GOE 198 (L.F.G. 5294) AIRFOIL (goe198-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 198 (L.F.G. 5294) AIRFOIL (goe198-il) Reynolds number: 50,000 Max Cl/Cd: 43.21 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe198-il-50000-n5.txt Download as CSV file: xf-goe198-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 198 (L.F.G. 5294) 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3068 0.11465 0.10811 -0.0220 1.0000 0.0762
-7.500 -0.3163 0.11364 0.10719 -0.0198 1.0000 0.0774
-7.250 -0.3246 0.11260 0.10623 -0.0183 1.0000 0.0787
-7.000 -0.3314 0.11170 0.10541 -0.0182 1.0000 0.0800
-6.750 -0.3364 0.11117 0.10494 -0.0197 1.0000 0.0809
-6.250 -0.2928 0.10231 0.09605 -0.0284 0.9878 0.0833
-6.000 -0.2699 0.09815 0.09185 -0.0318 0.9818 0.0855
-5.750 -0.2450 0.09454 0.08821 -0.0369 0.9746 0.0882
-5.500 -0.2169 0.09144 0.08502 -0.0441 0.9667 0.0917
-5.250 -0.1724 0.08876 0.08218 -0.0581 0.9594 0.0946
-5.000 -0.1641 0.08439 0.07788 -0.0552 0.9533 0.0968
-4.750 -0.1397 0.08100 0.07446 -0.0582 0.9475 0.1011
-4.500 -0.0918 0.07921 0.07242 -0.0710 0.9399 0.1081
-4.250 -0.0661 0.07522 0.06842 -0.0745 0.9338 0.1098
-4.000 -0.0417 0.07131 0.06452 -0.0760 0.9296 0.1132
-3.750 -0.0170 0.06881 0.06196 -0.0789 0.9213 0.1185
-3.500 0.0330 0.06592 0.05886 -0.0889 0.9159 0.1260
-3.250 0.0554 0.06291 0.05586 -0.0898 0.9096 0.1314
-3.000 0.0938 0.06043 0.05325 -0.0956 0.9026 0.1437
-2.750 0.1365 0.05767 0.05036 -0.1015 0.8984 0.1595
-2.500 0.1661 0.05579 0.04839 -0.1045 0.8896 0.1747
-2.250 0.2028 0.05315 0.04571 -0.1083 0.8845 0.1926
-1.250 0.3935 0.04363 0.03472 -0.1286 0.8580 0.0928
-1.000 0.4353 0.04156 0.03247 -0.1320 0.8527 0.0903
-0.750 0.4681 0.04010 0.03077 -0.1335 0.8433 0.0860
-0.500 0.5149 0.03841 0.02856 -0.1366 0.8373 0.0808
-0.250 0.5447 0.03725 0.02722 -0.1372 0.8264 0.0798
0.000 0.5881 0.03561 0.02528 -0.1396 0.8201 0.0790
0.500 0.6482 0.03379 0.02295 -0.1396 0.7954 0.0825
0.750 0.6860 0.03244 0.02145 -0.1406 0.7867 0.0853
1.000 0.7147 0.03165 0.02045 -0.1400 0.7740 0.0866
1.250 0.7417 0.03107 0.01965 -0.1391 0.7616 0.0886
1.500 0.7729 0.03035 0.01871 -0.1388 0.7524 0.0919
1.750 0.8012 0.02974 0.01804 -0.1382 0.7420 0.0987
2.000 0.8265 0.02941 0.01764 -0.1373 0.7299 0.1065
2.250 0.8567 0.02876 0.01699 -0.1370 0.7203 0.1160
2.500 0.8854 0.02829 0.01654 -0.1367 0.7093 0.1372
2.750 0.9121 0.02791 0.01643 -0.1363 0.6966 0.1895
3.000 0.9336 0.02641 0.01618 -0.1345 0.6850 1.0000
3.250 0.9643 0.02625 0.01569 -0.1340 0.6747 1.0000
3.500 0.9895 0.02641 0.01571 -0.1331 0.6610 1.0000
3.750 1.0150 0.02657 0.01576 -0.1323 0.6471 1.0000
4.000 1.0411 0.02670 0.01579 -0.1315 0.6333 1.0000
4.250 1.0678 0.02683 0.01583 -0.1308 0.6196 1.0000
4.500 1.0950 0.02695 0.01587 -0.1302 0.6060 1.0000
4.750 1.1226 0.02709 0.01594 -0.1296 0.5923 1.0000
5.000 1.1504 0.02725 0.01601 -0.1290 0.5785 1.0000
5.250 1.1753 0.02762 0.01635 -0.1282 0.5634 1.0000
5.500 1.1999 0.02800 0.01670 -0.1274 0.5473 1.0000
5.750 1.2237 0.02840 0.01703 -0.1263 0.5302 1.0000
6.000 1.2463 0.02884 0.01742 -0.1252 0.5126 1.0000
6.250 1.2675 0.02937 0.01794 -0.1239 0.4954 1.0000
6.500 1.2873 0.03000 0.01858 -0.1225 0.4792 1.0000
6.750 1.3068 0.03071 0.01938 -0.1213 0.4651 1.0000
7.000 1.3271 0.03144 0.02020 -0.1202 0.4531 1.0000
7.250 1.3474 0.03209 0.02094 -0.1190 0.4410 1.0000
7.500 1.3664 0.03271 0.02159 -0.1176 0.4281 1.0000
7.750 1.3829 0.03341 0.02237 -0.1159 0.4144 1.0000
8.000 1.3977 0.03418 0.02324 -0.1140 0.4008 1.0000
8.250 1.4133 0.03499 0.02417 -0.1122 0.3888 1.0000
8.500 1.4299 0.03575 0.02500 -0.1106 0.3780 1.0000
8.750 1.4468 0.03651 0.02584 -0.1090 0.3678 1.0000
9.000 1.4599 0.03751 0.02700 -0.1071 0.3572 1.0000
9.250 1.4731 0.03841 0.02801 -0.1051 0.3462 1.0000
9.500 1.4845 0.03935 0.02905 -0.1028 0.3353 1.0000
9.750 1.4901 0.04062 0.03049 -0.1000 0.3235 1.0000
10.000 1.4936 0.04197 0.03195 -0.0972 0.3098 1.0000
10.250 1.4957 0.04349 0.03357 -0.0944 0.2958 1.0000
10.500 1.4975 0.04516 0.03537 -0.0918 0.2823 1.0000
10.750 1.4965 0.04715 0.03761 -0.0894 0.2679 1.0000
11.000 1.4934 0.04945 0.04012 -0.0871 0.2518 1.0000
11.250 1.4886 0.05213 0.04304 -0.0852 0.2333 1.0000
11.500 1.4831 0.05503 0.04610 -0.0835 0.2124 1.0000
11.750 1.4763 0.05813 0.04919 -0.0818 0.1918 1.0000
12.000 1.4681 0.06159 0.05260 -0.0805 0.1736 1.0000
12.250 1.4589 0.06538 0.05632 -0.0794 0.1595 1.0000
12.500 1.4496 0.06937 0.06024 -0.0785 0.1488 1.0000
12.750 1.4417 0.07339 0.06432 -0.0779 0.1396 1.0000
13.000 1.4344 0.07742 0.06836 -0.0774 0.1325 1.0000
13.250 1.4285 0.08144 0.07249 -0.0771 0.1258 1.0000
13.500 1.4226 0.08543 0.07646 -0.0770 0.1205 1.0000
13.750 1.4186 0.08942 0.08062 -0.0770 0.1145 1.0000
14.000 1.4130 0.09352 0.08471 -0.0773 0.1091 1.0000
14.250 1.4072 0.09797 0.08930 -0.0779 0.1031 1.0000
14.500 1.4003 0.10248 0.09382 -0.0788 0.0972 1.0000
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Polar data table (+)
Polar graphs
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