GOE 396 AIRFOIL (goe396-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 396 AIRFOIL (goe396-il) Reynolds number: 100,000 Max Cl/Cd: 66.98 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe396-il-100000.txt Download as CSV file: xf-goe396-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 396 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
------ -------- --------- --------- -------- -------- --------
-7.000 -0.3091 0.09439 0.08997 -0.0251 1.0000 0.0477
-6.750 -0.3146 0.09299 0.08867 -0.0239 1.0000 0.0491
-6.500 -0.3213 0.09203 0.08781 -0.0230 1.0000 0.0504
-6.250 -0.3289 0.09198 0.08785 -0.0235 1.0000 0.0515
-6.000 -0.3310 0.09179 0.08771 -0.0255 1.0000 0.0520
-5.750 -0.3258 0.09108 0.08701 -0.0289 1.0000 0.0523
-5.500 -0.3264 0.08717 0.08317 -0.0278 1.0000 0.0529
-5.250 -0.3334 0.08273 0.07881 -0.0214 1.0000 0.0543
-5.000 -0.3320 0.08017 0.07623 -0.0199 1.0000 0.0558
-4.750 -0.3274 0.07774 0.07382 -0.0199 1.0000 0.0579
-4.500 -0.3186 0.07530 0.07138 -0.0212 1.0000 0.0605
-4.250 -0.2677 0.07443 0.07025 -0.0362 0.9990 0.0654
-4.000 -0.2547 0.06798 0.06390 -0.0358 0.9945 0.0672
-3.750 -0.2265 0.06397 0.05985 -0.0391 0.9883 0.0719
-3.500 -0.1630 0.05971 0.05532 -0.0527 0.9825 0.0798
-3.250 -0.1399 0.05602 0.05164 -0.0540 0.9755 0.0845
-3.000 -0.0852 0.05206 0.04743 -0.0635 0.9700 0.0942
-2.750 -0.0433 0.04903 0.04416 -0.0692 0.9624 0.1070
-2.500 -0.0022 0.04566 0.04066 -0.0741 0.9569 0.1213
-2.250 0.0359 0.04284 0.03763 -0.0780 0.9493 0.1345
-2.000 0.0782 0.03967 0.03429 -0.0822 0.9438 0.1492
-1.750 0.1136 0.03719 0.03163 -0.0848 0.9361 0.1638
-1.500 0.1557 0.03493 0.02916 -0.0885 0.9303 0.2026
-1.250 0.1886 0.03285 0.02687 -0.0901 0.9223 0.2300
-1.000 0.2590 0.02545 0.01765 -0.0949 0.9201 0.0876
-0.750 0.3047 0.02385 0.01561 -0.0979 0.9157 0.1010
-0.500 0.3369 0.02256 0.01393 -0.0983 0.9068 0.1085
-0.250 0.3837 0.02165 0.01282 -0.1016 0.9022 0.1319
0.000 0.4157 0.02085 0.01202 -0.1022 0.8929 0.1578
0.250 0.4640 0.01988 0.01121 -0.1058 0.8888 0.2353
0.500 0.4961 0.01963 0.01105 -0.1067 0.8790 0.2958
0.750 0.5430 0.01877 0.01041 -0.1100 0.8746 0.3701
1.000 0.5951 0.01725 0.00990 -0.1149 0.8668 1.0000
1.250 0.6364 0.01706 0.00948 -0.1168 0.8604 1.0000
1.500 0.6654 0.01710 0.00940 -0.1166 0.8490 1.0000
1.750 0.6944 0.01709 0.00932 -0.1162 0.8373 1.0000
2.000 0.7238 0.01702 0.00918 -0.1158 0.8253 1.0000
2.250 0.7526 0.01694 0.00910 -0.1152 0.8132 1.0000
2.500 0.7806 0.01688 0.00901 -0.1145 0.8012 1.0000
2.750 0.8089 0.01685 0.00897 -0.1138 0.7902 1.0000
3.000 0.8365 0.01684 0.00897 -0.1131 0.7791 1.0000
3.250 0.8614 0.01689 0.00905 -0.1120 0.7659 1.0000
3.500 0.8865 0.01692 0.00919 -0.1109 0.7526 1.0000
3.750 0.9113 0.01698 0.00932 -0.1098 0.7394 1.0000
4.000 0.9366 0.01696 0.00937 -0.1086 0.7255 1.0000
4.250 0.9619 0.01695 0.00945 -0.1074 0.7115 1.0000
4.500 0.9853 0.01685 0.00945 -0.1058 0.6933 1.0000
4.750 1.0079 0.01611 0.00873 -0.1028 0.6591 1.0000
5.000 1.0310 0.01609 0.00883 -0.1012 0.6371 1.0000
5.250 1.0488 0.01578 0.00838 -0.0977 0.5846 1.0000
5.500 1.0670 0.01593 0.00850 -0.0950 0.5356 1.0000
5.750 1.0787 0.01648 0.00863 -0.0912 0.4381 1.0000
6.000 1.0795 0.01841 0.00938 -0.0865 0.2383 1.0000
6.250 1.0790 0.02135 0.01110 -0.0825 0.0754 1.0000
6.500 1.0900 0.02306 0.01253 -0.0797 0.0504 1.0000
6.750 1.1037 0.02438 0.01404 -0.0772 0.0454 1.0000
7.000 1.1140 0.02592 0.01572 -0.0742 0.0428 1.0000
7.250 1.1214 0.02780 0.01770 -0.0709 0.0412 1.0000
7.500 1.1344 0.02973 0.01967 -0.0684 0.0405 1.0000
7.750 1.1567 0.03188 0.02190 -0.0670 0.0399 1.0000
8.000 1.1825 0.03403 0.02423 -0.0661 0.0381 1.0000
8.250 1.2108 0.03676 0.02719 -0.0656 0.0367 1.0000
8.500 1.2396 0.04049 0.03128 -0.0650 0.0380 1.0000
8.750 1.2628 0.04510 0.03633 -0.0640 0.0398 1.0000
9.000 1.2845 0.04831 0.03994 -0.0622 0.0424 1.0000
9.250 1.2898 0.05343 0.04602 -0.0582 0.0484 1.0000
9.500 1.2979 0.05890 0.05211 -0.0551 0.0560 1.0000
9.750 1.2912 0.06591 0.05986 -0.0510 0.0684 1.0000
10.000 1.2092 0.06290 0.05748 -0.0413 0.0675 1.0000
10.250 1.1808 0.06706 0.06194 -0.0369 0.0691 1.0000
10.500 1.1637 0.07301 0.06805 -0.0347 0.0736 1.0000
10.750 1.1361 0.07712 0.07234 -0.0325 0.0735 1.0000
11.000 1.1109 0.08206 0.07743 -0.0317 0.0739 1.0000
11.250 1.0861 0.08756 0.08306 -0.0318 0.0742 1.0000
11.500 1.0611 0.09351 0.08912 -0.0327 0.0746 1.0000
11.750 1.0367 0.09977 0.09541 -0.0345 0.0749 1.0000
12.000 1.0125 0.10627 0.10200 -0.0371 0.0751 1.0000
12.250 0.9858 0.11325 0.10906 -0.0406 0.0753 1.0000
12.500 0.9606 0.12018 0.11605 -0.0446 0.0754 1.0000
12.750 0.9311 0.12730 0.12322 -0.0495 0.0754 1.0000
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Polar data table (+)
Polar graphs
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