GOE 758 AIRFOIL (goe758-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 758 AIRFOIL (goe758-il) Reynolds number: 100,000 Max Cl/Cd: 45.41 at α=11.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe758-il-100000.txt Download as CSV file: xf-goe758-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 758 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2811 0.10415 0.09979 -0.0377 1.0000 0.1217
-8.750 -0.3098 0.10448 0.10028 -0.0341 1.0000 0.1235
-8.500 -0.3492 0.10394 0.09991 -0.0447 0.9892 0.1257
-8.250 -0.2993 0.09741 0.09332 -0.0413 0.9890 0.1289
-8.000 -0.2659 0.09327 0.08913 -0.0460 0.9825 0.1361
-7.750 -0.2752 0.08789 0.08381 -0.0619 0.9616 0.1428
-7.500 -0.2226 0.08422 0.08007 -0.0590 0.9610 0.1495
-7.250 -0.2191 0.07815 0.07399 -0.0742 0.9436 0.1594
-7.000 -0.1755 0.07484 0.07064 -0.0739 0.9415 0.1654
-6.750 -0.1606 0.06939 0.06513 -0.0847 0.9271 0.1768
-6.500 -0.1471 0.06492 0.06055 -0.0931 0.9126 0.1912
-6.250 -0.1110 0.06245 0.05809 -0.0915 0.9059 0.1971
-6.000 -0.0901 0.05915 0.05472 -0.0951 0.8951 0.2124
-5.750 -0.0768 0.05660 0.05211 -0.0964 0.8817 0.2276
-5.500 -0.0899 0.04157 0.03534 -0.1101 0.8641 0.1250
-5.250 -0.0722 0.03672 0.03008 -0.1097 0.8541 0.1057
-5.000 -0.0476 0.03349 0.02589 -0.1093 0.8464 0.0948
-4.750 -0.0284 0.03152 0.02371 -0.1082 0.8362 0.0930
-4.500 0.0003 0.02950 0.02133 -0.1082 0.8297 0.0913
-4.250 0.0208 0.02832 0.01987 -0.1070 0.8201 0.0908
-4.000 0.0502 0.02709 0.01833 -0.1068 0.8138 0.0924
-3.750 0.0727 0.02630 0.01733 -0.1058 0.8050 0.0934
-3.500 0.1015 0.02525 0.01608 -0.1054 0.7983 0.0940
-3.250 0.1270 0.02455 0.01522 -0.1047 0.7911 0.0950
-3.000 0.1526 0.02372 0.01436 -0.1040 0.7836 0.0967
-2.750 0.1818 0.02280 0.01349 -0.1038 0.7785 0.1001
-2.500 0.2008 0.02257 0.01331 -0.1023 0.7694 0.1048
-2.250 0.2292 0.02191 0.01262 -0.1019 0.7641 0.1134
-2.000 0.2483 0.02176 0.01249 -0.1004 0.7556 0.1249
-1.750 0.2727 0.02080 0.01183 -0.0996 0.7497 0.1708
-1.500 0.2863 0.01942 0.01205 -0.0970 0.7431 0.5551
-1.250 0.3052 0.01922 0.01219 -0.0945 0.7359 0.6770
-1.000 0.3368 0.01859 0.01194 -0.0931 0.7314 0.8200
-0.750 0.4448 0.01833 0.01164 -0.1076 0.7229 0.9946
-0.500 0.4711 0.01830 0.01133 -0.1078 0.7168 1.0000
-0.250 0.4867 0.01869 0.01156 -0.1061 0.7087 1.0000
0.000 0.5106 0.01879 0.01145 -0.1053 0.7022 1.0000
0.250 0.5315 0.01910 0.01161 -0.1042 0.6951 1.0000
0.500 0.5540 0.01934 0.01170 -0.1032 0.6879 1.0000
0.750 0.5811 0.01946 0.01163 -0.1028 0.6821 1.0000
1.000 0.5994 0.01994 0.01204 -0.1014 0.6736 1.0000
1.250 0.6296 0.01994 0.01186 -0.1014 0.6683 1.0000
1.500 0.6463 0.02055 0.01244 -0.0997 0.6593 1.0000
1.750 0.6750 0.02064 0.01238 -0.0995 0.6533 1.0000
2.000 0.6940 0.02119 0.01291 -0.0982 0.6451 1.0000
2.250 0.7208 0.02139 0.01299 -0.0978 0.6383 1.0000
2.500 0.7431 0.02184 0.01340 -0.0969 0.6309 1.0000
2.750 0.7667 0.02220 0.01370 -0.0961 0.6231 1.0000
3.000 0.7944 0.02244 0.01384 -0.0959 0.6169 1.0000
3.250 0.8126 0.02304 0.01447 -0.0944 0.6078 1.0000
3.500 0.8451 0.02308 0.01437 -0.0948 0.6024 1.0000
3.750 0.8584 0.02391 0.01529 -0.0928 0.5924 1.0000
4.000 0.8899 0.02395 0.01523 -0.0930 0.5867 1.0000
4.250 0.9036 0.02480 0.01617 -0.0911 0.5771 1.0000
4.500 0.9338 0.02488 0.01617 -0.0911 0.5711 1.0000
4.750 0.9489 0.02568 0.01705 -0.0894 0.5620 1.0000
5.000 0.9775 0.02580 0.01713 -0.0892 0.5556 1.0000
5.250 0.9947 0.02652 0.01792 -0.0877 0.5475 1.0000
5.500 1.0201 0.02678 0.01817 -0.0872 0.5404 1.0000
5.750 1.0428 0.02723 0.01865 -0.0864 0.5336 1.0000
6.000 1.0621 0.02777 0.01925 -0.0852 0.5256 1.0000
6.250 1.0979 0.02760 0.01900 -0.0860 0.5211 1.0000
6.500 1.1026 0.02888 0.02049 -0.0831 0.5115 1.0000
6.750 1.1369 0.02869 0.02025 -0.0836 0.5065 1.0000
7.000 1.1438 0.02994 0.02166 -0.0810 0.4979 1.0000
7.250 1.1730 0.03002 0.02175 -0.0810 0.4924 1.0000
7.500 1.1884 0.03088 0.02273 -0.0794 0.4857 1.0000
7.750 1.2069 0.03150 0.02343 -0.0782 0.4788 1.0000
8.000 1.2465 0.03111 0.02300 -0.0794 0.4747 1.0000
8.250 1.2389 0.03316 0.02529 -0.0753 0.4661 1.0000
8.500 1.2750 0.03279 0.02494 -0.0760 0.4609 1.0000
8.750 1.2796 0.03412 0.02642 -0.0732 0.4534 1.0000
9.000 1.3068 0.03410 0.02646 -0.0728 0.4470 1.0000
9.250 1.3345 0.03425 0.02668 -0.0726 0.4412 1.0000
9.500 1.3332 0.03578 0.02839 -0.0692 0.4337 1.0000
9.750 1.3909 0.03426 0.02681 -0.0723 0.4283 1.0000
10.000 1.3662 0.03688 0.02970 -0.0662 0.4203 1.0000
10.250 1.4281 0.03455 0.02729 -0.0693 0.4117 1.0000
10.500 1.4174 0.03612 0.02908 -0.0645 0.4034 1.0000
10.750 1.4470 0.03496 0.02790 -0.0638 0.3918 1.0000
11.000 1.4767 0.03379 0.02670 -0.0630 0.3792 1.0000
11.250 1.4996 0.03302 0.02587 -0.0616 0.3662 1.0000
11.500 1.4824 0.03426 0.02731 -0.0556 0.3581 1.0000
11.750 1.4889 0.03435 0.02743 -0.0526 0.3467 1.0000
12.000 1.4947 0.03448 0.02754 -0.0496 0.3345 1.0000
12.250 1.4853 0.03577 0.02898 -0.0457 0.3248 1.0000
12.500 1.4781 0.03715 0.03049 -0.0425 0.3147 1.0000
12.750 1.4748 0.03837 0.03178 -0.0398 0.3032 1.0000
13.000 1.4673 0.04003 0.03349 -0.0373 0.2907 1.0000
13.250 1.4475 0.04317 0.03685 -0.0350 0.2798 1.0000
13.500 1.4316 0.04632 0.04011 -0.0335 0.2669 1.0000
13.750 1.4123 0.05012 0.04401 -0.0324 0.2512 1.0000
14.000 1.3911 0.05450 0.04839 -0.0319 0.2321 1.0000
14.250 1.3666 0.05990 0.05387 -0.0321 0.2125 1.0000
14.500 1.3404 0.06575 0.05964 -0.0325 0.1859 1.0000
14.750 1.3109 0.07233 0.06601 -0.0334 0.1551 1.0000
15.000 1.2830 0.07909 0.07256 -0.0346 0.1322 1.0000
15.250 1.2552 0.08621 0.07947 -0.0362 0.1151 1.0000
15.500 1.2312 0.09301 0.08608 -0.0377 0.1023 1.0000
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