GOE 363 AIRFOIL (goe363-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 363 AIRFOIL (goe363-il) Reynolds number: 200,000 Max Cl/Cd: 70.1 at α=2° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe363-il-200000.txt Download as CSV file: xf-goe363-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 363 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 -0.2769 0.11524 0.11199 -0.0371 1.0000 0.0407
-9.500 -0.2948 0.11481 0.11165 -0.0340 1.0000 0.0407
-9.250 -0.3143 0.11448 0.11141 -0.0307 1.0000 0.0408
-9.000 -0.2956 0.10931 0.10624 -0.0267 1.0000 0.0420
-8.750 -0.2902 0.10713 0.10409 -0.0258 0.9990 0.0430
-8.500 -0.2719 0.10341 0.10036 -0.0296 0.9959 0.0448
-8.250 -0.2558 0.09950 0.09645 -0.0344 0.9923 0.0469
-8.000 -0.2477 0.09556 0.09253 -0.0465 0.9842 0.0496
-7.750 -0.2343 0.08981 0.08679 -0.0575 0.9746 0.0503
-7.500 -0.2164 0.08632 0.08329 -0.0532 0.9740 0.0515
-7.250 -0.1902 0.08295 0.07990 -0.0557 0.9715 0.0536
-7.000 -0.1710 0.07930 0.07625 -0.0608 0.9643 0.0565
-6.750 -0.1393 0.07106 0.06793 -0.0820 0.9567 0.0615
-6.500 -0.1163 0.06918 0.06607 -0.0792 0.9559 0.0638
-6.250 -0.1017 0.06662 0.06351 -0.0809 0.9473 0.0667
-6.000 -0.0618 0.05884 0.05553 -0.0981 0.9419 0.0738
-5.750 -0.0470 0.05715 0.05387 -0.0962 0.9357 0.0756
-5.500 -0.0215 0.05442 0.05109 -0.0990 0.9304 0.0801
-5.250 0.0142 0.04924 0.04573 -0.1072 0.9266 0.0881
-5.000 0.0320 0.04753 0.04400 -0.1069 0.9187 0.0925
-4.750 0.0717 0.02992 0.02471 -0.1193 0.9123 0.0607
-4.500 0.0960 0.02629 0.02070 -0.1198 0.9062 0.0601
-4.250 0.1243 0.02330 0.01727 -0.1202 0.9000 0.0595
-4.000 0.1594 0.02101 0.01451 -0.1212 0.8959 0.0597
-3.750 0.1847 0.01973 0.01291 -0.1203 0.8866 0.0612
-3.500 0.2177 0.01795 0.01093 -0.1206 0.8806 0.0628
-3.250 0.2432 0.01701 0.00990 -0.1196 0.8702 0.0642
-3.000 0.2728 0.01614 0.00893 -0.1191 0.8624 0.0665
-2.750 0.2998 0.01551 0.00821 -0.1182 0.8525 0.0699
-2.500 0.3267 0.01492 0.00751 -0.1173 0.8422 0.0724
-2.250 0.3553 0.01413 0.00672 -0.1168 0.8336 0.0768
-2.000 0.3809 0.01376 0.00633 -0.1158 0.8222 0.0830
-1.750 0.4080 0.01339 0.00601 -0.1152 0.8125 0.0969
-1.500 0.4364 0.01312 0.00584 -0.1147 0.8031 0.1459
-1.250 0.4625 0.01302 0.00574 -0.1140 0.7910 0.1777
-1.000 0.4891 0.01288 0.00558 -0.1134 0.7792 0.1961
-0.750 0.5160 0.01274 0.00542 -0.1128 0.7669 0.2153
-0.500 0.5427 0.01257 0.00524 -0.1122 0.7534 0.2320
-0.250 0.5690 0.01239 0.00506 -0.1116 0.7382 0.2486
0.000 0.5950 0.01220 0.00492 -0.1109 0.7208 0.2714
0.250 0.6207 0.01196 0.00476 -0.1103 0.7017 0.3057
0.500 0.6447 0.01131 0.00459 -0.1094 0.6814 0.4476
0.750 0.6748 0.01018 0.00442 -0.1089 0.6578 1.0000
1.000 0.7002 0.01031 0.00428 -0.1080 0.6326 1.0000
1.250 0.7250 0.01050 0.00423 -0.1072 0.6058 1.0000
1.500 0.7495 0.01075 0.00423 -0.1063 0.5800 1.0000
1.750 0.7737 0.01107 0.00429 -0.1054 0.5558 1.0000
2.000 0.7977 0.01138 0.00441 -0.1045 0.5314 1.0000
2.250 0.8213 0.01174 0.00456 -0.1036 0.5064 1.0000
2.500 0.8444 0.01210 0.00473 -0.1027 0.4787 1.0000
2.750 0.8670 0.01247 0.00491 -0.1017 0.4474 1.0000
3.000 0.8891 0.01288 0.00511 -0.1006 0.4151 1.0000
3.250 0.9112 0.01332 0.00534 -0.0996 0.3877 1.0000
3.500 0.9335 0.01380 0.00561 -0.0987 0.3681 1.0000
3.750 0.9563 0.01427 0.00591 -0.0979 0.3537 1.0000
4.000 0.9799 0.01470 0.00624 -0.0972 0.3421 1.0000
4.250 1.0039 0.01512 0.00658 -0.0966 0.3327 1.0000
4.500 1.0272 0.01561 0.00692 -0.0959 0.3245 1.0000
4.750 1.0518 0.01597 0.00728 -0.0954 0.3168 1.0000
5.000 1.0757 0.01643 0.00763 -0.0948 0.3104 1.0000
5.250 1.1001 0.01683 0.00801 -0.0943 0.3043 1.0000
5.500 1.1243 0.01721 0.00838 -0.0938 0.2985 1.0000
5.750 1.1484 0.01775 0.00881 -0.0933 0.2934 1.0000
6.000 1.1728 0.01809 0.00922 -0.0928 0.2887 1.0000
6.250 1.1969 0.01848 0.00962 -0.0923 0.2839 1.0000
6.500 1.2209 0.01897 0.01006 -0.0918 0.2795 1.0000
6.750 1.2449 0.01943 0.01055 -0.0913 0.2751 1.0000
7.000 1.2682 0.01981 0.01100 -0.0907 0.2704 1.0000
7.250 1.2913 0.02025 0.01146 -0.0901 0.2658 1.0000
7.500 1.3148 0.02081 0.01199 -0.0896 0.2611 1.0000
7.750 1.3351 0.02112 0.01242 -0.0885 0.2547 1.0000
8.000 1.3554 0.02162 0.01284 -0.0876 0.2478 1.0000
8.250 1.3737 0.02193 0.01331 -0.0862 0.2406 1.0000
8.500 1.3923 0.02237 0.01374 -0.0849 0.2342 1.0000
8.750 1.4096 0.02279 0.01426 -0.0835 0.2271 1.0000
9.000 1.4245 0.02319 0.01469 -0.0816 0.2201 1.0000
9.250 1.4397 0.02369 0.01527 -0.0799 0.2135 1.0000
9.500 1.4538 0.02415 0.01581 -0.0781 0.2062 1.0000
9.750 1.4677 0.02471 0.01642 -0.0763 0.1991 1.0000
10.000 1.4821 0.02525 0.01705 -0.0747 0.1917 1.0000
10.250 1.4961 0.02588 0.01775 -0.0731 0.1843 1.0000
10.500 1.5085 0.02655 0.01846 -0.0715 0.1748 1.0000
10.750 1.5230 0.02722 0.01920 -0.0702 0.1634 1.0000
11.000 1.5350 0.02811 0.02009 -0.0688 0.1516 1.0000
11.250 1.5451 0.02921 0.02117 -0.0672 0.1417 1.0000
11.500 1.5519 0.03061 0.02253 -0.0655 0.1312 1.0000
11.750 1.5565 0.03225 0.02415 -0.0637 0.1224 1.0000
12.000 1.5618 0.03391 0.02584 -0.0621 0.1134 1.0000
12.250 1.5677 0.03558 0.02756 -0.0606 0.1045 1.0000
12.500 1.5725 0.03741 0.02942 -0.0592 0.0918 1.0000
12.750 1.5591 0.04096 0.03271 -0.0572 0.0498 1.0000
13.000 1.5394 0.04535 0.03706 -0.0554 0.0322 1.0000
13.250 1.5307 0.04884 0.04064 -0.0543 0.0280 1.0000
13.500 1.5254 0.05215 0.04408 -0.0536 0.0265 1.0000
13.750 1.5197 0.05568 0.04776 -0.0533 0.0254 1.0000
14.000 1.5125 0.05956 0.05183 -0.0532 0.0247 1.0000
14.250 1.5037 0.06389 0.05633 -0.0536 0.0241 1.0000
14.500 1.4929 0.06870 0.06133 -0.0543 0.0237 1.0000
14.750 1.4802 0.07399 0.06681 -0.0555 0.0233 1.0000
15.000 1.4651 0.07985 0.07286 -0.0570 0.0230 1.0000
15.250 1.4480 0.08619 0.07941 -0.0589 0.0229 1.0000
15.500 1.4293 0.09295 0.08636 -0.0611 0.0228 1.0000
15.750 1.4097 0.10007 0.09367 -0.0636 0.0227 1.0000
16.000 1.3888 0.10761 0.10140 -0.0664 0.0227 1.0000
16.250 1.3683 0.11525 0.10922 -0.0695 0.0228 1.0000
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