GOE 621 AIRFOIL (goe621-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 621 AIRFOIL (goe621-il) Reynolds number: 100,000 Max Cl/Cd: 51.15 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe621-il-100000.txt Download as CSV file: xf-goe621-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 621 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.2160 0.10282 0.09818 -0.0538 0.9659 0.1527
-8.000 -0.2080 0.10001 0.09537 -0.0573 0.9582 0.1585
-7.750 -0.2500 0.09762 0.09307 -0.0648 0.9442 0.1629
-7.500 -0.1911 0.09349 0.08887 -0.0631 0.9441 0.1668
-7.250 -0.1713 0.09047 0.08583 -0.0673 0.9396 0.1744
-7.000 -0.2196 0.08775 0.08318 -0.0738 0.9235 0.1795
-6.750 -0.1951 0.08583 0.08127 -0.0686 0.9187 0.1817
-6.500 -0.1782 0.08362 0.07906 -0.0681 0.9123 0.1855
-6.000 -0.3081 0.04838 0.04183 -0.0898 0.8847 0.1037
-5.750 -0.2965 0.04568 0.03889 -0.0889 0.8788 0.1032
-5.500 -0.2721 0.04267 0.03539 -0.0899 0.8748 0.1034
-5.250 -0.2539 0.04051 0.03289 -0.0895 0.8699 0.1048
-5.000 -0.2435 0.03954 0.03188 -0.0874 0.8629 0.1065
-4.750 -0.2166 0.03824 0.03040 -0.0878 0.8590 0.1086
-4.500 -0.1814 0.03667 0.02849 -0.0893 0.8561 0.1110
-4.250 -0.1768 0.03621 0.02782 -0.0859 0.8486 0.1127
-4.000 -0.1532 0.03545 0.02667 -0.0853 0.8437 0.1163
-3.750 -0.1206 0.03441 0.02565 -0.0863 0.8403 0.1216
-3.500 -0.0799 0.03356 0.02458 -0.0882 0.8379 0.1294
-3.250 -0.0844 0.03374 0.02467 -0.0834 0.8290 0.1323
-3.000 -0.0559 0.03325 0.02427 -0.0837 0.8249 0.1419
-2.750 -0.0184 0.03255 0.02360 -0.0851 0.8219 0.1573
-2.500 -0.0121 0.03271 0.02381 -0.0821 0.8145 0.1681
-2.250 0.0107 0.03255 0.02372 -0.0814 0.8092 0.1907
-2.000 0.0469 0.03216 0.02347 -0.0825 0.8054 0.2245
-1.750 0.0603 0.03246 0.02381 -0.0805 0.7981 0.2489
-1.500 0.0898 0.03226 0.02373 -0.0804 0.7906 0.2831
-1.250 0.1466 0.03131 0.02295 -0.0838 0.7863 0.3387
-1.000 0.1516 0.03168 0.02344 -0.0801 0.7738 0.3649
-0.750 0.2015 0.03080 0.02267 -0.0824 0.7698 0.4185
-0.500 0.2037 0.03151 0.02345 -0.0787 0.7590 0.4402
-0.250 0.2434 0.03093 0.02297 -0.0798 0.7544 0.4795
0.000 0.2936 0.02991 0.02204 -0.0823 0.7517 0.5235
0.250 0.2912 0.03086 0.02306 -0.0781 0.7395 0.5457
0.500 0.3406 0.02978 0.02218 -0.0805 0.7360 0.5979
0.750 0.4760 0.02700 0.02048 -0.0978 0.7364 1.0000
1.000 0.5371 0.02594 0.01911 -0.1024 0.7343 1.0000
1.250 0.5326 0.02701 0.02007 -0.0974 0.7211 1.0000
1.500 0.5888 0.02593 0.01880 -0.1009 0.7182 1.0000
1.750 0.6392 0.02506 0.01777 -0.1035 0.7144 1.0000
2.000 0.6465 0.02562 0.01827 -0.1000 0.7021 1.0000
2.250 0.7034 0.02442 0.01693 -0.1034 0.6987 1.0000
2.500 0.7111 0.02495 0.01742 -0.0999 0.6859 1.0000
2.750 0.7652 0.02384 0.01618 -0.1029 0.6812 1.0000
3.000 0.7789 0.02410 0.01641 -0.1001 0.6686 1.0000
3.250 0.8330 0.02298 0.01515 -0.1032 0.6627 1.0000
3.500 0.8472 0.02316 0.01532 -0.1004 0.6490 1.0000
3.750 0.8772 0.02284 0.01493 -0.0999 0.6378 1.0000
4.000 0.9187 0.02213 0.01409 -0.1012 0.6274 1.0000
4.250 0.9385 0.02206 0.01400 -0.0992 0.6124 1.0000
4.500 0.9621 0.02190 0.01377 -0.0978 0.5973 1.0000
4.750 0.9871 0.02172 0.01352 -0.0966 0.5818 1.0000
5.000 1.0116 0.02158 0.01328 -0.0954 0.5658 1.0000
5.250 1.0350 0.02152 0.01312 -0.0940 0.5493 1.0000
5.500 1.0574 0.02155 0.01304 -0.0926 0.5329 1.0000
5.750 1.0793 0.02165 0.01304 -0.0912 0.5168 1.0000
6.000 1.1015 0.02182 0.01308 -0.0899 0.5015 1.0000
6.250 1.1245 0.02203 0.01314 -0.0888 0.4869 1.0000
6.500 1.1442 0.02237 0.01338 -0.0872 0.4726 1.0000
6.750 1.1607 0.02283 0.01378 -0.0852 0.4588 1.0000
7.000 1.1794 0.02331 0.01418 -0.0836 0.4461 1.0000
7.250 1.2025 0.02376 0.01452 -0.0828 0.4343 1.0000
7.500 1.2229 0.02428 0.01494 -0.0815 0.4228 1.0000
7.750 1.2390 0.02492 0.01558 -0.0797 0.4118 1.0000
8.000 1.2646 0.02549 0.01601 -0.0794 0.4016 1.0000
8.250 1.2799 0.02617 0.01671 -0.0774 0.3916 1.0000
8.500 1.3011 0.02687 0.01736 -0.0765 0.3822 1.0000
8.750 1.3215 0.02755 0.01800 -0.0755 0.3727 1.0000
9.000 1.3387 0.02837 0.01885 -0.0740 0.3640 1.0000
9.250 1.3612 0.02908 0.01948 -0.0733 0.3548 1.0000
9.500 1.3741 0.02998 0.02045 -0.0712 0.3464 1.0000
9.750 1.3968 0.03072 0.02113 -0.0707 0.3375 1.0000
10.000 1.4074 0.03170 0.02218 -0.0683 0.3296 1.0000
10.250 1.4252 0.03252 0.02299 -0.0670 0.3214 1.0000
10.500 1.4419 0.03356 0.02406 -0.0656 0.3140 1.0000
10.750 1.4475 0.03452 0.02514 -0.0625 0.3067 1.0000
11.000 1.4787 0.03550 0.02600 -0.0635 0.2988 1.0000
11.250 1.4703 0.03666 0.02738 -0.0584 0.2927 1.0000
11.500 1.4967 0.03745 0.02809 -0.0585 0.2854 1.0000
11.750 1.4998 0.03877 0.02954 -0.0555 0.2795 1.0000
12.000 1.4977 0.04006 0.03100 -0.0519 0.2739 1.0000
12.250 1.5357 0.04080 0.03159 -0.0536 0.2675 1.0000
12.500 1.5276 0.04250 0.03352 -0.0494 0.2632 1.0000
12.750 1.5195 0.04424 0.03547 -0.0456 0.2588 1.0000
13.000 1.5320 0.04540 0.03669 -0.0442 0.2541 1.0000
13.250 1.5640 0.04641 0.03764 -0.0451 0.2492 1.0000
13.500 1.5381 0.04891 0.04045 -0.0400 0.2460 1.0000
13.750 1.5234 0.05134 0.04310 -0.0365 0.2425 1.0000
14.000 1.5262 0.05310 0.04496 -0.0348 0.2389 1.0000
14.250 1.5729 0.05329 0.04504 -0.0365 0.2348 1.0000
14.500 1.5469 0.05673 0.04876 -0.0328 0.2327 1.0000
14.750 1.4948 0.06205 0.05443 -0.0285 0.2309 1.0000
15.000 1.3990 0.07245 0.06522 -0.0255 0.2295 1.0000
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Polar data table (+)
Polar graphs
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