GOE 429 AIRFOIL (goe429-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 429 AIRFOIL (goe429-il) Reynolds number: 200,000 Max Cl/Cd: 45.33 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe429-il-200000-n5.txt Download as CSV file: xf-goe429-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 429 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
------ -------- --------- --------- -------- -------- --------
-17.000 -0.9774 0.15774 0.15401 0.0580 1.0000 0.0176
-16.750 -1.0144 0.14316 0.13926 0.0498 1.0000 0.0175
-16.500 -1.0393 0.13259 0.12854 0.0439 1.0000 0.0175
-16.250 -1.0604 0.12338 0.11919 0.0388 1.0000 0.0175
-16.000 -1.0797 0.11490 0.11057 0.0342 1.0000 0.0175
-15.750 -1.0981 0.10687 0.10240 0.0298 1.0000 0.0176
-15.500 -1.1154 0.09927 0.09466 0.0257 1.0000 0.0176
-15.250 -1.1322 0.09202 0.08726 0.0218 1.0000 0.0177
-15.000 -1.1484 0.08513 0.08022 0.0181 1.0000 0.0177
-14.750 -1.1637 0.07864 0.07358 0.0147 1.0000 0.0178
-14.500 -1.1774 0.07250 0.06728 0.0114 1.0000 0.0179
-14.250 -1.1901 0.06668 0.06133 0.0083 1.0000 0.0180
-14.000 -1.2021 0.06108 0.05560 0.0052 1.0000 0.0182
-13.750 -1.2121 0.05589 0.05028 0.0023 1.0000 0.0184
-13.500 -1.2198 0.05118 0.04544 -0.0003 1.0000 0.0186
-13.250 -1.2251 0.04700 0.04112 -0.0025 1.0000 0.0189
-13.000 -1.2278 0.04333 0.03732 -0.0043 1.0000 0.0193
-12.750 -1.2282 0.04011 0.03395 -0.0057 1.0000 0.0197
-12.500 -1.2268 0.03732 0.03101 -0.0067 1.0000 0.0203
-12.250 -1.2239 0.03505 0.02859 -0.0067 1.0000 0.0210
-12.000 -1.2179 0.03325 0.02662 -0.0059 1.0000 0.0219
-11.750 -1.2086 0.03145 0.02471 -0.0054 1.0000 0.0229
-11.500 -1.1954 0.02994 0.02311 -0.0048 1.0000 0.0242
-11.250 -1.1797 0.02858 0.02161 -0.0043 1.0000 0.0258
-11.000 -1.1630 0.02724 0.02017 -0.0038 1.0000 0.0276
-10.750 -1.1445 0.02605 0.01891 -0.0034 1.0000 0.0301
-10.500 -1.1245 0.02495 0.01773 -0.0030 1.0000 0.0334
-10.250 -1.1031 0.02401 0.01672 -0.0027 1.0000 0.0378
-10.000 -1.0810 0.02313 0.01582 -0.0024 1.0000 0.0425
-9.750 -1.0577 0.02236 0.01498 -0.0022 1.0000 0.0475
-9.500 -1.0335 0.02172 0.01428 -0.0020 1.0000 0.0527
-9.250 -1.0092 0.02107 0.01357 -0.0019 1.0000 0.0576
-9.000 -0.9840 0.02053 0.01296 -0.0017 1.0000 0.0625
-8.750 -0.9588 0.01995 0.01231 -0.0016 1.0000 0.0670
-8.500 -0.9333 0.01941 0.01174 -0.0015 1.0000 0.0717
-8.250 -0.9068 0.01900 0.01120 -0.0015 1.0000 0.0765
-8.000 -0.8815 0.01838 0.01062 -0.0014 1.0000 0.0824
-7.750 -0.8548 0.01797 0.01012 -0.0014 1.0000 0.0880
-7.500 -0.8291 0.01732 0.00947 -0.0014 1.0000 0.0929
-7.250 -0.8027 0.01677 0.00888 -0.0013 1.0000 0.0977
-7.000 -0.7757 0.01630 0.00833 -0.0013 1.0000 0.1022
-6.750 -0.7493 0.01570 0.00774 -0.0013 1.0000 0.1075
-6.500 -0.7222 0.01519 0.00722 -0.0014 1.0000 0.1140
-6.250 -0.6950 0.01469 0.00672 -0.0015 1.0000 0.1212
-6.000 -0.6676 0.01419 0.00626 -0.0016 1.0000 0.1314
-5.750 -0.6402 0.01367 0.00584 -0.0018 1.0000 0.1484
-5.500 -0.6125 0.01321 0.00551 -0.0020 1.0000 0.1752
-5.250 -0.5844 0.01282 0.00521 -0.0022 1.0000 0.1999
-5.000 -0.5560 0.01249 0.00492 -0.0024 1.0000 0.2211
-4.750 -0.5275 0.01214 0.00465 -0.0027 1.0000 0.2401
-4.500 -0.4988 0.01182 0.00441 -0.0030 1.0000 0.2583
-4.250 -0.4686 0.01154 0.00421 -0.0037 0.9810 0.2788
-3.750 -0.4045 0.01117 0.00393 -0.0053 0.9148 0.3235
-3.500 -0.3779 0.01104 0.00383 -0.0048 0.8916 0.3486
-3.250 -0.3522 0.01091 0.00374 -0.0041 0.8693 0.3737
-3.000 -0.3265 0.01082 0.00363 -0.0033 0.8478 0.3954
-2.750 -0.3004 0.01070 0.00354 -0.0027 0.8277 0.4185
-2.500 -0.2737 0.01060 0.00345 -0.0021 0.8103 0.4416
-2.250 -0.2466 0.01052 0.00337 -0.0017 0.7941 0.4621
-2.000 -0.2195 0.01043 0.00330 -0.0013 0.7785 0.4841
-1.750 -0.1922 0.01035 0.00323 -0.0008 0.7623 0.5058
-1.500 -0.1648 0.01031 0.00317 -0.0004 0.7449 0.5245
-1.250 -0.1371 0.01027 0.00312 -0.0001 0.7283 0.5419
-1.000 -0.1092 0.01024 0.00311 0.0002 0.7135 0.5598
-0.750 -0.0811 0.01022 0.00310 0.0005 0.6994 0.5776
-0.500 -0.0529 0.01022 0.00310 0.0007 0.6845 0.5947
-0.250 -0.0245 0.01022 0.00311 0.0009 0.6683 0.6111
0.000 0.0039 0.01023 0.00311 0.0011 0.6498 0.6267
0.250 0.0323 0.01025 0.00311 0.0013 0.6279 0.6420
0.500 0.0606 0.01029 0.00310 0.0015 0.6030 0.6567
0.750 0.0888 0.01033 0.00309 0.0017 0.5740 0.6722
1.000 0.1168 0.01040 0.00311 0.0020 0.5397 0.6893
1.250 0.1445 0.01050 0.00312 0.0022 0.4984 0.7054
1.500 0.1723 0.01067 0.00314 0.0024 0.4530 0.7196
1.750 0.2001 0.01088 0.00320 0.0025 0.4118 0.7321
2.000 0.2279 0.01106 0.00329 0.0027 0.3766 0.7428
2.250 0.2559 0.01125 0.00340 0.0027 0.3461 0.7536
2.500 0.2840 0.01144 0.00352 0.0027 0.3189 0.7652
2.750 0.3116 0.01161 0.00366 0.0029 0.2954 0.7765
3.000 0.3391 0.01181 0.00382 0.0030 0.2717 0.7889
3.250 0.3663 0.01202 0.00398 0.0032 0.2483 0.8026
3.500 0.3931 0.01221 0.00415 0.0035 0.2274 0.8184
3.750 0.4196 0.01238 0.00433 0.0039 0.2108 0.8380
4.000 0.4458 0.01253 0.00451 0.0044 0.1977 0.8647
4.250 0.4734 0.01265 0.00471 0.0047 0.1878 0.9096
4.500 0.5093 0.01280 0.00491 0.0032 0.1776 1.0000
4.750 0.5379 0.01307 0.00515 0.0029 0.1689 1.0000
5.000 0.5662 0.01337 0.00540 0.0027 0.1569 1.0000
5.250 0.5945 0.01367 0.00566 0.0025 0.1444 1.0000
5.500 0.6226 0.01398 0.00593 0.0023 0.1304 1.0000
5.750 0.6505 0.01435 0.00625 0.0022 0.1136 1.0000
6.000 0.6770 0.01507 0.00668 0.0020 0.0668 1.0000
6.250 0.7034 0.01579 0.00729 0.0019 0.0582 1.0000
6.500 0.7305 0.01633 0.00786 0.0019 0.0547 1.0000
6.750 0.7573 0.01688 0.00849 0.0019 0.0522 1.0000
7.000 0.7835 0.01752 0.00917 0.0020 0.0499 1.0000
7.250 0.8091 0.01827 0.00997 0.0020 0.0478 1.0000
7.500 0.8344 0.01902 0.01079 0.0021 0.0465 1.0000
7.750 0.8599 0.01967 0.01152 0.0022 0.0457 1.0000
8.000 0.8849 0.02038 0.01231 0.0024 0.0448 1.0000
8.250 0.9093 0.02115 0.01316 0.0026 0.0439 1.0000
8.500 0.9332 0.02198 0.01407 0.0028 0.0429 1.0000
8.750 0.9565 0.02285 0.01500 0.0031 0.0418 1.0000
9.000 0.9790 0.02380 0.01599 0.0034 0.0407 1.0000
9.250 1.0007 0.02486 0.01708 0.0038 0.0399 1.0000
9.500 1.0213 0.02609 0.01834 0.0042 0.0391 1.0000
9.750 1.0407 0.02762 0.01989 0.0048 0.0383 1.0000
10.000 1.0622 0.02857 0.02098 0.0052 0.0376 1.0000
10.250 1.0828 0.02962 0.02217 0.0057 0.0368 1.0000
10.500 1.1023 0.03080 0.02349 0.0062 0.0360 1.0000
10.750 1.1208 0.03208 0.02489 0.0068 0.0352 1.0000
11.000 1.1380 0.03339 0.02633 0.0073 0.0343 1.0000
11.250 1.1541 0.03473 0.02778 0.0079 0.0335 1.0000
11.500 1.1688 0.03616 0.02929 0.0085 0.0327 1.0000
11.750 1.1819 0.03778 0.03096 0.0092 0.0320 1.0000
12.000 1.1927 0.03999 0.03322 0.0099 0.0313 1.0000
12.250 1.1967 0.04172 0.03519 0.0110 0.0308 1.0000
12.500 1.1972 0.04383 0.03755 0.0116 0.0303 1.0000
12.750 1.1963 0.04638 0.04031 0.0115 0.0298 1.0000
13.000 1.1940 0.04933 0.04348 0.0108 0.0293 1.0000
13.250 1.1903 0.05268 0.04702 0.0095 0.0288 1.0000
13.500 1.1846 0.05651 0.05104 0.0078 0.0284 1.0000
13.750 1.1771 0.06080 0.05551 0.0055 0.0280 1.0000
14.000 1.1677 0.06559 0.06048 0.0026 0.0277 1.0000
14.250 1.1562 0.07098 0.06603 -0.0008 0.0274 1.0000
14.500 1.1424 0.07705 0.07227 -0.0047 0.0272 1.0000
14.750 1.1252 0.08400 0.07940 -0.0093 0.0270 1.0000
15.000 1.1035 0.09210 0.08769 -0.0147 0.0269 1.0000
15.250 1.0722 0.10264 0.09845 -0.0217 0.0269 1.0000
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Polar data table (+)
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