GOE 619 AIRFOIL (goe619-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 619 AIRFOIL (goe619-il) Reynolds number: 200,000 Max Cl/Cd: 73.74 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe619-il-200000.txt Download as CSV file: xf-goe619-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 619 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2039 0.09976 0.09650 -0.0473 0.9878 0.0893
-9.500 -0.5675 0.04796 0.04392 -0.0871 0.9786 0.0565
-9.250 -0.5631 0.04014 0.03536 -0.0945 0.9698 0.0567
-9.000 -0.5517 0.03579 0.03057 -0.0962 0.9605 0.0573
-8.750 -0.5224 0.03281 0.02733 -0.0991 0.9566 0.0580
-8.500 -0.5001 0.03089 0.02522 -0.0996 0.9488 0.0587
-8.250 -0.4691 0.02906 0.02317 -0.1015 0.9442 0.0597
-8.000 -0.4331 0.02737 0.02123 -0.1041 0.9414 0.0612
-7.750 -0.4102 0.02608 0.01972 -0.1038 0.9330 0.0627
-7.500 -0.3758 0.02455 0.01786 -0.1056 0.9290 0.0644
-7.250 -0.3379 0.02291 0.01601 -0.1080 0.9267 0.0661
-7.000 -0.3094 0.02205 0.01516 -0.1083 0.9203 0.0679
-6.750 -0.2752 0.02121 0.01424 -0.1096 0.9154 0.0705
-6.500 -0.2357 0.02032 0.01314 -0.1118 0.9124 0.0742
-6.250 -0.1962 0.01934 0.01222 -0.1142 0.9099 0.0788
-6.000 -0.1716 0.01890 0.01166 -0.1134 0.9013 0.0841
-5.750 -0.1370 0.01806 0.01086 -0.1148 0.8967 0.0924
-5.500 -0.0992 0.01729 0.01005 -0.1166 0.8933 0.1066
-5.250 -0.0762 0.01688 0.00964 -0.1157 0.8841 0.1178
-5.000 -0.0424 0.01643 0.00913 -0.1167 0.8790 0.1292
-4.750 -0.0100 0.01617 0.00879 -0.1174 0.8733 0.1384
-4.500 0.0154 0.01582 0.00846 -0.1168 0.8649 0.1455
-4.250 0.0500 0.01553 0.00808 -0.1179 0.8600 0.1538
-4.000 0.0735 0.01534 0.00793 -0.1169 0.8511 0.1616
-3.750 0.1046 0.01513 0.00763 -0.1172 0.8448 0.1708
-3.500 0.1320 0.01494 0.00750 -0.1170 0.8378 0.1809
-3.250 0.1586 0.01475 0.00732 -0.1165 0.8300 0.1918
-3.000 0.1912 0.01449 0.00703 -0.1171 0.8248 0.2059
-2.750 0.2130 0.01439 0.00696 -0.1157 0.8153 0.2210
-2.500 0.2435 0.01415 0.00676 -0.1159 0.8092 0.2424
-2.250 0.2673 0.01410 0.00676 -0.1149 0.8005 0.2644
-2.000 0.2965 0.01400 0.00660 -0.1148 0.7932 0.2861
-1.750 0.3215 0.01393 0.00654 -0.1139 0.7841 0.3031
-1.500 0.3506 0.01376 0.00634 -0.1137 0.7755 0.3189
-1.250 0.3747 0.01365 0.00624 -0.1126 0.7648 0.3325
-1.000 0.4043 0.01349 0.00602 -0.1124 0.7562 0.3471
-0.750 0.4280 0.01342 0.00596 -0.1113 0.7458 0.3612
-0.500 0.4567 0.01334 0.00585 -0.1112 0.7387 0.3769
-0.250 0.4808 0.01328 0.00585 -0.1102 0.7295 0.3917
0.000 0.5097 0.01319 0.00574 -0.1101 0.7225 0.4087
0.250 0.5330 0.01314 0.00576 -0.1090 0.7128 0.4280
0.500 0.5608 0.01302 0.00567 -0.1086 0.7053 0.4512
0.750 0.5840 0.01292 0.00568 -0.1075 0.6955 0.4778
1.000 0.6105 0.01272 0.00559 -0.1069 0.6878 0.5133
1.250 0.6313 0.01239 0.00559 -0.1053 0.6780 0.5708
1.500 0.7104 0.01147 0.00558 -0.1151 0.6665 1.0000
1.750 0.7352 0.01155 0.00549 -0.1142 0.6565 1.0000
2.000 0.7565 0.01164 0.00553 -0.1127 0.6448 1.0000
2.250 0.7798 0.01173 0.00552 -0.1115 0.6338 1.0000
2.500 0.8036 0.01183 0.00550 -0.1104 0.6224 1.0000
2.750 0.8246 0.01193 0.00556 -0.1088 0.6093 1.0000
3.000 0.8464 0.01204 0.00561 -0.1074 0.5956 1.0000
3.250 0.8681 0.01216 0.00565 -0.1059 0.5810 1.0000
3.500 0.8891 0.01229 0.00571 -0.1043 0.5646 1.0000
3.750 0.9092 0.01243 0.00577 -0.1025 0.5461 1.0000
4.000 0.9285 0.01261 0.00584 -0.1006 0.5255 1.0000
4.250 0.9468 0.01284 0.00595 -0.0986 0.5028 1.0000
4.500 0.9640 0.01313 0.00610 -0.0963 0.4777 1.0000
4.750 0.9802 0.01350 0.00629 -0.0940 0.4525 1.0000
5.000 0.9960 0.01393 0.00656 -0.0916 0.4283 1.0000
5.250 1.0116 0.01442 0.00686 -0.0893 0.4073 1.0000
5.500 1.0281 0.01491 0.00720 -0.0872 0.3892 1.0000
6.000 1.0620 0.01585 0.00794 -0.0832 0.3589 1.0000
6.250 1.0800 0.01629 0.00832 -0.0815 0.3469 1.0000
6.500 1.0980 0.01678 0.00872 -0.0798 0.3368 1.0000
6.750 1.1160 0.01721 0.00911 -0.0781 0.3279 1.0000
7.000 1.1346 0.01769 0.00954 -0.0765 0.3202 1.0000
7.250 1.1527 0.01811 0.00995 -0.0748 0.3128 1.0000
7.500 1.1726 0.01865 0.01039 -0.0735 0.3065 1.0000
7.750 1.1903 0.01903 0.01084 -0.0718 0.3002 1.0000
8.000 1.2088 0.01950 0.01129 -0.0703 0.2944 1.0000
8.250 1.2286 0.02002 0.01178 -0.0691 0.2889 1.0000
8.500 1.2462 0.02044 0.01227 -0.0674 0.2838 1.0000
8.750 1.2646 0.02091 0.01275 -0.0660 0.2789 1.0000
9.000 1.2860 0.02149 0.01327 -0.0652 0.2742 1.0000
9.250 1.3010 0.02192 0.01382 -0.0632 0.2693 1.0000
9.500 1.3165 0.02238 0.01432 -0.0614 0.2643 1.0000
9.750 1.3342 0.02298 0.01484 -0.0600 0.2585 1.0000
10.000 1.3438 0.02344 0.01546 -0.0574 0.2527 1.0000
10.250 1.3552 0.02398 0.01602 -0.0552 0.2467 1.0000
10.500 1.3679 0.02461 0.01666 -0.0533 0.2408 1.0000
10.750 1.3772 0.02521 0.01738 -0.0510 0.2346 1.0000
11.000 1.3879 0.02592 0.01808 -0.0490 0.2288 1.0000
11.250 1.3992 0.02664 0.01890 -0.0472 0.2236 1.0000
11.500 1.4082 0.02742 0.01978 -0.0452 0.2173 1.0000
11.750 1.4163 0.02836 0.02069 -0.0433 0.2110 1.0000
12.000 1.4261 0.02922 0.02173 -0.0416 0.2046 1.0000
12.250 1.4331 0.03031 0.02284 -0.0399 0.1981 1.0000
12.500 1.4423 0.03134 0.02400 -0.0384 0.1910 1.0000
12.750 1.4481 0.03262 0.02533 -0.0368 0.1833 1.0000
13.000 1.4559 0.03388 0.02669 -0.0355 0.1736 1.0000
13.250 1.4608 0.03540 0.02827 -0.0342 0.1629 1.0000
13.500 1.4638 0.03715 0.03004 -0.0329 0.1498 1.0000
13.750 1.4627 0.03935 0.03220 -0.0316 0.1331 1.0000
14.000 1.4581 0.04198 0.03476 -0.0304 0.1186 1.0000
14.250 1.4534 0.04477 0.03751 -0.0294 0.1076 1.0000
14.500 1.4493 0.04762 0.04037 -0.0286 0.1003 1.0000
14.750 1.4453 0.05058 0.04336 -0.0280 0.0946 1.0000
15.000 1.4416 0.05362 0.04647 -0.0276 0.0908 1.0000
15.250 1.4399 0.05654 0.04947 -0.0273 0.0874 1.0000
15.500 1.4357 0.05986 0.05285 -0.0273 0.0845 1.0000
15.750 1.4290 0.06357 0.05664 -0.0275 0.0820 1.0000
16.000 1.4260 0.06695 0.06011 -0.0277 0.0799 1.0000
16.250 1.4233 0.07039 0.06367 -0.0282 0.0778 1.0000
16.500 1.4165 0.07446 0.06783 -0.0289 0.0752 1.0000
16.750 1.4080 0.07887 0.07232 -0.0298 0.0733 1.0000
17.250 1.3929 0.08780 0.08146 -0.0322 0.0698 1.0000
17.500 1.3874 0.09210 0.08590 -0.0334 0.0681 1.0000
17.750 1.3800 0.09675 0.09068 -0.0350 0.0665 1.0000
18.000 1.3715 0.10166 0.09568 -0.0367 0.0650 1.0000
18.250 1.3625 0.10671 0.10081 -0.0386 0.0637 1.0000
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