GOE 386 AIRFOIL (goe386-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: GOE 386 AIRFOIL (goe386-il) Reynolds number: 500,000 Max Cl/Cd: 88.74 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe386-il-500000.txt Download as CSV file: xf-goe386-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 386 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -0.6886 0.05692 0.05327 -0.1073 0.9950 0.0531
-14.500 -0.7081 0.04834 0.04442 -0.1185 0.9906 0.0533
-14.250 -0.7059 0.04406 0.04000 -0.1243 0.9845 0.0536
-14.000 -0.6953 0.04107 0.03689 -0.1285 0.9792 0.0540
-13.750 -0.6898 0.03850 0.03420 -0.1309 0.9702 0.0543
-13.500 -0.6834 0.03629 0.03184 -0.1323 0.9617 0.0547
-13.250 -0.6836 0.03452 0.02991 -0.1313 0.9495 0.0550
-13.000 -0.6845 0.03304 0.02827 -0.1291 0.9380 0.0554
-12.500 -0.6757 0.03031 0.02514 -0.1251 0.9178 0.0564
-12.250 -0.6668 0.02915 0.02372 -0.1233 0.9091 0.0570
-12.000 -0.6558 0.02802 0.02240 -0.1216 0.8994 0.0575
-11.750 -0.6361 0.02695 0.02130 -0.1208 0.8913 0.0580
-11.500 -0.6153 0.02632 0.02066 -0.1200 0.8822 0.0585
-11.250 -0.5945 0.02573 0.02001 -0.1191 0.8725 0.0589
-11.000 -0.5732 0.02511 0.01933 -0.1183 0.8624 0.0595
-10.750 -0.5520 0.02448 0.01861 -0.1174 0.8510 0.0600
-10.500 -0.5309 0.02380 0.01783 -0.1165 0.8383 0.0607
-10.250 -0.5099 0.02313 0.01699 -0.1156 0.8240 0.0614
-10.000 -0.4889 0.02251 0.01618 -0.1145 0.8061 0.0621
-9.750 -0.4677 0.02205 0.01549 -0.1134 0.7837 0.0627
-9.500 -0.4459 0.02117 0.01446 -0.1126 0.7562 0.0634
-9.250 -0.4230 0.02066 0.01383 -0.1118 0.7265 0.0640
-9.000 -0.3999 0.02034 0.01337 -0.1110 0.7008 0.0647
-8.750 -0.3763 0.02003 0.01293 -0.1102 0.6809 0.0655
-8.500 -0.3520 0.01968 0.01246 -0.1096 0.6659 0.0662
-8.250 -0.3274 0.01931 0.01197 -0.1090 0.6545 0.0671
-8.000 -0.3027 0.01900 0.01151 -0.1085 0.6446 0.0679
-7.750 -0.2774 0.01878 0.01114 -0.1079 0.6367 0.0686
-7.500 -0.2520 0.01808 0.01041 -0.1076 0.6298 0.0694
-7.250 -0.2264 0.01761 0.00994 -0.1072 0.6234 0.0703
-7.000 -0.2004 0.01733 0.00960 -0.1069 0.6175 0.0713
-6.750 -0.1738 0.01700 0.00927 -0.1066 0.6130 0.0724
-6.500 -0.1472 0.01671 0.00893 -0.1063 0.6080 0.0733
-6.250 -0.1206 0.01648 0.00861 -0.1059 0.6032 0.0743
-6.000 -0.0937 0.01637 0.00839 -0.1056 0.5983 0.0750
-5.750 -0.0680 0.01576 0.00781 -0.1053 0.5945 0.0762
-5.500 -0.0416 0.01536 0.00746 -0.1050 0.5905 0.0774
-5.250 -0.0150 0.01509 0.00719 -0.1047 0.5862 0.0786
-5.000 0.0118 0.01487 0.00693 -0.1044 0.5819 0.0799
-4.750 0.0388 0.01472 0.00670 -0.1041 0.5776 0.0810
-4.500 0.0665 0.01461 0.00654 -0.1039 0.5741 0.0819
-4.250 0.0922 0.01415 0.00613 -0.1035 0.5714 0.0834
-4.000 0.1187 0.01386 0.00587 -0.1032 0.5677 0.0850
-3.750 0.1456 0.01364 0.00565 -0.1029 0.5639 0.0866
-3.500 0.1729 0.01349 0.00547 -0.1027 0.5605 0.0881
-3.250 0.2006 0.01340 0.00533 -0.1025 0.5574 0.0894
-3.000 0.2276 0.01322 0.00513 -0.1023 0.5536 0.0915
-2.750 0.2546 0.01300 0.00495 -0.1021 0.5508 0.0938
-2.500 0.2821 0.01284 0.00480 -0.1018 0.5472 0.0964
-2.250 0.3095 0.01268 0.00467 -0.1016 0.5438 0.0997
-2.000 0.3371 0.01255 0.00456 -0.1015 0.5408 0.1045
-1.750 0.3644 0.01239 0.00449 -0.1013 0.5379 0.1207
-1.500 0.3921 0.01232 0.00452 -0.1013 0.5347 0.1588
-1.250 0.4203 0.01228 0.00456 -0.1012 0.5318 0.1786
-1.000 0.4481 0.01221 0.00456 -0.1011 0.5290 0.1933
-0.750 0.4760 0.01218 0.00456 -0.1010 0.5257 0.2043
-0.500 0.5037 0.01212 0.00455 -0.1009 0.5224 0.2151
-0.250 0.5316 0.01211 0.00454 -0.1008 0.5191 0.2258
0.000 0.5594 0.01211 0.00455 -0.1007 0.5158 0.2375
0.250 0.5876 0.01216 0.00461 -0.1007 0.5121 0.2496
0.500 0.6149 0.01209 0.00462 -0.1005 0.5094 0.2643
0.750 0.6420 0.01201 0.00464 -0.1003 0.5059 0.2851
1.000 0.6688 0.01191 0.00465 -0.1001 0.5020 0.3162
1.250 0.6952 0.01181 0.00466 -0.0998 0.4979 0.3577
1.500 0.7216 0.01175 0.00472 -0.0995 0.4934 0.4097
1.750 0.7471 0.01156 0.00478 -0.0991 0.4897 0.4801
2.000 0.7713 0.01126 0.00485 -0.0985 0.4854 0.5893
2.250 0.7931 0.01091 0.00496 -0.0972 0.4808 0.7273
2.500 0.8127 0.01071 0.00510 -0.0951 0.4761 0.8510
2.750 0.8395 0.01075 0.00527 -0.0943 0.4711 0.9316
3.000 0.8809 0.01085 0.00539 -0.0969 0.4644 0.9708
3.250 0.9234 0.01103 0.00548 -0.1000 0.4568 0.9897
3.500 0.9724 0.01118 0.00560 -0.1044 0.4478 0.9986
3.750 0.9939 0.01129 0.00565 -0.1033 0.4388 1.0000
4.000 1.0106 0.01140 0.00572 -0.1011 0.4296 1.0000
4.250 1.0246 0.01156 0.00580 -0.0985 0.4187 1.0000
4.500 1.0409 0.01173 0.00591 -0.0963 0.4057 1.0000
4.750 1.0554 0.01198 0.00607 -0.0938 0.3925 1.0000
5.000 1.0672 0.01229 0.00628 -0.0909 0.3800 1.0000
5.250 1.0812 0.01264 0.00654 -0.0884 0.3687 1.0000
5.500 1.0976 0.01300 0.00684 -0.0865 0.3597 1.0000
5.750 1.1135 0.01343 0.00718 -0.0846 0.3516 1.0000
6.000 1.1314 0.01382 0.00753 -0.0831 0.3452 1.0000
6.250 1.1505 0.01420 0.00788 -0.0818 0.3397 1.0000
6.500 1.1676 0.01467 0.00829 -0.0803 0.3346 1.0000
6.750 1.1853 0.01515 0.00872 -0.0789 0.3302 1.0000
7.000 1.2062 0.01550 0.00909 -0.0780 0.3269 1.0000
7.250 1.2257 0.01592 0.00951 -0.0770 0.3233 1.0000
7.500 1.2437 0.01642 0.00997 -0.0758 0.3197 1.0000
7.750 1.2597 0.01704 0.01054 -0.0743 0.3156 1.0000
8.000 1.2788 0.01753 0.01102 -0.0734 0.3123 1.0000
8.250 1.2985 0.01797 0.01150 -0.0725 0.3094 1.0000
8.500 1.3174 0.01847 0.01201 -0.0716 0.3066 1.0000
8.750 1.3351 0.01904 0.01257 -0.0706 0.3037 1.0000
9.000 1.3515 0.01970 0.01320 -0.0694 0.3009 1.0000
9.250 1.3679 0.02040 0.01386 -0.0683 0.2976 1.0000
9.500 1.3864 0.02096 0.01446 -0.0675 0.2956 1.0000
9.750 1.4043 0.02155 0.01509 -0.0666 0.2936 1.0000
10.000 1.4220 0.02217 0.01574 -0.0658 0.2913 1.0000
10.250 1.4388 0.02285 0.01645 -0.0649 0.2889 1.0000
10.500 1.4548 0.02358 0.01720 -0.0640 0.2866 1.0000
10.750 1.4701 0.02437 0.01797 -0.0630 0.2842 1.0000
11.000 1.4854 0.02518 0.01876 -0.0620 0.2815 1.0000
11.250 1.5014 0.02596 0.01956 -0.0612 0.2792 1.0000
11.500 1.5161 0.02681 0.02048 -0.0603 0.2772 1.0000
11.750 1.5305 0.02771 0.02143 -0.0595 0.2750 1.0000
12.000 1.5448 0.02862 0.02239 -0.0587 0.2728 1.0000
12.250 1.5581 0.02962 0.02342 -0.0579 0.2706 1.0000
12.500 1.5714 0.03063 0.02444 -0.0571 0.2684 1.0000
12.750 1.5844 0.03167 0.02547 -0.0562 0.2661 1.0000
13.000 1.5996 0.03255 0.02634 -0.0555 0.2637 1.0000
13.250 1.6115 0.03374 0.02763 -0.0548 0.2622 1.0000
13.500 1.6230 0.03501 0.02896 -0.0542 0.2603 1.0000
13.750 1.6346 0.03627 0.03029 -0.0536 0.2582 1.0000
14.000 1.6455 0.03762 0.03169 -0.0530 0.2560 1.0000
14.250 1.6562 0.03900 0.03311 -0.0525 0.2539 1.0000
14.500 1.6664 0.04041 0.03452 -0.0519 0.2516 1.0000
14.750 1.6792 0.04148 0.03557 -0.0512 0.2489 1.0000
15.000 1.6876 0.04315 0.03733 -0.0508 0.2470 1.0000
15.250 1.6945 0.04502 0.03930 -0.0504 0.2447 1.0000
15.500 1.7010 0.04694 0.04129 -0.0501 0.2421 1.0000
15.750 1.7072 0.04892 0.04333 -0.0498 0.2393 1.0000
16.000 1.7136 0.05082 0.04524 -0.0495 0.2365 1.0000
16.250 1.7226 0.05230 0.04668 -0.0490 0.2333 1.0000
16.500 1.7250 0.05479 0.04930 -0.0488 0.2311 1.0000
16.750 1.7281 0.05719 0.05181 -0.0487 0.2281 1.0000
17.000 1.7315 0.05954 0.05421 -0.0486 0.2249 1.0000
17.250 1.7334 0.06201 0.05668 -0.0484 0.2217 1.0000
17.500 1.7368 0.06423 0.05893 -0.0482 0.2184 1.0000
17.750 1.7362 0.06714 0.06196 -0.0482 0.2150 1.0000
18.000 1.7368 0.06986 0.06475 -0.0483 0.2112 1.0000
18.250 1.7345 0.07288 0.06777 -0.0483 0.2074 1.0000
18.500 1.7341 0.07568 0.07062 -0.0483 0.2036 1.0000
18.750 1.7308 0.07895 0.07399 -0.0485 0.1992 1.0000
19.000 1.7268 0.08221 0.07726 -0.0486 0.1946 1.0000
19.250 1.7206 0.08579 0.08089 -0.0488 0.1902 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 386 AIRFOIL (goe386-il)