GOE 395 AIRFOIL (goe395-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 395 AIRFOIL (goe395-il) Reynolds number: 200,000 Max Cl/Cd: 100.79 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe395-il-200000-n5.txt Download as CSV file: xf-goe395-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 395 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.1691 0.11305 0.10937 -0.0432 0.8461 0.0226
-10.500 -0.1633 0.11015 0.10645 -0.0439 0.8410 0.0231
-10.250 -0.2707 0.12166 0.11797 -0.0357 0.8755 0.0211
-10.000 -0.2607 0.11816 0.11441 -0.0348 0.8652 0.0218
-9.750 -0.2528 0.11541 0.11162 -0.0355 0.8562 0.0223
-9.500 -0.2449 0.11264 0.10881 -0.0364 0.8484 0.0227
-9.250 -0.2367 0.10986 0.10599 -0.0375 0.8421 0.0233
-9.000 -0.2283 0.10705 0.10314 -0.0388 0.8364 0.0239
-8.750 -0.2198 0.10423 0.10029 -0.0401 0.8315 0.0247
-8.500 -0.2108 0.10180 0.09784 -0.0430 0.8266 0.0272
-8.250 -0.2023 0.09910 0.09512 -0.0454 0.8221 0.0274
-8.000 -0.1939 0.09649 0.09248 -0.0483 0.8180 0.0276
-7.750 -0.1851 0.09369 0.08967 -0.0511 0.8147 0.0277
-7.500 -0.1740 0.09032 0.08629 -0.0532 0.8114 0.0277
-7.250 -0.1634 0.08652 0.08248 -0.0514 0.8090 0.0262
-7.000 -0.1513 0.08332 0.07927 -0.0539 0.8061 0.0251
-6.750 -0.1366 0.08001 0.07592 -0.0573 0.8035 0.0248
-6.500 -0.1183 0.07660 0.07247 -0.0623 0.8011 0.0265
-6.250 -0.0948 0.07247 0.06830 -0.0699 0.7984 0.0274
-6.000 -0.0720 0.06850 0.06430 -0.0755 0.7957 0.0274
-5.750 -0.0469 0.06428 0.06003 -0.0819 0.7933 0.0285
-5.500 -0.0321 0.06373 0.05949 -0.0799 0.7915 0.0309
-5.250 -0.0055 0.06088 0.05658 -0.0846 0.7895 0.0335
-5.000 0.0245 0.05705 0.05267 -0.0909 0.7878 0.0334
-4.750 0.0577 0.05317 0.04869 -0.0976 0.7862 0.0339
-4.500 0.1047 0.04788 0.04323 -0.1089 0.7847 0.0362
-4.250 0.1449 0.04343 0.03864 -0.1166 0.7831 0.0365
-4.000 0.1847 0.03925 0.03433 -0.1238 0.7814 0.0381
-3.750 0.2100 0.03846 0.03352 -0.1246 0.7797 0.0397
-3.500 0.2531 0.03429 0.02914 -0.1317 0.7779 0.0398
-3.250 0.2963 0.03012 0.02470 -0.1381 0.7762 0.0402
-3.000 0.3390 0.02586 0.02007 -0.1438 0.7748 0.0411
-2.750 0.3837 0.02010 0.01356 -0.1498 0.7734 0.0434
-2.500 0.4191 0.01689 0.00958 -0.1522 0.7715 0.0446
-2.250 0.4492 0.01571 0.00803 -0.1528 0.7689 0.0459
-2.000 0.4784 0.01496 0.00704 -0.1531 0.7652 0.0472
-1.750 0.5070 0.01445 0.00643 -0.1533 0.7615 0.0489
-1.500 0.5353 0.01420 0.00613 -0.1533 0.7583 0.0510
-1.250 0.5635 0.01400 0.00584 -0.1532 0.7556 0.0544
-1.000 0.5917 0.01379 0.00558 -0.1532 0.7524 0.0594
-0.750 0.6196 0.01372 0.00554 -0.1531 0.7482 0.0651
-0.500 0.6476 0.01353 0.00530 -0.1530 0.7441 0.0729
-0.250 0.6755 0.01350 0.00521 -0.1527 0.7406 0.0811
0.000 0.7033 0.01343 0.00512 -0.1527 0.7369 0.0875
0.250 0.7309 0.01341 0.00513 -0.1526 0.7328 0.0938
0.500 0.7586 0.01341 0.00512 -0.1524 0.7290 0.1026
0.750 0.7862 0.01341 0.00512 -0.1522 0.7256 0.1112
1.000 0.8139 0.01333 0.00507 -0.1521 0.7217 0.1156
1.250 0.8413 0.01324 0.00505 -0.1520 0.7171 0.1190
1.500 0.8689 0.01316 0.00502 -0.1518 0.7129 0.1230
1.750 0.8966 0.01311 0.00494 -0.1516 0.7092 0.1279
2.000 0.9238 0.01307 0.00504 -0.1515 0.7036 0.1344
2.250 0.9510 0.01303 0.00505 -0.1513 0.6982 0.1417
2.500 0.9785 0.01296 0.00504 -0.1510 0.6933 0.1511
2.750 1.0054 0.01291 0.00514 -0.1508 0.6852 0.1667
3.000 1.0324 0.01279 0.00512 -0.1504 0.6777 0.2008
3.250 1.0582 0.01233 0.00539 -0.1501 0.6676 0.5305
3.750 1.1083 0.01168 0.00538 -0.1486 0.6448 1.0000
4.000 1.1346 0.01171 0.00545 -0.1482 0.6278 1.0000
4.250 1.1606 0.01173 0.00545 -0.1476 0.6029 1.0000
4.500 1.1853 0.01176 0.00529 -0.1466 0.5657 1.0000
4.750 1.2085 0.01203 0.00533 -0.1455 0.5319 1.0000
5.000 1.2309 0.01250 0.00558 -0.1444 0.5032 1.0000
5.250 1.2532 0.01302 0.00596 -0.1435 0.4757 1.0000
5.500 1.2754 0.01356 0.00637 -0.1425 0.4482 1.0000
5.750 1.2975 0.01409 0.00683 -0.1416 0.4236 1.0000
6.000 1.3198 0.01459 0.00727 -0.1407 0.4008 1.0000
6.250 1.3413 0.01513 0.00775 -0.1397 0.3765 1.0000
6.500 1.3625 0.01568 0.00825 -0.1387 0.3540 1.0000
6.750 1.3826 0.01630 0.00882 -0.1375 0.3267 1.0000
7.000 1.3995 0.01716 0.00949 -0.1360 0.2852 1.0000
7.250 1.4121 0.01835 0.01034 -0.1340 0.2239 1.0000
7.500 1.4220 0.01977 0.01139 -0.1316 0.1668 1.0000
7.750 1.4346 0.02094 0.01238 -0.1296 0.1377 1.0000
8.000 1.4484 0.02195 0.01331 -0.1277 0.1199 1.0000
8.250 1.4618 0.02292 0.01427 -0.1258 0.1041 1.0000
8.500 1.4740 0.02383 0.01516 -0.1236 0.0863 1.0000
8.750 1.4838 0.02492 0.01617 -0.1213 0.0672 1.0000
9.000 1.4912 0.02626 0.01741 -0.1188 0.0517 1.0000
9.250 1.4982 0.02767 0.01879 -0.1163 0.0348 1.0000
9.500 1.5029 0.02934 0.02037 -0.1138 0.0237 1.0000
9.750 1.5090 0.03096 0.02201 -0.1115 0.0200 1.0000
10.000 1.5162 0.03254 0.02371 -0.1095 0.0183 1.0000
10.250 1.5235 0.03414 0.02547 -0.1076 0.0171 1.0000
10.500 1.5296 0.03590 0.02736 -0.1057 0.0160 1.0000
10.750 1.5341 0.03783 0.02941 -0.1038 0.0150 1.0000
11.000 1.5357 0.04010 0.03180 -0.1019 0.0140 1.0000
11.250 1.5333 0.04281 0.03464 -0.0998 0.0132 1.0000
11.500 1.5368 0.04498 0.03696 -0.0982 0.0129 1.0000
11.750 1.5384 0.04736 0.03949 -0.0966 0.0125 1.0000
12.000 1.5390 0.04989 0.04217 -0.0951 0.0122 1.0000
12.250 1.5387 0.05256 0.04499 -0.0936 0.0118 1.0000
12.500 1.5376 0.05534 0.04791 -0.0921 0.0115 1.0000
12.750 1.5361 0.05823 0.05098 -0.0908 0.0113 1.0000
13.000 1.5345 0.06120 0.05408 -0.0896 0.0110 1.0000
13.250 1.5324 0.06427 0.05729 -0.0886 0.0106 1.0000
13.500 1.5301 0.06748 0.06062 -0.0877 0.0103 1.0000
13.750 1.5271 0.07087 0.06412 -0.0871 0.0100 1.0000
14.000 1.5228 0.07448 0.06785 -0.0866 0.0097 1.0000
14.250 1.5169 0.07838 0.07186 -0.0860 0.0094 1.0000
14.500 1.5113 0.08235 0.07595 -0.0856 0.0092 1.0000
14.750 1.5086 0.08616 0.07995 -0.0856 0.0090 1.0000
15.000 1.5048 0.09018 0.08416 -0.0858 0.0089 1.0000
15.250 1.5000 0.09446 0.08864 -0.0863 0.0088 1.0000
15.500 1.4944 0.09901 0.09337 -0.0870 0.0087 1.0000
15.750 1.4879 0.10384 0.09840 -0.0881 0.0086 1.0000
16.000 1.4806 0.10895 0.10371 -0.0895 0.0085 1.0000
16.250 1.4723 0.11438 0.10934 -0.0913 0.0084 1.0000
16.500 1.4632 0.12012 0.11528 -0.0936 0.0083 1.0000
16.750 1.4532 0.12626 0.12162 -0.0963 0.0083 1.0000
17.000 1.4428 0.13271 0.12827 -0.0994 0.0082 1.0000
17.250 1.4316 0.13955 0.13531 -0.1031 0.0082 1.0000
17.500 1.4196 0.14685 0.14280 -0.1074 0.0082 1.0000
17.750 1.4072 0.15455 0.15070 -0.1121 0.0082 1.0000
18.000 1.3943 0.16284 0.15918 -0.1175 0.0082 1.0000
18.250 1.3805 0.17184 0.16836 -0.1235 0.0082 1.0000
18.500 1.3659 0.18177 0.17847 -0.1303 0.0083 1.0000
18.750 1.3504 0.19280 0.18966 -0.1380 0.0084 1.0000
19.000 1.3313 0.20650 0.20351 -0.1473 0.0086 1.0000
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