GOE 387 AIRFOIL (goe387-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 387 AIRFOIL (goe387-il) Reynolds number: 1,000,000 Max Cl/Cd: 122.51 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe387-il-1000000.txt Download as CSV file: xf-goe387-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 387 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.2460 0.14334 0.14157 -0.0416 1.0000 0.0207
-13.500 -0.2551 0.13772 0.13595 -0.0447 1.0000 0.0216
-13.250 -0.2520 0.13388 0.13211 -0.0466 0.9998 0.0216
-13.000 -0.2404 0.12899 0.12722 -0.0509 0.9989 0.0217
-12.750 -0.2255 0.12484 0.12307 -0.0536 0.9976 0.0219
-12.500 -0.2084 0.12211 0.12034 -0.0554 0.9918 0.0220
-12.250 -0.1939 0.11903 0.11727 -0.0578 0.9849 0.0221
-12.000 -0.1804 0.11580 0.11404 -0.0604 0.9746 0.0223
-11.750 -0.1600 0.11227 0.11049 -0.0647 0.9635 0.0226
-11.500 -0.1355 0.10804 0.10623 -0.0709 0.9525 0.0230
-11.000 -0.0964 0.09304 0.09108 -0.0919 0.9277 0.0252
-10.750 -0.0712 0.08583 0.08379 -0.1023 0.9147 0.0254
-10.500 -0.0367 0.08223 0.08005 -0.1098 0.8932 0.0256
-10.250 -0.0158 0.07938 0.07705 -0.1140 0.8671 0.0257
-10.000 -0.0048 0.07704 0.07460 -0.1157 0.8439 0.0259
-9.750 0.0039 0.07503 0.07250 -0.1165 0.8251 0.0262
-9.500 0.0093 0.07265 0.07004 -0.1173 0.8092 0.0264
-9.250 0.0120 0.06995 0.06729 -0.1182 0.7946 0.0267
-9.000 -0.0970 0.04627 0.04342 -0.1366 0.7759 0.0291
-8.750 -0.1327 0.04293 0.03986 -0.1334 0.7621 0.0291
-8.500 -0.1485 0.03999 0.03670 -0.1312 0.7515 0.0292
-8.250 -0.1761 0.03385 0.03025 -0.1283 0.7419 0.0295
-8.000 -0.1624 0.03222 0.02860 -0.1272 0.7337 0.0297
-7.750 -0.1503 0.03075 0.02702 -0.1258 0.7254 0.0298
-7.500 -0.1367 0.02932 0.02550 -0.1246 0.7179 0.0300
-7.250 -0.1222 0.02803 0.02409 -0.1232 0.7103 0.0302
-7.000 -0.1072 0.02672 0.02266 -0.1219 0.7032 0.0305
-6.750 -0.0913 0.02542 0.02122 -0.1205 0.6963 0.0308
-6.500 -0.0753 0.02415 0.01977 -0.1190 0.6894 0.0313
-6.250 -0.0584 0.02283 0.01824 -0.1175 0.6832 0.0322
-6.000 -0.0503 0.02116 0.01594 -0.1142 0.6764 0.0340
-5.750 -0.0279 0.01991 0.01470 -0.1136 0.6691 0.0344
-5.500 -0.0053 0.01900 0.01375 -0.1128 0.6626 0.0348
-5.250 0.0098 0.01635 0.01040 -0.1096 0.6571 0.0294
-5.000 0.0338 0.01587 0.00979 -0.1088 0.6517 0.0293
-4.750 0.0592 0.01482 0.00875 -0.1083 0.6473 0.0288
-4.500 0.0838 0.01410 0.00794 -0.1076 0.6422 0.0288
-4.250 0.1084 0.01349 0.00724 -0.1068 0.6373 0.0287
-4.000 0.1335 0.01296 0.00664 -0.1061 0.6327 0.0288
-3.750 0.1596 0.01253 0.00616 -0.1056 0.6286 0.0289
-3.500 0.1854 0.01219 0.00577 -0.1050 0.6237 0.0290
-3.250 0.2111 0.01203 0.00553 -0.1044 0.6187 0.0292
-3.000 0.2347 0.01114 0.00465 -0.1036 0.6142 0.0297
-2.750 0.2602 0.01076 0.00427 -0.1029 0.6099 0.0300
-2.500 0.2854 0.01047 0.00397 -0.1023 0.6052 0.0303
-2.250 0.3104 0.01025 0.00373 -0.1016 0.6004 0.0306
-2.000 0.3361 0.01005 0.00352 -0.1010 0.5961 0.0311
-1.750 0.3621 0.00984 0.00332 -0.1004 0.5914 0.0315
-1.500 0.3875 0.00969 0.00314 -0.0998 0.5861 0.0319
-1.250 0.4125 0.00957 0.00297 -0.0990 0.5805 0.0323
-1.000 0.4389 0.00941 0.00283 -0.0986 0.5757 0.0327
-0.750 0.4648 0.00930 0.00270 -0.0980 0.5701 0.0332
-0.500 0.4901 0.00925 0.00260 -0.0973 0.5643 0.0335
-0.250 0.5155 0.00904 0.00239 -0.0967 0.5591 0.0345
0.000 0.5413 0.00895 0.00230 -0.0961 0.5529 0.0358
0.250 0.5662 0.00892 0.00223 -0.0954 0.5458 0.0369
0.500 0.5924 0.00886 0.00217 -0.0949 0.5382 0.0381
0.750 0.6166 0.00885 0.00211 -0.0940 0.5288 0.0397
1.000 0.6422 0.00882 0.00207 -0.0934 0.5189 0.0427
1.250 0.6649 0.00866 0.00204 -0.0923 0.5097 0.1033
1.500 0.6847 0.00826 0.00209 -0.0908 0.5000 0.2778
1.750 0.7054 0.00803 0.00217 -0.0894 0.4907 0.4000
2.000 0.7207 0.00762 0.00227 -0.0869 0.4806 0.6107
2.250 0.8404 0.00728 0.00272 -0.1071 0.4607 0.9887
2.500 0.9108 0.00755 0.00285 -0.1165 0.4444 0.9999
2.750 0.9331 0.00770 0.00293 -0.1153 0.4325 1.0000
3.000 0.9546 0.00785 0.00302 -0.1140 0.4229 1.0000
3.250 0.9755 0.00803 0.00313 -0.1126 0.4132 1.0000
3.500 0.9973 0.00817 0.00323 -0.1114 0.4051 1.0000
3.750 1.0179 0.00835 0.00335 -0.1099 0.3964 1.0000
4.000 1.0396 0.00850 0.00346 -0.1086 0.3892 1.0000
4.250 1.0602 0.00868 0.00359 -0.1072 0.3815 1.0000
4.500 1.0812 0.00885 0.00373 -0.1058 0.3752 1.0000
4.750 1.1026 0.00900 0.00385 -0.1045 0.3694 1.0000
5.000 1.1223 0.00920 0.00401 -0.1029 0.3632 1.0000
5.250 1.1432 0.00936 0.00416 -0.1015 0.3581 1.0000
5.500 1.1640 0.00952 0.00430 -0.1002 0.3530 1.0000
5.750 1.1834 0.00972 0.00447 -0.0985 0.3481 1.0000
6.000 1.2026 0.00992 0.00465 -0.0969 0.3434 1.0000
6.250 1.2234 0.01006 0.00480 -0.0955 0.3395 1.0000
6.500 1.2425 0.01025 0.00498 -0.0938 0.3351 1.0000
6.750 1.2575 0.01046 0.00517 -0.0913 0.3305 1.0000
7.000 1.2732 0.01065 0.00535 -0.0890 0.3268 1.0000
7.250 1.2916 0.01079 0.00551 -0.0872 0.3231 1.0000
7.500 1.3078 0.01101 0.00571 -0.0850 0.3174 1.0000
7.750 1.3223 0.01130 0.00597 -0.0826 0.3117 1.0000
8.000 1.3425 0.01146 0.00616 -0.0813 0.3078 1.0000
8.250 1.3609 0.01169 0.00638 -0.0797 0.3032 1.0000
8.500 1.3776 0.01198 0.00667 -0.0779 0.2986 1.0000
8.750 1.3954 0.01226 0.00695 -0.0763 0.2934 1.0000
9.000 1.4145 0.01251 0.00721 -0.0749 0.2887 1.0000
9.250 1.4311 0.01285 0.00755 -0.0732 0.2832 1.0000
9.500 1.4481 0.01321 0.00790 -0.0717 0.2782 1.0000
9.750 1.4663 0.01353 0.00824 -0.0703 0.2718 1.0000
10.000 1.4808 0.01402 0.00870 -0.0685 0.2648 1.0000
10.250 1.4980 0.01442 0.00911 -0.0671 0.2570 1.0000
10.500 1.5103 0.01506 0.00970 -0.0651 0.2448 1.0000
10.750 1.5205 0.01584 0.01041 -0.0630 0.2296 1.0000
11.000 1.5274 0.01683 0.01132 -0.0606 0.2116 1.0000
11.250 1.5338 0.01792 0.01233 -0.0582 0.1971 1.0000
11.500 1.5401 0.01907 0.01342 -0.0561 0.1857 1.0000
11.750 1.5479 0.02019 0.01452 -0.0542 0.1783 1.0000
12.000 1.5596 0.02111 0.01545 -0.0528 0.1739 1.0000
12.250 1.5704 0.02212 0.01648 -0.0514 0.1702 1.0000
12.500 1.5771 0.02343 0.01779 -0.0498 0.1646 1.0000
12.750 1.5897 0.02438 0.01877 -0.0487 0.1618 1.0000
13.000 1.6010 0.02543 0.01986 -0.0476 0.1589 1.0000
13.250 1.6102 0.02667 0.02113 -0.0464 0.1559 1.0000
13.500 1.6170 0.02811 0.02259 -0.0452 0.1520 1.0000
13.750 1.6267 0.02937 0.02389 -0.0441 0.1494 1.0000
14.000 1.6379 0.03052 0.02509 -0.0433 0.1460 1.0000
14.250 1.6467 0.03190 0.02650 -0.0424 0.1427 1.0000
14.500 1.6512 0.03367 0.02828 -0.0413 0.1384 1.0000
14.750 1.6597 0.03513 0.02979 -0.0405 0.1347 1.0000
15.000 1.6673 0.03669 0.03138 -0.0397 0.1299 1.0000
15.250 1.6694 0.03877 0.03345 -0.0387 0.1240 1.0000
15.500 1.6726 0.04080 0.03550 -0.0379 0.1160 1.0000
15.750 1.6689 0.04353 0.03819 -0.0369 0.1055 1.0000
16.000 1.6598 0.04683 0.04145 -0.0359 0.0945 1.0000
16.250 1.6523 0.05009 0.04470 -0.0351 0.0875 1.0000
16.500 1.6442 0.05350 0.04812 -0.0345 0.0820 1.0000
16.750 1.6423 0.05631 0.05098 -0.0341 0.0791 1.0000
17.000 1.6378 0.05947 0.05418 -0.0337 0.0763 1.0000
17.250 1.6320 0.06285 0.05761 -0.0335 0.0736 1.0000
17.500 1.6300 0.06586 0.06069 -0.0334 0.0715 1.0000
17.750 1.6264 0.06905 0.06394 -0.0333 0.0693 1.0000
18.000 1.6207 0.07257 0.06751 -0.0334 0.0673 1.0000
18.250 1.6132 0.07639 0.07138 -0.0336 0.0652 1.0000
18.500 1.6102 0.07968 0.07475 -0.0338 0.0638 1.0000
18.750 1.6079 0.08288 0.07803 -0.0341 0.0626 1.0000
19.000 1.6027 0.08651 0.08171 -0.0345 0.0607 1.0000
19.250 1.5947 0.09055 0.08581 -0.0350 0.0590 1.0000
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