GOE 600 AIRFOIL (goe600-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 600 AIRFOIL (goe600-il) Reynolds number: 200,000 Max Cl/Cd: 62.89 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe600-il-200000-n5.txt Download as CSV file: xf-goe600-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 600 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
------ -------- --------- --------- -------- -------- --------
-14.250 -0.7802 0.09332 0.08944 -0.0274 1.0000 0.0157
-14.000 -0.8286 0.07876 0.07463 -0.0368 1.0000 0.0153
-13.750 -0.8584 0.06892 0.06455 -0.0436 1.0000 0.0151
-13.500 -0.8794 0.06133 0.05675 -0.0490 1.0000 0.0151
-13.250 -0.8947 0.05521 0.05042 -0.0532 1.0000 0.0152
-13.000 -0.9058 0.05016 0.04516 -0.0564 1.0000 0.0153
-12.750 -0.9140 0.04593 0.04073 -0.0587 1.0000 0.0155
-12.500 -0.9198 0.04244 0.03703 -0.0598 1.0000 0.0157
-12.250 -0.9234 0.03958 0.03397 -0.0599 1.0000 0.0160
-12.000 -0.9252 0.03724 0.03142 -0.0590 1.0000 0.0164
-11.750 -0.9255 0.03529 0.02925 -0.0573 1.0000 0.0168
-11.500 -0.9216 0.03358 0.02731 -0.0554 1.0000 0.0173
-11.250 -0.9153 0.03191 0.02556 -0.0538 1.0000 0.0179
-11.000 -0.9046 0.03064 0.02421 -0.0525 1.0000 0.0185
-10.750 -0.8922 0.02946 0.02293 -0.0511 1.0000 0.0192
-10.500 -0.8792 0.02827 0.02161 -0.0496 1.0000 0.0199
-10.250 -0.8662 0.02710 0.02031 -0.0480 1.0000 0.0208
-10.000 -0.8534 0.02602 0.01907 -0.0461 1.0000 0.0217
-9.750 -0.8417 0.02503 0.01800 -0.0440 1.0000 0.0227
-9.500 -0.8291 0.02432 0.01727 -0.0420 1.0000 0.0239
-9.250 -0.8086 0.02356 0.01642 -0.0415 0.9977 0.0257
-9.000 -0.7780 0.02257 0.01526 -0.0428 0.9928 0.0279
-8.750 -0.7483 0.02162 0.01427 -0.0442 0.9873 0.0302
-8.500 -0.7168 0.02090 0.01344 -0.0456 0.9820 0.0337
-8.250 -0.6868 0.02008 0.01256 -0.0468 0.9756 0.0371
-8.000 -0.6563 0.01943 0.01182 -0.0479 0.9691 0.0411
-7.750 -0.6265 0.01868 0.01098 -0.0489 0.9625 0.0453
-7.500 -0.5975 0.01804 0.01027 -0.0496 0.9553 0.0499
-7.250 -0.5673 0.01750 0.00961 -0.0504 0.9484 0.0542
-7.000 -0.5403 0.01679 0.00889 -0.0508 0.9402 0.0598
-6.500 -0.4854 0.01574 0.00780 -0.0512 0.9239 0.0746
-6.250 -0.4580 0.01531 0.00742 -0.0513 0.9163 0.0873
-6.000 -0.4314 0.01500 0.00709 -0.0511 0.9074 0.1033
-5.750 -0.4042 0.01472 0.00674 -0.0510 0.8998 0.1172
-5.500 -0.3783 0.01441 0.00642 -0.0508 0.8902 0.1285
-5.250 -0.3519 0.01413 0.00609 -0.0505 0.8822 0.1389
-5.000 -0.3253 0.01391 0.00579 -0.0503 0.8732 0.1490
-4.750 -0.2992 0.01359 0.00547 -0.0501 0.8653 0.1596
-4.500 -0.2728 0.01333 0.00517 -0.0498 0.8570 0.1697
-4.250 -0.2466 0.01300 0.00489 -0.0497 0.8487 0.1869
-4.000 -0.2207 0.01261 0.00461 -0.0494 0.8408 0.2179
-3.750 -0.1950 0.01221 0.00440 -0.0493 0.8325 0.2733
-3.500 -0.1688 0.01189 0.00422 -0.0491 0.8255 0.3238
-3.250 -0.1424 0.01160 0.00408 -0.0489 0.8180 0.3749
-3.000 -0.1160 0.01135 0.00397 -0.0487 0.8112 0.4217
-2.750 -0.0889 0.01119 0.00389 -0.0485 0.8043 0.4566
-2.500 -0.0615 0.01108 0.00380 -0.0484 0.7975 0.4835
-2.250 -0.0340 0.01098 0.00374 -0.0483 0.7918 0.5112
-2.000 -0.0062 0.01091 0.00369 -0.0483 0.7854 0.5358
-1.750 0.0215 0.01084 0.00363 -0.0482 0.7799 0.5573
-1.500 0.0493 0.01078 0.00359 -0.0481 0.7729 0.5787
-1.250 0.0770 0.01073 0.00352 -0.0479 0.7655 0.5973
-1.000 0.1045 0.01066 0.00348 -0.0478 0.7574 0.6160
-0.750 0.1318 0.01060 0.00344 -0.0475 0.7495 0.6372
-0.500 0.1591 0.01054 0.00342 -0.0473 0.7411 0.6586
-0.250 0.1862 0.01048 0.00340 -0.0470 0.7335 0.6817
0.000 0.2130 0.01041 0.00343 -0.0466 0.7263 0.7101
0.250 0.2395 0.01034 0.00347 -0.0461 0.7198 0.7420
0.500 0.2658 0.01030 0.00352 -0.0455 0.7137 0.7742
0.750 0.2922 0.01026 0.00359 -0.0450 0.7066 0.8050
1.000 0.3190 0.01026 0.00362 -0.0444 0.7006 0.8351
1.250 0.3466 0.01026 0.00372 -0.0441 0.6929 0.8665
1.500 0.3764 0.01029 0.00377 -0.0442 0.6859 0.8980
1.750 0.4097 0.01033 0.00386 -0.0452 0.6775 0.9270
2.000 0.4457 0.01038 0.00389 -0.0467 0.6693 0.9511
2.250 0.4823 0.01043 0.00397 -0.0486 0.6588 0.9712
2.500 0.5202 0.01049 0.00402 -0.0508 0.6472 0.9863
2.750 0.5589 0.01054 0.00405 -0.0532 0.6328 0.9983
3.000 0.5851 0.01060 0.00408 -0.0529 0.6173 1.0000
3.250 0.6091 0.01068 0.00412 -0.0522 0.6002 1.0000
3.500 0.6332 0.01077 0.00417 -0.0515 0.5808 1.0000
3.750 0.6574 0.01089 0.00424 -0.0508 0.5594 1.0000
4.000 0.6817 0.01104 0.00434 -0.0501 0.5353 1.0000
4.250 0.7054 0.01125 0.00444 -0.0493 0.5048 1.0000
4.500 0.7276 0.01157 0.00458 -0.0483 0.4664 1.0000
4.750 0.7493 0.01199 0.00480 -0.0473 0.4316 1.0000
5.000 0.7716 0.01240 0.00508 -0.0464 0.4045 1.0000
5.250 0.7942 0.01282 0.00539 -0.0457 0.3802 1.0000
5.500 0.8174 0.01320 0.00572 -0.0450 0.3584 1.0000
5.750 0.8407 0.01357 0.00605 -0.0443 0.3387 1.0000
6.000 0.8637 0.01397 0.00639 -0.0436 0.3192 1.0000
6.250 0.8862 0.01440 0.00677 -0.0429 0.2957 1.0000
6.500 0.9076 0.01490 0.00717 -0.0420 0.2697 1.0000
6.750 0.9288 0.01541 0.00760 -0.0411 0.2440 1.0000
7.000 0.9500 0.01592 0.00805 -0.0403 0.2228 1.0000
7.250 0.9709 0.01646 0.00853 -0.0393 0.2022 1.0000
7.500 0.9906 0.01707 0.00907 -0.0383 0.1813 1.0000
7.750 1.0103 0.01768 0.00962 -0.0372 0.1610 1.0000
8.000 1.0292 0.01832 0.01021 -0.0361 0.1423 1.0000
8.250 1.0476 0.01900 0.01082 -0.0349 0.1241 1.0000
8.500 1.0655 0.01969 0.01148 -0.0336 0.1079 1.0000
8.750 1.0821 0.02044 0.01218 -0.0322 0.0940 1.0000
9.000 1.0979 0.02123 0.01294 -0.0307 0.0830 1.0000
9.250 1.1118 0.02207 0.01377 -0.0289 0.0727 1.0000
9.500 1.1255 0.02283 0.01455 -0.0270 0.0616 1.0000
9.750 1.1383 0.02368 0.01539 -0.0252 0.0498 1.0000
10.250 1.1597 0.02579 0.01750 -0.0213 0.0377 1.0000
10.500 1.1679 0.02709 0.01881 -0.0193 0.0343 1.0000
10.750 1.1780 0.02828 0.02011 -0.0177 0.0318 1.0000
11.000 1.1866 0.02962 0.02154 -0.0160 0.0297 1.0000
11.250 1.1923 0.03124 0.02323 -0.0144 0.0279 1.0000
11.500 1.1973 0.03297 0.02506 -0.0128 0.0264 1.0000
11.750 1.2050 0.03453 0.02675 -0.0116 0.0250 1.0000
12.000 1.2115 0.03626 0.02861 -0.0104 0.0236 1.0000
12.250 1.2161 0.03819 0.03064 -0.0094 0.0225 1.0000
12.500 1.2176 0.04048 0.03301 -0.0084 0.0216 1.0000
12.750 1.2174 0.04302 0.03564 -0.0075 0.0209 1.0000
13.000 1.2216 0.04520 0.03797 -0.0068 0.0202 1.0000
13.250 1.2244 0.04758 0.04050 -0.0063 0.0194 1.0000
13.500 1.2261 0.05013 0.04317 -0.0059 0.0186 1.0000
13.750 1.2271 0.05280 0.04596 -0.0056 0.0179 1.0000
14.000 1.2270 0.05567 0.04894 -0.0056 0.0174 1.0000
14.250 1.2254 0.05878 0.05215 -0.0058 0.0169 1.0000
14.500 1.2216 0.06224 0.05572 -0.0061 0.0164 1.0000
14.750 1.2171 0.06592 0.05949 -0.0065 0.0161 1.0000
15.000 1.2147 0.06950 0.06324 -0.0071 0.0157 1.0000
15.250 1.2111 0.07333 0.06724 -0.0079 0.0154 1.0000
15.500 1.2067 0.07742 0.07148 -0.0089 0.0151 1.0000
15.750 1.2017 0.08172 0.07594 -0.0101 0.0148 1.0000
16.000 1.1957 0.08627 0.08064 -0.0116 0.0146 1.0000
16.250 1.1892 0.09107 0.08559 -0.0134 0.0143 1.0000
16.500 1.1820 0.09611 0.09078 -0.0154 0.0141 1.0000
16.750 1.1742 0.10139 0.09621 -0.0177 0.0139 1.0000
17.000 1.1657 0.10690 0.10186 -0.0202 0.0137 1.0000
17.250 1.1568 0.11261 0.10771 -0.0230 0.0135 1.0000
17.500 1.1474 0.11855 0.11378 -0.0260 0.0133 1.0000
17.750 1.1378 0.12469 0.12006 -0.0293 0.0132 1.0000
18.000 1.1278 0.13101 0.12650 -0.0328 0.0130 1.0000
18.250 1.1173 0.13760 0.13323 -0.0365 0.0129 1.0000
18.500 1.1065 0.14448 0.14023 -0.0405 0.0128 1.0000
18.750 1.0947 0.15185 0.14772 -0.0450 0.0127 1.0000
19.000 1.0801 0.16028 0.15630 -0.0502 0.0127 1.0000
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