Bambino 6 (bambino6-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: Bambino 6 (bambino6-il) Reynolds number: 50,000 Max Cl/Cd: 30.18 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-bambino6-il-50000-n5.txt Download as CSV file: xf-bambino6-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: Bambino 6
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4105 0.09992 0.09334 -0.0417 1.0000 0.0637
-9.250 -0.4177 0.09578 0.08929 -0.0429 1.0000 0.0635
-9.000 -0.4292 0.09126 0.08488 -0.0445 1.0000 0.0637
-8.750 -0.4433 0.08687 0.08060 -0.0459 1.0000 0.0635
-8.500 -0.4600 0.08307 0.07689 -0.0458 1.0000 0.0632
-8.250 -0.4804 0.07984 0.07375 -0.0439 1.0000 0.0630
-8.000 -0.5024 0.07667 0.07064 -0.0411 1.0000 0.0631
-7.750 -0.5225 0.07320 0.06718 -0.0383 1.0000 0.0635
-7.500 -0.5416 0.06979 0.06374 -0.0350 1.0000 0.0638
-7.250 -0.5624 0.06610 0.05993 -0.0312 1.0000 0.0648
-7.000 -0.5823 0.06225 0.05587 -0.0270 1.0000 0.0657
-6.750 -0.6034 0.05814 0.05134 -0.0221 1.0000 0.0668
-6.500 -0.5884 0.05839 0.05190 -0.0200 1.0000 0.0718
-6.250 -0.5956 0.05535 0.04863 -0.0161 1.0000 0.0735
-6.000 -0.6023 0.05219 0.04512 -0.0121 1.0000 0.0761
-5.750 -0.6118 0.04854 0.04085 -0.0074 1.0000 0.0800
-5.500 -0.5866 0.04705 0.03936 -0.0081 0.9944 0.0846
-5.250 -0.5625 0.04338 0.03508 -0.0088 0.9857 0.0872
-5.000 -0.5373 0.04000 0.03097 -0.0090 0.9768 0.0901
-4.750 -0.5086 0.03812 0.02874 -0.0099 0.9675 0.0949
-4.500 -0.4779 0.03684 0.02716 -0.0109 0.9583 0.1010
-4.250 -0.4432 0.03459 0.02429 -0.0122 0.9504 0.1042
-4.000 -0.4112 0.03324 0.02275 -0.0131 0.9406 0.1067
-3.750 -0.3718 0.03202 0.02127 -0.0154 0.9333 0.1108
-3.500 -0.3359 0.03084 0.01977 -0.0168 0.9237 0.1157
-3.250 -0.2997 0.03016 0.01898 -0.0185 0.9148 0.1233
-3.000 -0.2569 0.02946 0.01808 -0.0213 0.9070 0.1343
-2.750 -0.2093 0.02868 0.01705 -0.0248 0.8998 0.1454
-2.500 -0.1615 0.02791 0.01621 -0.0286 0.8929 0.1613
-2.250 -0.1177 0.02713 0.01549 -0.0318 0.8860 0.1858
-2.000 -0.0794 0.02633 0.01481 -0.0339 0.8778 0.2158
-1.750 -0.0467 0.02572 0.01437 -0.0350 0.8689 0.2534
-1.500 0.0588 0.02372 0.01496 -0.0483 0.8750 0.8427
-1.250 0.0993 0.02432 0.01524 -0.0496 0.8657 0.9199
-1.000 0.2666 0.02414 0.01462 -0.0767 0.8756 1.0000
-0.750 0.2980 0.02411 0.01445 -0.0777 0.8638 1.0000
-0.500 0.3298 0.02409 0.01429 -0.0787 0.8528 1.0000
-0.250 0.3646 0.02396 0.01404 -0.0802 0.8423 1.0000
0.000 0.3964 0.02367 0.01363 -0.0806 0.8242 1.0000
0.250 0.4289 0.02324 0.01307 -0.0807 0.8029 1.0000
0.500 0.4566 0.02288 0.01259 -0.0799 0.7786 1.0000
0.750 0.4815 0.02270 0.01231 -0.0788 0.7570 1.0000
1.000 0.5066 0.02257 0.01209 -0.0779 0.7384 1.0000
1.250 0.5286 0.02265 0.01215 -0.0768 0.7249 1.0000
1.500 0.5507 0.02276 0.01228 -0.0758 0.7130 1.0000
1.750 0.5741 0.02286 0.01239 -0.0749 0.7024 1.0000
2.000 0.5991 0.02291 0.01246 -0.0744 0.6925 1.0000
2.250 0.6200 0.02309 0.01272 -0.0731 0.6816 1.0000
2.500 0.6422 0.02315 0.01279 -0.0719 0.6669 1.0000
2.750 0.6644 0.02316 0.01277 -0.0705 0.6493 1.0000
3.000 0.6827 0.02318 0.01272 -0.0681 0.6228 1.0000
3.250 0.6977 0.02323 0.01258 -0.0650 0.5858 1.0000
3.500 0.7067 0.02344 0.01272 -0.0612 0.5460 1.0000
3.750 0.7150 0.02369 0.01291 -0.0574 0.5004 1.0000
4.000 0.7217 0.02404 0.01289 -0.0533 0.4032 1.0000
4.250 0.7009 0.02665 0.01355 -0.0456 0.1650 1.0000
4.500 0.7023 0.02804 0.01448 -0.0419 0.1116 1.0000
4.750 0.7071 0.02904 0.01522 -0.0385 0.0775 1.0000
5.000 0.7145 0.02974 0.01582 -0.0354 0.0733 1.0000
5.250 0.7206 0.03047 0.01647 -0.0322 0.0691 1.0000
5.500 0.7258 0.03119 0.01715 -0.0287 0.0656 1.0000
5.750 0.7312 0.03181 0.01782 -0.0253 0.0631 1.0000
6.000 0.7336 0.03245 0.01852 -0.0214 0.0613 1.0000
6.250 0.7362 0.03304 0.01921 -0.0176 0.0604 1.0000
6.500 0.7378 0.03372 0.01994 -0.0137 0.0592 1.0000
6.750 0.7394 0.03449 0.02074 -0.0100 0.0579 1.0000
7.000 0.7402 0.03541 0.02167 -0.0064 0.0561 1.0000
7.250 0.7422 0.03635 0.02267 -0.0031 0.0551 1.0000
7.500 0.7496 0.03702 0.02340 -0.0007 0.0526 1.0000
7.750 0.7563 0.03782 0.02427 0.0017 0.0493 1.0000
8.000 0.7627 0.03873 0.02525 0.0040 0.0482 1.0000
8.250 0.7696 0.03967 0.02631 0.0062 0.0471 1.0000
8.500 0.7767 0.04066 0.02737 0.0081 0.0464 1.0000
8.750 0.7838 0.04174 0.02852 0.0099 0.0454 1.0000
9.000 0.7918 0.04279 0.02962 0.0116 0.0444 1.0000
9.250 0.8015 0.04375 0.03071 0.0130 0.0437 1.0000
9.500 0.8125 0.04465 0.03176 0.0142 0.0416 1.0000
9.750 0.8225 0.04567 0.03293 0.0154 0.0402 1.0000
10.000 0.8315 0.04685 0.03425 0.0166 0.0392 1.0000
10.250 0.8406 0.04807 0.03562 0.0177 0.0386 1.0000
10.500 0.8498 0.04932 0.03701 0.0187 0.0381 1.0000
10.750 0.8584 0.05069 0.03860 0.0197 0.0377 1.0000
11.000 0.8673 0.05207 0.04014 0.0205 0.0375 1.0000
11.250 0.8761 0.05350 0.04174 0.0213 0.0374 1.0000
11.500 0.8847 0.05498 0.04339 0.0219 0.0372 1.0000
11.750 0.9009 0.05589 0.04483 0.0234 0.0246 1.0000
12.000 0.8982 0.05854 0.04719 0.0232 0.0235 1.0000
12.250 0.9052 0.06030 0.04901 0.0234 0.0230 1.0000
12.500 0.9105 0.06233 0.05113 0.0236 0.0227 1.0000
12.750 0.9143 0.06462 0.05354 0.0238 0.0224 1.0000
13.000 0.9147 0.06743 0.05648 0.0240 0.0221 1.0000
13.250 0.9181 0.06986 0.05907 0.0239 0.0221 1.0000
13.500 0.9147 0.07335 0.06274 0.0237 0.0218 1.0000
13.750 0.9127 0.07677 0.06634 0.0233 0.0216 1.0000
14.000 0.9104 0.08028 0.07003 0.0227 0.0216 1.0000
14.250 0.9062 0.08422 0.07416 0.0218 0.0215 1.0000
14.500 0.8991 0.08884 0.07897 0.0206 0.0214 1.0000
14.750 0.8975 0.09261 0.08292 0.0194 0.0215 1.0000
15.000 0.8860 0.09833 0.08885 0.0175 0.0213 1.0000
15.250 0.8817 0.10289 0.09359 0.0158 0.0215 1.0000
15.500 0.8734 0.10842 0.09931 0.0136 0.0215 1.0000
15.750 0.8634 0.11452 0.10559 0.0112 0.0215 1.0000
16.000 0.8546 0.12052 0.11176 0.0087 0.0216 1.0000
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Polar data table (+)
Polar graphs
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