BOEING-VERTOL V23010-1.58 AIRFOIL (v23010-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING-VERTOL V23010-1.58 AIRFOIL (v23010-il) Reynolds number: 50,000 Max Cl/Cd: 23.75 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-v23010-il-50000.txt Download as CSV file: xf-v23010-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: BOEING-VERTOL V23010-1.58 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4672 0.10926 0.10205 0.0134 1.0000 0.3180
-8.750 -0.4610 0.10660 0.09943 0.0142 1.0000 0.3391
-8.500 -0.4679 0.10499 0.09791 0.0147 1.0000 0.3590
-8.250 -0.4388 0.10058 0.09350 0.0165 1.0000 0.3857
-8.000 -0.4393 0.09844 0.09144 0.0178 1.0000 0.4108
-7.750 -0.4295 0.09613 0.08918 0.0196 1.0000 0.4403
-7.500 -0.4035 0.09215 0.08520 0.0209 1.0000 0.4700
-7.250 -0.3864 0.08896 0.08205 0.0223 1.0000 0.5004
-7.000 -0.3707 0.08595 0.07908 0.0237 1.0000 0.5314
-6.750 -0.3588 0.08319 0.07637 0.0251 1.0000 0.5612
-6.250 -0.3264 0.07700 0.07026 0.0265 1.0000 0.6121
-6.000 -0.3123 0.07396 0.06726 0.0268 1.0000 0.6313
-5.750 -0.3021 0.07109 0.06445 0.0271 1.0000 0.6462
-5.000 -0.4839 0.05155 0.04507 -0.0038 1.0000 0.3239
-4.750 -0.4679 0.04353 0.03572 -0.0120 1.0000 0.2287
-4.500 -0.4457 0.04020 0.03167 -0.0119 1.0000 0.1965
-4.250 -0.4241 0.03759 0.02859 -0.0108 1.0000 0.1789
-4.000 -0.4023 0.03570 0.02611 -0.0093 1.0000 0.1651
-3.750 -0.3816 0.03350 0.02375 -0.0080 1.0000 0.1597
-3.500 -0.3602 0.03190 0.02176 -0.0064 1.0000 0.1543
-3.250 -0.3385 0.03095 0.02039 -0.0047 1.0000 0.1502
-3.000 -0.3167 0.02928 0.01864 -0.0034 1.0000 0.1478
-2.750 -0.2946 0.02794 0.01719 -0.0021 1.0000 0.1449
-2.500 -0.2722 0.02684 0.01595 -0.0007 1.0000 0.1425
-2.250 -0.2499 0.02591 0.01490 0.0006 1.0000 0.1410
-2.000 -0.2276 0.02510 0.01404 0.0020 1.0000 0.1406
-1.750 -0.2057 0.02437 0.01333 0.0033 1.0000 0.1424
-1.500 -0.1845 0.02380 0.01276 0.0045 1.0000 0.1460
-1.250 -0.1643 0.02339 0.01228 0.0057 1.0000 0.1498
-1.000 -0.1470 0.02292 0.01185 0.0072 1.0000 0.1534
-0.750 -0.1305 0.02256 0.01153 0.0085 1.0000 0.1584
-0.500 -0.1139 0.02238 0.01132 0.0097 1.0000 0.1656
-0.250 -0.0975 0.02213 0.01118 0.0105 1.0000 0.1799
0.000 -0.0273 0.01929 0.01173 0.0045 0.9992 1.0000
0.250 0.0757 0.02014 0.01184 -0.0093 0.9648 1.0000
0.500 0.1857 0.02025 0.01167 -0.0240 0.9262 1.0000
0.750 0.2889 0.01954 0.01088 -0.0357 0.8782 1.0000
1.000 0.3417 0.01908 0.01027 -0.0377 0.8188 1.0000
1.250 0.3697 0.01895 0.00986 -0.0351 0.7609 1.0000
1.500 0.3882 0.01927 0.00987 -0.0317 0.7051 1.0000
1.750 0.4071 0.01967 0.00997 -0.0289 0.6598 1.0000
2.000 0.4276 0.02012 0.01017 -0.0268 0.6233 1.0000
2.250 0.4495 0.02061 0.01043 -0.0251 0.5947 1.0000
2.500 0.4714 0.02119 0.01084 -0.0237 0.5701 1.0000
2.750 0.4941 0.02182 0.01129 -0.0225 0.5504 1.0000
3.000 0.5168 0.02249 0.01184 -0.0213 0.5327 1.0000
3.250 0.5391 0.02321 0.01247 -0.0202 0.5162 1.0000
3.500 0.5612 0.02399 0.01322 -0.0192 0.5010 1.0000
3.750 0.5830 0.02480 0.01400 -0.0181 0.4861 1.0000
4.000 0.6046 0.02564 0.01484 -0.0171 0.4718 1.0000
4.250 0.6262 0.02651 0.01569 -0.0160 0.4580 1.0000
4.500 0.6481 0.02742 0.01658 -0.0149 0.4453 1.0000
4.750 0.6712 0.02826 0.01734 -0.0138 0.4331 1.0000
5.000 0.6913 0.02943 0.01864 -0.0129 0.4205 1.0000
5.250 0.7110 0.03074 0.02006 -0.0119 0.4087 1.0000
5.500 0.7328 0.03194 0.02126 -0.0109 0.3982 1.0000
5.750 0.7520 0.03345 0.02293 -0.0100 0.3878 1.0000
6.000 0.7690 0.03528 0.02495 -0.0091 0.3778 1.0000
6.250 0.7931 0.03640 0.02598 -0.0082 0.3683 1.0000
6.500 0.8024 0.03906 0.02903 -0.0073 0.3587 1.0000
6.750 0.8264 0.04047 0.03042 -0.0065 0.3517 1.0000
7.000 0.8270 0.04435 0.03476 -0.0060 0.3452 1.0000
7.250 0.8417 0.04663 0.03716 -0.0052 0.3379 1.0000
7.500 0.8478 0.04998 0.04069 -0.0046 0.3321 1.0000
7.750 0.8311 0.05596 0.04697 -0.0052 0.3294 1.0000
8.000 0.8026 0.06339 0.05455 -0.0070 0.3301 1.0000
8.250 0.7778 0.07064 0.06184 -0.0094 0.3325 1.0000
8.500 0.7620 0.07693 0.06812 -0.0114 0.3354 1.0000
8.750 0.5794 0.09999 0.09079 -0.0343 0.5033 1.0000
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Polar data table (+)
Polar graphs
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