GOE 286 AIRFOIL (goe286-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 286 AIRFOIL (goe286-il) Reynolds number: 1,000,000 Max Cl/Cd: 89.87 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe286-il-1000000-n5.txt Download as CSV file: xf-goe286-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 286 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4483 0.09149 0.08994 -0.0127 0.9787 0.0106
-9.000 -0.4451 0.08789 0.08632 -0.0147 0.9626 0.0109
-8.500 -0.4650 0.07295 0.07134 -0.0276 0.9369 0.0126
-8.250 -0.4539 0.06966 0.06800 -0.0310 0.9158 0.0128
-8.000 -0.4429 0.06651 0.06467 -0.0339 0.8655 0.0129
-7.500 -0.4261 0.03954 0.03705 -0.0582 0.8375 0.0160
-7.250 -0.4040 0.03747 0.03475 -0.0590 0.8091 0.0162
-7.000 -0.3995 0.01992 0.01588 -0.0631 0.8089 0.0190
-6.750 -0.3742 0.01865 0.01424 -0.0630 0.7824 0.0194
-6.500 -0.3489 0.01734 0.01258 -0.0630 0.7485 0.0197
-6.250 -0.3233 0.01635 0.01122 -0.0630 0.6841 0.0200
-6.000 -0.2963 0.01592 0.01055 -0.0630 0.6452 0.0202
-5.750 -0.2686 0.01563 0.01012 -0.0631 0.6270 0.0205
-5.500 -0.2408 0.01529 0.00967 -0.0631 0.6146 0.0207
-5.250 -0.2130 0.01479 0.00904 -0.0632 0.6059 0.0210
-5.000 -0.1851 0.01421 0.00832 -0.0632 0.5979 0.0212
-4.750 -0.1571 0.01367 0.00767 -0.0633 0.5910 0.0215
-4.500 -0.1290 0.01313 0.00701 -0.0633 0.5831 0.0217
-4.250 -0.1007 0.01266 0.00642 -0.0634 0.5756 0.0220
-4.000 -0.0724 0.01220 0.00587 -0.0634 0.5679 0.0223
-3.750 -0.0440 0.01184 0.00540 -0.0635 0.5548 0.0226
-3.500 -0.0156 0.01157 0.00501 -0.0635 0.5364 0.0231
-3.250 0.0128 0.01128 0.00459 -0.0636 0.5138 0.0233
-3.000 0.0409 0.01112 0.00423 -0.0637 0.4729 0.0236
-2.750 0.0690 0.01105 0.00396 -0.0637 0.4306 0.0238
-2.500 0.0972 0.01097 0.00372 -0.0638 0.4019 0.0240
-2.250 0.1256 0.01087 0.00352 -0.0639 0.3823 0.0242
-2.000 0.1541 0.01077 0.00333 -0.0640 0.3652 0.0243
-1.750 0.1824 0.01060 0.00306 -0.0640 0.3477 0.0245
-1.500 0.2106 0.01037 0.00272 -0.0641 0.3298 0.0249
-1.250 0.2390 0.01024 0.00251 -0.0642 0.3129 0.0252
-1.000 0.2674 0.01016 0.00235 -0.0643 0.2977 0.0255
-0.750 0.2958 0.01014 0.00224 -0.0644 0.2782 0.0259
-0.500 0.3241 0.01017 0.00216 -0.0645 0.2560 0.0264
-0.250 0.3522 0.01026 0.00213 -0.0646 0.2291 0.0270
0.000 0.3786 0.01085 0.00231 -0.0647 0.1241 0.0275
0.250 0.4070 0.01087 0.00229 -0.0647 0.1184 0.0281
0.500 0.4354 0.01090 0.00229 -0.0648 0.1131 0.0287
0.750 0.4638 0.01092 0.00229 -0.0649 0.1099 0.0293
1.000 0.4922 0.01095 0.00230 -0.0649 0.1085 0.0299
1.250 0.5206 0.01098 0.00232 -0.0650 0.1080 0.0303
1.500 0.5490 0.01101 0.00235 -0.0651 0.1072 0.0311
1.750 0.5773 0.01106 0.00238 -0.0652 0.1060 0.0326
2.000 0.6055 0.01111 0.00245 -0.0652 0.1047 0.0352
2.250 0.6337 0.01113 0.00253 -0.0653 0.1035 0.0675
2.500 0.6618 0.01108 0.00264 -0.0655 0.1025 0.1402
2.750 0.6895 0.01063 0.00282 -0.0658 0.1013 0.4256
3.250 0.7415 0.00955 0.00310 -0.0652 0.0988 1.0000
3.750 0.7971 0.00988 0.00337 -0.0653 0.0958 1.0000
4.000 0.8249 0.01001 0.00348 -0.0653 0.0952 1.0000
4.250 0.8527 0.01014 0.00359 -0.0653 0.0945 1.0000
4.500 0.8805 0.01028 0.00372 -0.0654 0.0932 1.0000
4.750 0.9081 0.01043 0.00385 -0.0654 0.0906 1.0000
5.000 0.9354 0.01063 0.00400 -0.0654 0.0844 1.0000
5.250 0.9614 0.01104 0.00425 -0.0653 0.0580 1.0000
5.500 0.9882 0.01130 0.00449 -0.0652 0.0550 1.0000
5.750 1.0150 0.01154 0.00472 -0.0651 0.0527 1.0000
6.000 1.0419 0.01177 0.00495 -0.0650 0.0509 1.0000
6.250 1.0686 0.01199 0.00519 -0.0650 0.0497 1.0000
6.500 1.0952 0.01223 0.00544 -0.0649 0.0485 1.0000
6.750 1.1216 0.01249 0.00571 -0.0648 0.0472 1.0000
7.000 1.1477 0.01277 0.00599 -0.0646 0.0459 1.0000
7.250 1.1734 0.01308 0.00632 -0.0644 0.0443 1.0000
7.500 1.1989 0.01342 0.00667 -0.0642 0.0426 1.0000
7.750 1.2247 0.01369 0.00696 -0.0640 0.0418 1.0000
8.000 1.2505 0.01393 0.00722 -0.0639 0.0407 1.0000
8.250 1.2759 0.01422 0.00751 -0.0637 0.0383 1.0000
8.500 1.3005 0.01459 0.00787 -0.0634 0.0350 1.0000
8.750 1.3241 0.01504 0.00824 -0.0630 0.0224 1.0000
9.000 1.3456 0.01572 0.00887 -0.0623 0.0139 1.0000
9.250 1.3682 0.01625 0.00942 -0.0617 0.0118 1.0000
9.500 1.3911 0.01670 0.00992 -0.0611 0.0107 1.0000
9.750 1.4136 0.01717 0.01042 -0.0605 0.0099 1.0000
10.000 1.4352 0.01769 0.01098 -0.0598 0.0091 1.0000
10.250 1.4556 0.01830 0.01162 -0.0590 0.0084 1.0000
10.500 1.4762 0.01885 0.01222 -0.0581 0.0080 1.0000
10.750 1.4962 0.01940 0.01282 -0.0573 0.0077 1.0000
11.000 1.5153 0.02000 0.01346 -0.0562 0.0073 1.0000
11.250 1.5332 0.02064 0.01415 -0.0551 0.0069 1.0000
11.500 1.5495 0.02134 0.01489 -0.0537 0.0065 1.0000
11.750 1.5627 0.02215 0.01576 -0.0519 0.0061 1.0000
12.000 1.5716 0.02303 0.01671 -0.0494 0.0059 1.0000
12.250 1.5820 0.02388 0.01763 -0.0474 0.0057 1.0000
12.500 1.5916 0.02486 0.01868 -0.0455 0.0056 1.0000
12.750 1.6006 0.02596 0.01985 -0.0437 0.0054 1.0000
13.000 1.6085 0.02721 0.02118 -0.0421 0.0053 1.0000
13.250 1.6155 0.02863 0.02268 -0.0406 0.0051 1.0000
13.500 1.6217 0.03024 0.02437 -0.0394 0.0050 1.0000
13.750 1.6267 0.03207 0.02628 -0.0384 0.0048 1.0000
14.000 1.6305 0.03414 0.02844 -0.0377 0.0047 1.0000
14.250 1.6329 0.03648 0.03087 -0.0372 0.0046 1.0000
14.500 1.6337 0.03914 0.03363 -0.0369 0.0045 1.0000
14.750 1.6326 0.04222 0.03680 -0.0370 0.0044 1.0000
15.000 1.6289 0.04576 0.04045 -0.0375 0.0043 1.0000
15.250 1.6228 0.04975 0.04456 -0.0382 0.0042 1.0000
15.500 1.6131 0.05424 0.04917 -0.0390 0.0042 1.0000
15.750 1.6009 0.05910 0.05416 -0.0400 0.0041 1.0000
16.000 1.5911 0.06375 0.05892 -0.0411 0.0041 1.0000
16.250 1.5799 0.06869 0.06398 -0.0424 0.0040 1.0000
16.500 1.5686 0.07383 0.06924 -0.0438 0.0040 1.0000
16.750 1.5563 0.07925 0.07477 -0.0455 0.0040 1.0000
17.000 1.5422 0.08500 0.08064 -0.0473 0.0040 1.0000
17.250 1.5291 0.09070 0.08644 -0.0492 0.0039 1.0000
17.500 1.5152 0.09659 0.09245 -0.0512 0.0039 1.0000
17.750 1.5004 0.10265 0.09862 -0.0533 0.0039 1.0000
18.000 1.4863 0.10871 0.10478 -0.0556 0.0039 1.0000
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