GOE 403 AIRFOIL (goe403-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 403 AIRFOIL (goe403-il) Reynolds number: 100,000 Max Cl/Cd: 59.26 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe403-il-100000.txt Download as CSV file: xf-goe403-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 403 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3444 0.10009 0.09535 -0.0271 1.0000 0.0638
-7.750 -0.3524 0.09923 0.09462 -0.0284 1.0000 0.0644
-7.500 -0.3561 0.09798 0.09347 -0.0321 1.0000 0.0647
-7.250 -0.3534 0.09603 0.09158 -0.0371 1.0000 0.0650
-7.000 -0.3386 0.08838 0.08393 -0.0253 1.0000 0.0703
-6.750 -0.3370 0.08596 0.08158 -0.0259 1.0000 0.0733
-6.500 -0.3368 0.08399 0.07970 -0.0287 1.0000 0.0763
-6.250 -0.3328 0.08307 0.07880 -0.0375 1.0000 0.0779
-6.000 -0.3326 0.07884 0.07466 -0.0358 1.0000 0.0789
-5.750 -0.3331 0.07551 0.07140 -0.0302 1.0000 0.0808
-5.500 -0.3324 0.07315 0.06908 -0.0283 1.0000 0.0835
-5.250 -0.3297 0.07083 0.06679 -0.0286 1.0000 0.0868
-5.000 -0.3067 0.06831 0.06403 -0.0402 1.0000 0.0920
-4.750 -0.3098 0.06460 0.06047 -0.0351 1.0000 0.0934
-4.500 -0.3058 0.06204 0.05791 -0.0327 1.0000 0.0964
-4.250 -0.2734 0.05879 0.05432 -0.0418 1.0000 0.1060
-4.000 -0.2720 0.05555 0.05123 -0.0381 1.0000 0.1083
-3.750 -0.2473 0.05261 0.04807 -0.0422 1.0000 0.1205
-3.500 -0.2403 0.05015 0.04570 -0.0397 1.0000 0.1267
-3.250 -0.1941 0.04599 0.04131 -0.0468 0.9945 0.1417
-3.000 -0.1446 0.04196 0.03695 -0.0543 0.9872 0.1632
-2.750 -0.1050 0.03900 0.03387 -0.0582 0.9802 0.1942
-2.500 -0.0328 0.03121 0.02470 -0.0677 0.9752 0.1211
-2.250 0.0170 0.02752 0.02042 -0.0720 0.9697 0.1119
-2.000 0.0627 0.02472 0.01659 -0.0745 0.9614 0.1052
-1.750 0.1100 0.02254 0.01406 -0.0783 0.9550 0.1080
-1.500 0.1518 0.02157 0.01282 -0.0809 0.9445 0.1182
-1.250 0.1936 0.02028 0.01140 -0.0834 0.9345 0.1260
-1.000 0.2413 0.01906 0.01009 -0.0868 0.9267 0.1403
-0.750 0.2853 0.01794 0.00903 -0.0895 0.9168 0.1744
-0.500 0.3266 0.01697 0.00837 -0.0919 0.9059 0.2435
-0.250 0.3861 0.01412 0.00751 -0.0974 0.9015 1.0000
0.000 0.4264 0.01396 0.00699 -0.0991 0.8882 1.0000
0.250 0.4643 0.01380 0.00662 -0.1004 0.8741 1.0000
0.500 0.4972 0.01372 0.00637 -0.1007 0.8580 1.0000
0.750 0.5271 0.01371 0.00622 -0.1003 0.8401 1.0000
1.000 0.5564 0.01373 0.00611 -0.0999 0.8228 1.0000
1.250 0.5849 0.01378 0.00604 -0.0993 0.8058 1.0000
1.500 0.6103 0.01394 0.00612 -0.0983 0.7870 1.0000
1.750 0.6357 0.01410 0.00620 -0.0974 0.7688 1.0000
2.000 0.6615 0.01425 0.00627 -0.0965 0.7520 1.0000
2.250 0.6875 0.01441 0.00635 -0.0957 0.7362 1.0000
2.500 0.7126 0.01460 0.00655 -0.0948 0.7200 1.0000
2.750 0.7378 0.01481 0.00674 -0.0940 0.7042 1.0000
3.000 0.7633 0.01503 0.00695 -0.0933 0.6895 1.0000
3.250 0.7889 0.01526 0.00719 -0.0926 0.6753 1.0000
3.500 0.8146 0.01552 0.00746 -0.0919 0.6618 1.0000
3.750 0.8393 0.01560 0.00757 -0.0907 0.6431 1.0000
4.000 0.8618 0.01544 0.00728 -0.0886 0.6139 1.0000
4.250 0.8836 0.01544 0.00717 -0.0866 0.5833 1.0000
4.500 0.9064 0.01563 0.00736 -0.0852 0.5586 1.0000
4.750 0.9265 0.01577 0.00745 -0.0831 0.5218 1.0000
5.000 0.9452 0.01595 0.00762 -0.0808 0.4768 1.0000
5.250 0.9615 0.01626 0.00775 -0.0781 0.4068 1.0000
5.500 0.9717 0.01757 0.00815 -0.0750 0.2395 1.0000
5.750 0.9741 0.02082 0.01005 -0.0718 0.0603 1.0000
6.000 0.9918 0.02211 0.01145 -0.0700 0.0497 1.0000
6.250 1.0085 0.02341 0.01296 -0.0681 0.0466 1.0000
6.500 1.0245 0.02465 0.01442 -0.0661 0.0450 1.0000
6.750 1.0384 0.02603 0.01596 -0.0637 0.0440 1.0000
7.000 1.0516 0.02754 0.01762 -0.0613 0.0435 1.0000
7.250 1.0679 0.02925 0.01934 -0.0592 0.0434 1.0000
7.500 1.0917 0.03126 0.02133 -0.0580 0.0437 1.0000
7.750 1.1191 0.03338 0.02350 -0.0574 0.0426 1.0000
8.000 1.1469 0.03573 0.02597 -0.0568 0.0413 1.0000
8.250 1.1775 0.03885 0.02934 -0.0563 0.0438 1.0000
8.500 1.2071 0.04349 0.03415 -0.0561 0.0468 1.0000
8.750 1.2285 0.04467 0.03602 -0.0534 0.0526 1.0000
9.000 1.2591 0.04923 0.04093 -0.0525 0.0617 1.0000
9.250 1.2842 0.05740 0.04988 -0.0505 0.0844 1.0000
9.500 1.2789 0.06496 0.05933 -0.0448 0.1356 1.0000
9.750 1.2384 0.06916 0.06423 -0.0408 0.1400 1.0000
10.000 1.2046 0.07760 0.07307 -0.0400 0.1588 1.0000
10.250 1.1741 0.08208 0.07768 -0.0383 0.1589 1.0000
10.500 1.1431 0.08773 0.08341 -0.0389 0.1594 1.0000
10.750 1.1133 0.09460 0.09033 -0.0416 0.1599 1.0000
11.000 1.0824 0.10299 0.09873 -0.0464 0.1602 1.0000
11.250 1.0483 0.11363 0.10933 -0.0539 0.1604 1.0000
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Polar data table (+)
Polar graphs
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