 -0.0211 0.3484 1.0000
3.750 0.5363 0.01141 0.00340 -0.0196 0.2004 1.0000
4.000 0.5532 0.01264 0.00403 -0.0181 0.0744 1.0000
4.250 0.5748 0.01328 0.00457 -0.0170 0.0541 1.0000
4.500 0.5973 0.01381 0.00515 -0.0160 0.0495 1.0000
4.750 0.6191 0.01444 0.00589 -0.0149 0.0470 1.0000
5.000 0.6401 0.01519 0.00673 -0.0137 0.0459 1.0000
5.250 0.6611 0.01596 0.00758 -0.0125 0.0455 1.0000
5.500 0.6818 0.01686 0.00854 -0.0112 0.0453 1.0000
5.750 0.7028 0.01788 0.00961 -0.0100 0.0450 1.0000
6.000 0.7251 0.01881 0.01065 -0.0090 0.0435 1.0000
6.250 0.7478 0.02002 0.01193 -0.0080 0.0425 1.0000
6.500 0.7705 0.02113 0.01309 -0.0072 0.0396 1.0000
6.750 0.7940 0.02284 0.01489 -0.0063 0.0385 1.0000
7.000 0.8183 0.02505 0.01730 -0.0053 0.0383 1.0000
7.250 0.8408 0.02793 0.02036 -0.0045 0.0372 1.0000
7.500 0.8614 0.03116 0.02395 -0.0034 0.0369 1.0000
10.250 0.6715 0.09075 0.08761 -0.0071 0.0795 1.0000
10.500 0.6583 0.09762 0.09445 -0.0108 0.0770 1.0000
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Polar data table (+)
Polar graphs
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