GOE 590 AIRFOIL (goe590-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 590 AIRFOIL (goe590-il) Reynolds number: 50,000 Max Cl/Cd: 37.3 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe590-il-50000.txt Download as CSV file: xf-goe590-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 590 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4388 0.11294 0.10622 -0.0055 1.0000 0.1021
-8.500 -0.4427 0.11190 0.10529 -0.0083 1.0000 0.1040
-8.250 -0.4504 0.11144 0.10496 -0.0116 1.0000 0.1046
-8.000 -0.4263 0.10311 0.09659 -0.0086 1.0000 0.1102
-7.750 -0.4241 0.10040 0.09395 -0.0098 1.0000 0.1145
-7.500 -0.4273 0.09906 0.09272 -0.0131 1.0000 0.1174
-7.250 -0.4287 0.09894 0.09264 -0.0191 1.0000 0.1186
-7.000 -0.4118 0.09105 0.08481 -0.0138 1.0000 0.1257
-6.750 -0.4083 0.08933 0.08313 -0.0177 1.0000 0.1310
-6.500 -0.4000 0.08507 0.07894 -0.0180 1.0000 0.1350
-6.250 -0.3915 0.08207 0.07596 -0.0194 1.0000 0.1436
-6.000 -0.3829 0.07856 0.07248 -0.0207 1.0000 0.1485
-5.750 -0.3724 0.07710 0.07095 -0.0244 1.0000 0.1591
-5.500 -0.3633 0.07240 0.06630 -0.0224 1.0000 0.1707
-5.250 -0.3537 0.06915 0.06307 -0.0227 1.0000 0.1840
-5.000 -0.3427 0.06706 0.06093 -0.0247 1.0000 0.2004
-4.750 -0.3348 0.06285 0.05683 -0.0228 1.0000 0.2159
-4.500 -0.3262 0.05951 0.05355 -0.0213 1.0000 0.2341
-4.250 -0.3184 0.05668 0.05075 -0.0205 1.0000 0.2581
-4.000 -0.3133 0.05371 0.04787 -0.0183 1.0000 0.2870
-3.750 -0.3123 0.05103 0.04529 -0.0154 1.0000 0.3261
-3.500 -0.3159 0.04822 0.04263 -0.0107 1.0000 0.3687
-3.250 -0.3219 0.04556 0.04013 -0.0056 1.0000 0.4127
-3.000 -0.3270 0.04303 0.03772 -0.0010 1.0000 0.4523
-2.750 -0.3276 0.04093 0.03564 0.0020 1.0000 0.4880
-2.500 -0.3271 0.03838 0.03320 0.0057 1.0000 0.5182
-2.250 -0.3245 0.03610 0.03099 0.0090 1.0000 0.5521
-2.000 -0.3151 0.03395 0.02878 0.0103 1.0000 0.5770
-1.750 -0.2889 0.03211 0.02671 0.0068 0.9997 0.5839
-1.500 -0.1037 0.03419 0.02600 -0.0278 0.9799 0.2249
-1.250 -0.0427 0.03212 0.02306 -0.0331 0.9658 0.1849
-1.000 0.0109 0.03000 0.02033 -0.0373 0.9525 0.1671
-0.750 0.0643 0.02840 0.01800 -0.0414 0.9395 0.1606
-0.500 0.1181 0.02699 0.01630 -0.0462 0.9273 0.1777
-0.250 0.1769 0.02583 0.01472 -0.0512 0.9155 0.1878
0.000 0.2246 0.02481 0.01364 -0.0547 0.9036 0.2114
0.250 0.2611 0.02360 0.01287 -0.0565 0.8916 0.2956
0.500 0.3673 0.02145 0.01141 -0.0704 0.8851 1.0000
0.750 0.4036 0.02184 0.01156 -0.0723 0.8723 1.0000
1.000 0.4342 0.02234 0.01190 -0.0732 0.8597 1.0000
1.250 0.4598 0.02295 0.01240 -0.0733 0.8474 1.0000
1.500 0.4830 0.02365 0.01301 -0.0730 0.8358 1.0000
1.750 0.5063 0.02437 0.01367 -0.0728 0.8252 1.0000
2.000 0.5342 0.02499 0.01426 -0.0732 0.8162 1.0000
2.250 0.5544 0.02585 0.01511 -0.0725 0.8064 1.0000
2.750 0.5992 0.02756 0.01693 -0.0719 0.7898 1.0000
3.000 0.6108 0.02884 0.01825 -0.0704 0.7808 1.0000
3.250 0.6297 0.02994 0.01942 -0.0699 0.7733 1.0000
3.500 0.6465 0.03115 0.02072 -0.0691 0.7659 1.0000
3.750 0.6601 0.03255 0.02221 -0.0681 0.7588 1.0000
4.000 0.6765 0.03388 0.02374 -0.0674 0.7520 1.0000
4.250 0.6877 0.03547 0.02546 -0.0663 0.7455 1.0000
4.500 0.6985 0.03710 0.02721 -0.0653 0.7391 1.0000
4.750 0.7147 0.03865 0.02894 -0.0647 0.7335 1.0000
5.000 0.7138 0.04075 0.03113 -0.0627 0.7273 1.0000
5.250 0.7395 0.04213 0.03281 -0.0632 0.7220 1.0000
5.500 0.8501 0.02313 0.01422 -0.0376 0.5218 1.0000
5.750 0.8437 0.02262 0.01226 -0.0284 0.2216 1.0000
6.000 0.8431 0.02634 0.01484 -0.0257 0.1369 1.0000
6.250 0.8516 0.02856 0.01701 -0.0231 0.1183 1.0000
6.500 0.8616 0.03052 0.01896 -0.0204 0.1099 1.0000
6.750 0.8778 0.03233 0.02081 -0.0178 0.1030 1.0000
7.000 0.9048 0.03436 0.02283 -0.0162 0.0939 1.0000
7.250 0.9453 0.03739 0.02577 -0.0160 0.0880 1.0000
7.500 0.9813 0.04061 0.02921 -0.0155 0.0881 1.0000
7.750 1.0066 0.04334 0.03260 -0.0138 0.0907 1.0000
8.000 1.0283 0.04683 0.03668 -0.0121 0.0942 1.0000
8.250 1.0460 0.05064 0.04095 -0.0105 0.0959 1.0000
8.500 1.0589 0.05465 0.04540 -0.0088 0.0974 1.0000
8.750 1.0744 0.05916 0.05023 -0.0076 0.1008 1.0000
9.000 1.0679 0.06270 0.05467 -0.0048 0.1083 1.0000
9.250 1.0674 0.06720 0.05966 -0.0033 0.1164 1.0000
9.500 1.0693 0.07284 0.06562 -0.0026 0.1270 1.0000
9.750 1.0390 0.07674 0.06992 -0.0016 0.1292 1.0000
10.000 1.0101 0.08107 0.07440 -0.0012 0.1306 1.0000
10.250 0.9798 0.08612 0.07951 -0.0028 0.1319 1.0000
10.500 0.9652 0.09288 0.08634 -0.0058 0.1406 1.0000
10.750 0.9403 0.10211 0.09556 -0.0118 0.1528 1.0000
11.000 0.8873 0.11541 0.10867 -0.0251 0.1683 1.0000
11.250 0.8591 0.12684 0.11994 -0.0343 0.2018 1.0000
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Polar data table (+)
Polar graphs
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