GOE 413 AIRFOIL (goe413-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 413 AIRFOIL (goe413-il) Reynolds number: 1,000,000 Max Cl/Cd: 107.56 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe413-il-1000000-n5.txt Download as CSV file: xf-goe413-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 413 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.500 -0.8468 0.10768 0.10512 -0.0374 1.0000 0.0318
-17.250 -0.9074 0.09345 0.09065 -0.0465 1.0000 0.0322
-17.000 -0.9345 0.08525 0.08230 -0.0518 1.0000 0.0324
-16.750 -0.9556 0.07820 0.07513 -0.0566 1.0000 0.0325
-16.500 -0.9736 0.07181 0.06863 -0.0609 1.0000 0.0326
-16.250 -0.9908 0.06587 0.06259 -0.0651 1.0000 0.0327
-16.000 -1.0072 0.06040 0.05691 -0.0689 0.9244 0.0328
-15.750 -1.0231 0.05535 0.05163 -0.0719 0.8929 0.0328
-15.250 -1.0427 0.04581 0.04179 -0.0790 0.8646 0.0329
-15.000 -1.0481 0.04136 0.03718 -0.0827 0.8540 0.0330
-14.750 -1.0512 0.03690 0.03260 -0.0870 0.8450 0.0331
-14.500 -1.0487 0.03290 0.02846 -0.0915 0.8363 0.0333
-14.250 -1.0404 0.02918 0.02461 -0.0969 0.8298 0.0334
-14.000 -1.0268 0.02671 0.02202 -0.1009 0.8244 0.0335
-13.750 -1.0081 0.02541 0.02063 -0.1022 0.8193 0.0336
-13.250 -0.9653 0.02346 0.01853 -0.1036 0.8105 0.0339
-13.000 -0.9422 0.02266 0.01768 -0.1041 0.8064 0.0341
-12.750 -0.9184 0.02192 0.01689 -0.1045 0.8022 0.0342
-12.500 -0.8941 0.02126 0.01615 -0.1049 0.7978 0.0344
-12.250 -0.8693 0.02063 0.01546 -0.1051 0.7935 0.0346
-12.000 -0.8438 0.02003 0.01481 -0.1054 0.7894 0.0348
-11.750 -0.8179 0.01949 0.01422 -0.1057 0.7846 0.0350
-11.500 -0.7918 0.01898 0.01365 -0.1059 0.7798 0.0352
-11.250 -0.7655 0.01847 0.01308 -0.1061 0.7750 0.0355
-11.000 -0.7388 0.01795 0.01250 -0.1063 0.7705 0.0357
-10.750 -0.7121 0.01744 0.01194 -0.1065 0.7644 0.0359
-10.500 -0.6852 0.01697 0.01140 -0.1067 0.7574 0.0361
-10.250 -0.6579 0.01652 0.01088 -0.1069 0.7511 0.0363
-10.000 -0.6304 0.01608 0.01039 -0.1071 0.7433 0.0365
-9.750 -0.6029 0.01569 0.00992 -0.1072 0.7351 0.0367
-9.500 -0.5750 0.01531 0.00947 -0.1074 0.7247 0.0368
-9.250 -0.5471 0.01497 0.00905 -0.1075 0.7120 0.0369
-9.000 -0.5195 0.01456 0.00855 -0.1077 0.6954 0.0371
-8.750 -0.4920 0.01416 0.00806 -0.1078 0.6779 0.0374
-8.500 -0.4639 0.01385 0.00767 -0.1080 0.6628 0.0377
-8.250 -0.4355 0.01357 0.00733 -0.1081 0.6510 0.0379
-8.000 -0.4070 0.01335 0.00705 -0.1083 0.6404 0.0382
-7.750 -0.3781 0.01313 0.00678 -0.1085 0.6318 0.0385
-7.500 -0.3493 0.01293 0.00653 -0.1086 0.6231 0.0388
-7.250 -0.3204 0.01270 0.00626 -0.1088 0.6163 0.0391
-7.000 -0.2913 0.01247 0.00599 -0.1090 0.6095 0.0394
-6.750 -0.2623 0.01227 0.00573 -0.1092 0.6035 0.0397
-6.500 -0.2331 0.01205 0.00548 -0.1094 0.5989 0.0400
-6.250 -0.2037 0.01184 0.00524 -0.1096 0.5943 0.0403
-6.000 -0.1744 0.01165 0.00501 -0.1097 0.5891 0.0406
-5.750 -0.1451 0.01148 0.00479 -0.1099 0.5836 0.0409
-5.500 -0.1156 0.01132 0.00459 -0.1101 0.5793 0.0411
-5.250 -0.0859 0.01115 0.00441 -0.1103 0.5756 0.0413
-5.000 -0.0564 0.01092 0.00415 -0.1106 0.5713 0.0417
-4.750 -0.0269 0.01073 0.00394 -0.1108 0.5666 0.0422
-4.250 0.0324 0.01047 0.00364 -0.1112 0.5585 0.0431
-4.000 0.0622 0.01034 0.00350 -0.1114 0.5547 0.0436
-3.750 0.0919 0.01022 0.00337 -0.1116 0.5501 0.0441
-3.500 0.1215 0.01012 0.00324 -0.1118 0.5452 0.0446
-3.250 0.1512 0.01004 0.00312 -0.1120 0.5401 0.0451
-3.000 0.1811 0.00993 0.00301 -0.1122 0.5355 0.0455
-2.750 0.2108 0.00985 0.00291 -0.1124 0.5305 0.0459
-2.500 0.2405 0.00977 0.00280 -0.1126 0.5259 0.0464
-2.250 0.2702 0.00967 0.00268 -0.1128 0.5215 0.0472
-2.000 0.3001 0.00957 0.00259 -0.1130 0.5183 0.0479
-1.750 0.3300 0.00950 0.00251 -0.1133 0.5140 0.0486
-1.500 0.3597 0.00945 0.00245 -0.1134 0.5098 0.0495
-1.250 0.3893 0.00942 0.00240 -0.1136 0.5053 0.0505
-1.000 0.4190 0.00939 0.00236 -0.1138 0.5012 0.0512
-0.750 0.4489 0.00931 0.00229 -0.1140 0.4973 0.0524
-0.500 0.4787 0.00927 0.00225 -0.1142 0.4932 0.0538
-0.250 0.5083 0.00925 0.00222 -0.1144 0.4885 0.0553
0.250 0.5675 0.00920 0.00218 -0.1148 0.4796 0.0611
0.500 0.5975 0.00892 0.00211 -0.1152 0.4751 0.1318
0.750 0.6270 0.00887 0.00213 -0.1155 0.4694 0.1562
1.000 0.6563 0.00886 0.00216 -0.1157 0.4626 0.1741
1.250 0.6857 0.00886 0.00219 -0.1158 0.4550 0.1894
1.500 0.7148 0.00889 0.00223 -0.1160 0.4483 0.2058
1.750 0.7442 0.00889 0.00228 -0.1162 0.4403 0.2250
2.000 0.7728 0.00895 0.00235 -0.1163 0.4286 0.2510
2.250 0.8020 0.00894 0.00242 -0.1165 0.4197 0.2858
2.500 0.8307 0.00900 0.00252 -0.1166 0.4109 0.3124
2.750 0.8595 0.00906 0.00261 -0.1168 0.4013 0.3340
3.000 0.8878 0.00918 0.00272 -0.1168 0.3900 0.3553
3.500 0.9434 0.00949 0.00301 -0.1168 0.3611 0.4017
3.750 0.9711 0.00963 0.00317 -0.1168 0.3470 0.4340
4.000 0.9989 0.00975 0.00336 -0.1168 0.3356 0.4783
4.250 1.0261 0.00993 0.00356 -0.1168 0.3237 0.5176
4.500 1.0538 0.01009 0.00374 -0.1168 0.3131 0.5453
4.750 1.0808 0.01029 0.00394 -0.1166 0.3026 0.5699
5.000 1.1076 0.01051 0.00416 -0.1165 0.2909 0.5965
5.250 1.1342 0.01071 0.00439 -0.1164 0.2772 0.6329
5.500 1.1604 0.01085 0.00468 -0.1162 0.2641 0.7134
5.750 1.1851 0.01103 0.00499 -0.1157 0.2496 0.8029
6.000 1.2057 0.01121 0.00531 -0.1143 0.2340 0.8921
6.250 1.2253 0.01150 0.00559 -0.1127 0.2158 1.0000
6.500 1.2473 0.01210 0.00602 -0.1120 0.1927 1.0000
6.750 1.2665 0.01287 0.00660 -0.1108 0.1619 1.0000
7.000 1.2690 0.01479 0.00802 -0.1076 0.0816 1.0000
7.250 1.2876 0.01546 0.00860 -0.1063 0.0687 1.0000
7.500 1.3089 0.01590 0.00902 -0.1055 0.0649 1.0000
7.750 1.3280 0.01637 0.00947 -0.1042 0.0622 1.0000
8.000 1.3466 0.01683 0.00993 -0.1029 0.0603 1.0000
8.250 1.3654 0.01731 0.01041 -0.1017 0.0591 1.0000
8.500 1.3836 0.01784 0.01095 -0.1006 0.0581 1.0000
8.750 1.4012 0.01844 0.01155 -0.0994 0.0571 1.0000
9.000 1.4181 0.01909 0.01221 -0.0983 0.0562 1.0000
9.250 1.4345 0.01983 0.01295 -0.0971 0.0553 1.0000
9.500 1.4502 0.02062 0.01376 -0.0960 0.0544 1.0000
9.750 1.4661 0.02145 0.01461 -0.0950 0.0539 1.0000
10.000 1.4822 0.02227 0.01546 -0.0941 0.0535 1.0000
10.250 1.4979 0.02315 0.01636 -0.0932 0.0532 1.0000
10.500 1.5128 0.02411 0.01735 -0.0923 0.0528 1.0000
10.750 1.5270 0.02513 0.01841 -0.0914 0.0525 1.0000
11.000 1.5406 0.02622 0.01952 -0.0904 0.0521 1.0000
11.250 1.5532 0.02741 0.02075 -0.0895 0.0517 1.0000
11.500 1.5651 0.02867 0.02204 -0.0885 0.0513 1.0000
11.750 1.5761 0.03001 0.02342 -0.0876 0.0509 1.0000
12.000 1.5861 0.03149 0.02493 -0.0867 0.0505 1.0000
12.250 1.5954 0.03305 0.02653 -0.0858 0.0502 1.0000
12.500 1.6037 0.03470 0.02822 -0.0849 0.0499 1.0000
12.750 1.6110 0.03650 0.03007 -0.0840 0.0496 1.0000
13.000 1.6173 0.03844 0.03206 -0.0832 0.0493 1.0000
13.250 1.6225 0.04052 0.03418 -0.0825 0.0490 1.0000
13.500 1.6269 0.04272 0.03644 -0.0818 0.0487 1.0000
13.750 1.6305 0.04510 0.03888 -0.0812 0.0484 1.0000
14.000 1.6333 0.04761 0.04145 -0.0807 0.0481 1.0000
14.250 1.6343 0.05034 0.04425 -0.0802 0.0478 1.0000
14.500 1.6378 0.05285 0.04682 -0.0798 0.0478 1.0000
14.750 1.6414 0.05534 0.04938 -0.0794 0.0477 1.0000
15.000 1.6439 0.05801 0.05211 -0.0791 0.0475 1.0000
15.250 1.6468 0.06062 0.05478 -0.0788 0.0474 1.0000
15.500 1.6496 0.06326 0.05748 -0.0786 0.0471 1.0000
15.750 1.6510 0.06611 0.06040 -0.0784 0.0469 1.0000
16.000 1.6535 0.06883 0.06318 -0.0783 0.0466 1.0000
16.250 1.6535 0.07189 0.06631 -0.0782 0.0463 1.0000
16.500 1.6545 0.07481 0.06929 -0.0782 0.0460 1.0000
16.750 1.6538 0.07802 0.07256 -0.0782 0.0457 1.0000
17.000 1.6537 0.08115 0.07576 -0.0783 0.0455 1.0000
17.250 1.6519 0.08455 0.07922 -0.0785 0.0452 1.0000
17.500 1.6499 0.08796 0.08270 -0.0787 0.0450 1.0000
17.750 1.6480 0.09138 0.08619 -0.0789 0.0448 1.0000
18.000 1.6450 0.09500 0.08988 -0.0793 0.0446 1.0000
18.250 1.6435 0.09843 0.09337 -0.0797 0.0443 1.0000
18.500 1.6398 0.10219 0.09719 -0.0803 0.0441 1.0000
18.750 1.6377 0.10569 0.10075 -0.0808 0.0439 1.0000
19.000 1.6333 0.10960 0.10472 -0.0815 0.0436 1.0000
19.250 1.6310 0.11317 0.10836 -0.0822 0.0434 1.0000
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