GOE 394 AIRFOIL (goe394-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 394 AIRFOIL (goe394-il) Reynolds number: 100,000 Max Cl/Cd: 66.64 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe394-il-100000-n5.txt Download as CSV file: xf-goe394-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 394 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.2905 0.10330 0.09861 -0.0240 1.0000 0.0454
-8.000 -0.2838 0.10071 0.09608 -0.0256 1.0000 0.0475
-7.750 -0.2834 0.09949 0.09498 -0.0281 1.0000 0.0500
-7.500 -0.2756 0.09817 0.09373 -0.0352 0.9846 0.0506
-7.250 -0.2563 0.09310 0.08867 -0.0391 0.9730 0.0514
-7.000 -0.2389 0.08862 0.08417 -0.0387 0.9652 0.0530
-6.750 -0.2182 0.08506 0.08058 -0.0426 0.9535 0.0549
-6.500 -0.1968 0.08164 0.07712 -0.0475 0.9416 0.0574
-6.250 -0.1571 0.07901 0.07436 -0.0646 0.9260 0.0615
-6.000 -0.1453 0.07449 0.06984 -0.0630 0.9199 0.0626
-5.750 -0.1293 0.07127 0.06659 -0.0635 0.9114 0.0640
-5.500 -0.1069 0.06804 0.06329 -0.0670 0.9047 0.0654
-5.250 -0.0834 0.06493 0.06013 -0.0711 0.8967 0.0671
-4.750 -0.0184 0.05656 0.05146 -0.0854 0.8835 0.0602
-4.500 0.0062 0.05302 0.04783 -0.0883 0.8782 0.0562
-4.000 0.0736 0.04610 0.04059 -0.0989 0.8689 0.0571
-3.750 0.1097 0.04227 0.03655 -0.1042 0.8641 0.0554
-3.500 0.1482 0.03817 0.03215 -0.1095 0.8597 0.0542
-3.250 0.1836 0.03455 0.02822 -0.1135 0.8525 0.0538
-3.000 0.2154 0.03212 0.02553 -0.1154 0.8457 0.0556
-2.750 0.2478 0.02943 0.02248 -0.1175 0.8370 0.0579
-2.500 0.2808 0.02642 0.01902 -0.1192 0.8304 0.0580
-2.250 0.3125 0.02378 0.01590 -0.1206 0.8230 0.0587
-2.000 0.3439 0.02140 0.01293 -0.1214 0.8175 0.0602
-1.750 0.3733 0.01993 0.01107 -0.1217 0.8123 0.0623
-1.500 0.4007 0.01956 0.01063 -0.1215 0.8062 0.0647
-1.250 0.4288 0.01896 0.00981 -0.1213 0.8011 0.0694
-1.000 0.4562 0.01871 0.00946 -0.1211 0.7949 0.0766
-0.750 0.4841 0.01821 0.00877 -0.1208 0.7889 0.0863
-0.500 0.5117 0.01784 0.00821 -0.1203 0.7833 0.0985
-0.250 0.5388 0.01767 0.00791 -0.1200 0.7761 0.1097
0.000 0.5657 0.01754 0.00774 -0.1196 0.7703 0.1221
0.250 0.5922 0.01748 0.00771 -0.1194 0.7625 0.1356
0.500 0.6188 0.01727 0.00753 -0.1189 0.7559 0.1449
0.750 0.6454 0.01717 0.00737 -0.1184 0.7478 0.1508
1.000 0.6719 0.01695 0.00716 -0.1178 0.7405 0.1546
1.250 0.6987 0.01684 0.00706 -0.1174 0.7316 0.1574
1.500 0.7258 0.01671 0.00688 -0.1168 0.7240 0.1604
1.750 0.7522 0.01667 0.00687 -0.1163 0.7136 0.1637
2.250 0.8054 0.01654 0.00677 -0.1151 0.6943 0.1737
2.500 0.8315 0.01654 0.00683 -0.1146 0.6822 0.1822
2.750 0.8576 0.01649 0.00691 -0.1141 0.6695 0.1926
3.000 0.8838 0.01644 0.00697 -0.1136 0.6557 0.2105
3.250 0.9097 0.01613 0.00715 -0.1132 0.6405 0.3558
3.500 0.9354 0.01526 0.00717 -0.1125 0.6238 1.0000
3.750 0.9612 0.01534 0.00720 -0.1118 0.6061 1.0000
4.000 0.9869 0.01545 0.00727 -0.1111 0.5869 1.0000
4.250 1.0124 0.01555 0.00730 -0.1103 0.5682 1.0000
4.500 1.0375 0.01570 0.00731 -0.1094 0.5489 1.0000
4.750 1.0621 0.01596 0.00744 -0.1085 0.5287 1.0000
5.000 1.0863 0.01630 0.00767 -0.1076 0.5092 1.0000
5.250 1.1106 0.01671 0.00802 -0.1068 0.4920 1.0000
5.500 1.1348 0.01714 0.00841 -0.1061 0.4757 1.0000
5.750 1.1587 0.01758 0.00883 -0.1053 0.4595 1.0000
6.000 1.1822 0.01805 0.00930 -0.1045 0.4424 1.0000
6.250 1.2057 0.01851 0.00979 -0.1037 0.4263 1.0000
6.500 1.2295 0.01896 0.01033 -0.1030 0.4127 1.0000
6.750 1.2528 0.01943 0.01088 -0.1022 0.3977 1.0000
7.000 1.2754 0.01991 0.01148 -0.1013 0.3814 1.0000
7.250 1.2977 0.02040 0.01211 -0.1004 0.3635 1.0000
7.500 1.3191 0.02093 0.01275 -0.0994 0.3422 1.0000
7.750 1.3371 0.02161 0.01340 -0.0980 0.3048 1.0000
8.000 1.3503 0.02271 0.01419 -0.0962 0.2403 1.0000
8.250 1.3586 0.02444 0.01538 -0.0940 0.1714 1.0000
8.500 1.3687 0.02608 0.01680 -0.0921 0.1360 1.0000
8.750 1.3800 0.02754 0.01819 -0.0902 0.1132 1.0000
9.000 1.3898 0.02907 0.01967 -0.0883 0.0911 1.0000
9.250 1.3988 0.03062 0.02116 -0.0862 0.0647 1.0000
9.500 1.4025 0.03240 0.02287 -0.0834 0.0489 1.0000
9.750 1.4032 0.03437 0.02480 -0.0806 0.0412 1.0000
10.000 1.4049 0.03633 0.02685 -0.0781 0.0362 1.0000
10.250 1.4037 0.03863 0.02921 -0.0758 0.0332 1.0000
10.500 1.4051 0.04083 0.03164 -0.0738 0.0310 1.0000
10.750 1.4057 0.04319 0.03416 -0.0720 0.0293 1.0000
11.000 1.4055 0.04573 0.03682 -0.0705 0.0277 1.0000
11.250 1.4028 0.04861 0.03979 -0.0691 0.0263 1.0000
11.500 1.4018 0.05142 0.04273 -0.0677 0.0251 1.0000
11.750 1.4034 0.05404 0.04554 -0.0665 0.0238 1.0000
12.000 1.4040 0.05682 0.04850 -0.0654 0.0229 1.0000
12.250 1.4045 0.05969 0.05153 -0.0642 0.0221 1.0000
12.500 1.4049 0.06264 0.05463 -0.0632 0.0215 1.0000
12.750 1.4049 0.06569 0.05784 -0.0622 0.0209 1.0000
13.000 1.4042 0.06888 0.06117 -0.0615 0.0203 1.0000
13.250 1.4019 0.07229 0.06471 -0.0610 0.0197 1.0000
13.500 1.3987 0.07592 0.06845 -0.0606 0.0191 1.0000
13.750 1.3943 0.07992 0.07263 -0.0601 0.0185 1.0000
14.000 1.3881 0.08417 0.07715 -0.0605 0.0182 1.0000
14.250 1.3804 0.08880 0.08205 -0.0613 0.0179 1.0000
14.500 1.3711 0.09387 0.08739 -0.0625 0.0176 1.0000
14.750 1.3607 0.09936 0.09313 -0.0642 0.0174 1.0000
15.000 1.3488 0.10536 0.09938 -0.0665 0.0173 1.0000
15.250 1.3358 0.11188 0.10614 -0.0694 0.0172 1.0000
15.500 1.3216 0.11894 0.11343 -0.0729 0.0172 1.0000
15.750 1.3063 0.12658 0.12129 -0.0772 0.0172 1.0000
16.000 1.2902 0.13485 0.12977 -0.0821 0.0173 1.0000
16.250 1.2730 0.14395 0.13906 -0.0879 0.0174 1.0000
16.500 1.2550 0.15392 0.14921 -0.0944 0.0175 1.0000
16.750 1.2363 0.16495 0.16033 -0.1018 0.0178 1.0000
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Polar data table (+)
Polar graphs
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