NACA 63-209 (naca63209-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 63-209 (naca63209-il) Reynolds number: 100,000 Max Cl/Cd: 47.33 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca63209-il-100000.txt Download as CSV file: xf-naca63209-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63-209
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4512 0.09996 0.09529 -0.0110 1.0000 0.1147
-9.500 -0.4675 0.09585 0.09127 -0.0149 1.0000 0.1194
-9.250 -0.4976 0.09133 0.08686 -0.0213 1.0000 0.1204
-9.000 -0.4542 0.08739 0.08281 -0.0148 1.0000 0.1287
-8.750 -0.4792 0.08275 0.07828 -0.0200 1.0000 0.1336
-8.500 -0.4643 0.07835 0.07388 -0.0181 1.0000 0.1387
-8.250 -0.4698 0.07430 0.06988 -0.0198 1.0000 0.1456
-8.000 -0.5116 0.06867 0.06438 -0.0274 1.0000 0.1478
-7.750 -0.4787 0.06560 0.06129 -0.0220 1.0000 0.1582
-7.500 -0.5257 0.05930 0.05501 -0.0308 1.0000 0.1618
-7.250 -0.5749 0.06569 0.06105 -0.0311 1.0000 0.1600
-7.000 -0.5669 0.06211 0.05750 -0.0306 1.0000 0.1703
-6.750 -0.5618 0.05866 0.05402 -0.0311 1.0000 0.1843
-6.500 -0.5618 0.05525 0.05048 -0.0324 1.0000 0.2066
-6.000 -0.5224 0.03708 0.02982 -0.0378 1.0000 0.0780
-5.750 -0.5041 0.03341 0.02592 -0.0369 1.0000 0.0757
-5.500 -0.4842 0.03038 0.02251 -0.0358 1.0000 0.0739
-5.250 -0.4624 0.02738 0.01893 -0.0343 1.0000 0.0696
-5.000 -0.4400 0.02517 0.01626 -0.0328 1.0000 0.0681
-4.750 -0.4182 0.02329 0.01418 -0.0315 1.0000 0.0687
-4.500 -0.3974 0.02190 0.01273 -0.0303 1.0000 0.0733
-4.250 -0.3760 0.02072 0.01135 -0.0289 1.0000 0.0775
-4.000 -0.3551 0.01927 0.00986 -0.0274 1.0000 0.0807
-3.750 -0.3356 0.01805 0.00878 -0.0260 1.0000 0.0869
-3.500 -0.3162 0.01708 0.00789 -0.0248 1.0000 0.0993
-3.250 -0.2960 0.01610 0.00698 -0.0237 1.0000 0.1177
-3.000 -0.2802 0.01279 0.00617 -0.0227 1.0000 0.5602
-2.750 -0.2704 0.01288 0.00661 -0.0179 1.0000 0.7022
-2.500 -0.2599 0.01313 0.00692 -0.0136 1.0000 0.7586
-2.250 -0.2505 0.01334 0.00714 -0.0093 1.0000 0.7974
-2.000 -0.2498 0.01359 0.00746 -0.0028 1.0000 0.8459
-1.750 -0.2539 0.01371 0.00767 0.0049 1.0000 0.8944
-1.500 -0.2336 0.01382 0.00774 0.0079 1.0000 0.9502
-1.250 -0.1717 0.01398 0.00764 0.0007 1.0000 0.9752
-1.000 -0.1022 0.01414 0.00758 -0.0085 0.9971 0.9903
-0.750 -0.0441 0.01426 0.00752 -0.0160 0.9902 1.0000
-0.500 0.0012 0.01438 0.00752 -0.0213 0.9796 1.0000
-0.250 0.0476 0.01451 0.00756 -0.0264 0.9699 1.0000
0.000 0.0871 0.01460 0.00758 -0.0301 0.9584 1.0000
0.250 0.1266 0.01472 0.00765 -0.0335 0.9474 1.0000
0.500 0.1723 0.01484 0.00775 -0.0379 0.9385 1.0000
0.750 0.2167 0.01493 0.00784 -0.0418 0.9290 1.0000
1.000 0.2550 0.01504 0.00796 -0.0445 0.9182 1.0000
1.250 0.2949 0.01513 0.00809 -0.0472 0.9083 1.0000
1.500 0.3372 0.01517 0.00820 -0.0501 0.8993 1.0000
1.750 0.3675 0.01531 0.00839 -0.0509 0.8868 1.0000
2.000 0.3974 0.01546 0.00860 -0.0514 0.8745 1.0000
2.250 0.4273 0.01559 0.00883 -0.0517 0.8621 1.0000
2.500 0.4566 0.01569 0.00902 -0.0518 0.8493 1.0000
2.750 0.4849 0.01575 0.00917 -0.0514 0.8356 1.0000
3.000 0.5120 0.01573 0.00926 -0.0504 0.8201 1.0000
3.250 0.5387 0.01547 0.00911 -0.0487 0.8014 1.0000
3.500 0.5615 0.01488 0.00855 -0.0453 0.7730 1.0000
3.750 0.5816 0.01409 0.00772 -0.0410 0.7318 1.0000
4.000 0.6032 0.01370 0.00733 -0.0381 0.6913 1.0000
4.250 0.6253 0.01350 0.00718 -0.0356 0.6443 1.0000
4.500 0.6409 0.01354 0.00679 -0.0316 0.5063 1.0000
4.750 0.6375 0.01737 0.00807 -0.0270 0.1274 1.0000
5.000 0.6558 0.01899 0.00945 -0.0256 0.0973 1.0000
5.250 0.6766 0.02046 0.01084 -0.0243 0.0849 1.0000
5.500 0.6996 0.02195 0.01229 -0.0234 0.0751 1.0000
5.750 0.7247 0.02393 0.01414 -0.0229 0.0695 1.0000
6.000 0.7528 0.02605 0.01638 -0.0224 0.0670 1.0000
6.250 0.7807 0.02814 0.01875 -0.0218 0.0652 1.0000
6.500 0.8062 0.03009 0.02097 -0.0211 0.0614 1.0000
6.750 0.8310 0.03269 0.02393 -0.0203 0.0605 1.0000
7.000 0.8537 0.03610 0.02788 -0.0191 0.0623 1.0000
7.250 0.8737 0.04013 0.03242 -0.0179 0.0654 1.0000
7.500 0.8907 0.04518 0.03832 -0.0158 0.0760 1.0000
10.250 0.8097 0.11192 0.10746 -0.0317 0.1352 1.0000
10.500 0.7782 0.11863 0.11405 -0.0405 0.1317 1.0000
10.750 0.6603 0.12065 0.11642 -0.0359 0.1387 1.0000
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Polar data table (+)
Polar graphs
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