GOE 591 AIRFOIL (goe591-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 591 AIRFOIL (goe591-il) Reynolds number: 1,000,000 Max Cl/Cd: 122.71 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe591-il-1000000-n5.txt Download as CSV file: xf-goe591-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 591 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
------ -------- --------- --------- -------- -------- --------
-14.500 -0.3538 0.15205 0.15027 -0.0310 1.0000 0.0046
-14.250 -0.3480 0.14929 0.14752 -0.0319 1.0000 0.0048
-12.750 -0.7735 0.03006 0.02754 -0.1105 0.9777 0.0074
-12.500 -0.7577 0.02530 0.02241 -0.1141 0.9747 0.0076
-12.250 -0.7396 0.02314 0.02003 -0.1147 0.9686 0.0078
-12.000 -0.7146 0.02138 0.01806 -0.1161 0.9647 0.0081
-11.750 -0.6897 0.02002 0.01653 -0.1168 0.9598 0.0083
-11.500 -0.6654 0.01887 0.01521 -0.1172 0.9531 0.0085
-11.250 -0.6400 0.01768 0.01388 -0.1177 0.9468 0.0091
-11.000 -0.6161 0.01683 0.01291 -0.1176 0.9380 0.0094
-10.750 -0.5911 0.01607 0.01203 -0.1175 0.9291 0.0100
-10.500 -0.5662 0.01541 0.01124 -0.1173 0.9184 0.0106
-10.250 -0.5421 0.01483 0.01051 -0.1169 0.9054 0.0111
-10.000 -0.5176 0.01431 0.00990 -0.1164 0.8915 0.0118
-9.750 -0.4927 0.01397 0.00947 -0.1159 0.8770 0.0126
-9.500 -0.4680 0.01364 0.00904 -0.1154 0.8634 0.0134
-9.250 -0.4435 0.01329 0.00856 -0.1148 0.8507 0.0141
-9.000 -0.4189 0.01295 0.00811 -0.1142 0.8391 0.0147
-8.750 -0.3933 0.01281 0.00790 -0.1138 0.8286 0.0154
-8.500 -0.3672 0.01267 0.00772 -0.1134 0.8188 0.0161
-8.250 -0.3411 0.01254 0.00753 -0.1130 0.8099 0.0168
-8.000 -0.3152 0.01237 0.00727 -0.1126 0.8005 0.0176
-7.750 -0.2891 0.01220 0.00702 -0.1122 0.7917 0.0182
-7.250 -0.2378 0.01165 0.00630 -0.1113 0.7749 0.0192
-6.750 -0.1846 0.01140 0.00598 -0.1107 0.7603 0.0204
-6.500 -0.1582 0.01127 0.00579 -0.1104 0.7527 0.0210
-6.250 -0.1315 0.01108 0.00554 -0.1101 0.7456 0.0217
-6.000 -0.1052 0.01091 0.00529 -0.1098 0.7378 0.0223
-5.750 -0.0785 0.01071 0.00503 -0.1095 0.7307 0.0229
-5.500 -0.0521 0.01054 0.00478 -0.1091 0.7225 0.0233
-5.250 -0.0253 0.01041 0.00459 -0.1088 0.7146 0.0236
-5.000 0.0012 0.01027 0.00437 -0.1085 0.7061 0.0238
-4.750 0.0267 0.00983 0.00385 -0.1080 0.6979 0.0244
-4.500 0.0522 0.00951 0.00345 -0.1075 0.6888 0.0252
-4.250 0.0784 0.00928 0.00316 -0.1071 0.6794 0.0257
-4.000 0.1047 0.00910 0.00292 -0.1067 0.6704 0.0261
-3.750 0.1310 0.00896 0.00272 -0.1064 0.6609 0.0266
-3.500 0.1576 0.00882 0.00253 -0.1060 0.6509 0.0272
-3.250 0.1840 0.00872 0.00236 -0.1057 0.6406 0.0278
-3.000 0.2104 0.00863 0.00221 -0.1053 0.6302 0.0285
-2.750 0.2371 0.00854 0.00207 -0.1050 0.6203 0.0290
-2.500 0.2636 0.00847 0.00194 -0.1046 0.6102 0.0296
-2.250 0.2900 0.00843 0.00183 -0.1042 0.5991 0.0299
-2.000 0.3166 0.00838 0.00173 -0.1039 0.5878 0.0303
-1.750 0.3432 0.00835 0.00165 -0.1036 0.5776 0.0307
-1.500 0.3697 0.00834 0.00158 -0.1032 0.5671 0.0310
-1.250 0.3961 0.00832 0.00151 -0.1029 0.5560 0.0320
-1.000 0.4227 0.00830 0.00145 -0.1026 0.5457 0.0337
-0.750 0.4490 0.00830 0.00142 -0.1022 0.5357 0.0368
-0.500 0.4753 0.00827 0.00139 -0.1019 0.5252 0.0469
-0.250 0.5015 0.00823 0.00140 -0.1015 0.5152 0.0716
0.000 0.5276 0.00826 0.00141 -0.1012 0.5042 0.0811
0.250 0.5535 0.00832 0.00142 -0.1008 0.4908 0.0871
0.500 0.5791 0.00837 0.00145 -0.1003 0.4767 0.0992
0.750 0.6049 0.00837 0.00148 -0.0999 0.4653 0.1291
1.000 0.6307 0.00836 0.00153 -0.0996 0.4555 0.1680
1.250 0.6564 0.00840 0.00159 -0.0992 0.4460 0.1953
1.500 0.6823 0.00839 0.00165 -0.0988 0.4370 0.2290
1.750 0.7069 0.00826 0.00173 -0.0983 0.4288 0.3295
2.000 0.7280 0.00773 0.00185 -0.0973 0.4220 0.5950
2.500 0.8176 0.00721 0.00218 -0.1049 0.4049 0.9974
2.750 0.8474 0.00735 0.00227 -0.1054 0.3965 1.0000
3.000 0.8711 0.00746 0.00234 -0.1046 0.3902 1.0000
3.250 0.8947 0.00759 0.00243 -0.1037 0.3838 1.0000
3.500 0.9185 0.00771 0.00252 -0.1029 0.3765 1.0000
3.750 0.9418 0.00785 0.00262 -0.1020 0.3691 1.0000
4.000 0.9657 0.00797 0.00272 -0.1013 0.3619 1.0000
4.250 0.9890 0.00813 0.00285 -0.1004 0.3547 1.0000
4.500 1.0127 0.00828 0.00296 -0.0996 0.3458 1.0000
4.750 1.0358 0.00845 0.00310 -0.0987 0.3365 1.0000
5.000 1.0590 0.00863 0.00325 -0.0979 0.3272 1.0000
5.250 1.0818 0.00883 0.00340 -0.0970 0.3152 1.0000
5.500 1.1033 0.00910 0.00359 -0.0959 0.2988 1.0000
5.750 1.1235 0.00945 0.00383 -0.0945 0.2775 1.0000
6.000 1.1418 0.00990 0.00413 -0.0929 0.2509 1.0000
6.250 1.1617 0.01025 0.00439 -0.0915 0.2326 1.0000
6.500 1.1809 0.01064 0.00468 -0.0901 0.2139 1.0000
6.750 1.1989 0.01108 0.00501 -0.0884 0.1942 1.0000
7.000 1.2163 0.01153 0.00536 -0.0867 0.1724 1.0000
7.250 1.2304 0.01213 0.00579 -0.0844 0.1441 1.0000
7.500 1.2430 0.01268 0.00622 -0.0817 0.1239 1.0000
7.750 1.2572 0.01313 0.00661 -0.0794 0.1118 1.0000
8.000 1.2726 0.01354 0.00699 -0.0773 0.1016 1.0000
8.250 1.2868 0.01402 0.00741 -0.0751 0.0885 1.0000
8.500 1.2881 0.01512 0.00828 -0.0708 0.0512 1.0000
8.750 1.2894 0.01628 0.00928 -0.0667 0.0202 1.0000
9.000 1.3020 0.01690 0.00989 -0.0645 0.0147 1.0000
9.250 1.3164 0.01744 0.01047 -0.0627 0.0125 1.0000
9.500 1.3315 0.01797 0.01103 -0.0610 0.0117 1.0000
9.750 1.3455 0.01856 0.01166 -0.0592 0.0107 1.0000
10.000 1.3578 0.01927 0.01240 -0.0573 0.0096 1.0000
10.250 1.3711 0.01994 0.01311 -0.0556 0.0092 1.0000
10.500 1.3847 0.02062 0.01383 -0.0540 0.0086 1.0000
10.750 1.3971 0.02140 0.01465 -0.0523 0.0081 1.0000
11.000 1.4085 0.02226 0.01555 -0.0507 0.0076 1.0000
11.250 1.4188 0.02324 0.01657 -0.0490 0.0071 1.0000
11.500 1.4276 0.02436 0.01774 -0.0473 0.0067 1.0000
11.750 1.4384 0.02538 0.01881 -0.0459 0.0066 1.0000
12.000 1.4483 0.02650 0.01999 -0.0445 0.0063 1.0000
12.250 1.4570 0.02775 0.02130 -0.0432 0.0061 1.0000
12.500 1.4660 0.02902 0.02263 -0.0419 0.0058 1.0000
12.750 1.4734 0.03047 0.02414 -0.0407 0.0056 1.0000
13.000 1.4810 0.03192 0.02564 -0.0396 0.0053 1.0000
13.250 1.4858 0.03367 0.02744 -0.0384 0.0051 1.0000
13.500 1.4892 0.03562 0.02946 -0.0373 0.0049 1.0000
13.750 1.4921 0.03769 0.03160 -0.0364 0.0048 1.0000
14.000 1.4960 0.03971 0.03371 -0.0356 0.0047 1.0000
14.250 1.4988 0.04193 0.03600 -0.0349 0.0046 1.0000
14.500 1.5027 0.04411 0.03826 -0.0344 0.0045 1.0000
14.750 1.5042 0.04659 0.04083 -0.0339 0.0043 1.0000
15.000 1.5043 0.04931 0.04363 -0.0336 0.0042 1.0000
15.250 1.5041 0.05214 0.04655 -0.0334 0.0042 1.0000
15.500 1.5042 0.05503 0.04952 -0.0334 0.0041 1.0000
15.750 1.5009 0.05839 0.05297 -0.0335 0.0040 1.0000
16.000 1.4985 0.06173 0.05639 -0.0337 0.0039 1.0000
16.250 1.4962 0.06512 0.05987 -0.0340 0.0038 1.0000
16.500 1.4921 0.06885 0.06369 -0.0346 0.0038 1.0000
16.750 1.4864 0.07286 0.06779 -0.0352 0.0037 1.0000
17.000 1.4820 0.07673 0.07174 -0.0360 0.0035 1.0000
17.250 1.4743 0.08120 0.07631 -0.0370 0.0036 1.0000
17.500 1.4670 0.08569 0.08090 -0.0381 0.0035 1.0000
17.750 1.4568 0.09070 0.08601 -0.0395 0.0034 1.0000
18.000 1.4460 0.09592 0.09133 -0.0411 0.0034 1.0000
18.250 1.4368 0.10099 0.09651 -0.0427 0.0034 1.0000
18.500 1.4243 0.10670 0.10233 -0.0448 0.0033 1.0000
18.750 1.4153 0.11190 0.10763 -0.0467 0.0033 1.0000
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