GOE 458 AIRFOIL (goe458-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 458 AIRFOIL (goe458-il) Reynolds number: 200,000 Max Cl/Cd: 87.47 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe458-il-200000.txt Download as CSV file: xf-goe458-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 458 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3326 0.09597 0.09290 -0.0261 1.0000 0.0306
-7.250 -0.3510 0.09574 0.09276 -0.0230 1.0000 0.0316
-7.000 -0.3672 0.09502 0.09211 -0.0197 1.0000 0.0316
-6.750 -0.3413 0.09136 0.08846 -0.0327 0.9938 0.0328
-6.500 -0.3106 0.08652 0.08359 -0.0428 0.9874 0.0331
-6.250 -0.2954 0.07928 0.07636 -0.0473 0.9838 0.0341
-6.000 -0.2792 0.07584 0.07291 -0.0470 0.9797 0.0359
-5.750 -0.2540 0.07194 0.06896 -0.0520 0.9740 0.0381
-5.500 -0.2177 0.06699 0.06395 -0.0614 0.9700 0.0415
-5.250 -0.1609 0.06108 0.05780 -0.0795 0.9610 0.0457
-5.000 -0.1397 0.05479 0.05152 -0.0835 0.9576 0.0477
-4.750 -0.1169 0.05215 0.04886 -0.0848 0.9517 0.0505
-4.500 -0.0600 0.04475 0.04098 -0.0990 0.9461 0.0598
-4.250 -0.0327 0.04213 0.03846 -0.1004 0.9436 0.0629
-4.000 0.0027 0.03769 0.03371 -0.1055 0.9364 0.0742
-3.750 0.0415 0.03439 0.03016 -0.1098 0.9325 0.0870
-3.500 0.0920 0.02249 0.01663 -0.1143 0.9305 0.0351
-3.250 0.1250 0.02061 0.01454 -0.1157 0.9252 0.0392
-3.000 0.1617 0.01827 0.01145 -0.1164 0.9204 0.0348
-2.750 0.2012 0.01666 0.00955 -0.1181 0.9173 0.0343
-2.500 0.2325 0.01520 0.00799 -0.1185 0.9112 0.0361
-2.250 0.2663 0.01428 0.00702 -0.1193 0.9054 0.0420
-2.000 0.3023 0.01332 0.00596 -0.1205 0.9010 0.0520
-1.750 0.3300 0.01257 0.00555 -0.1201 0.8922 0.1790
-1.500 0.3619 0.01250 0.00545 -0.1208 0.8854 0.2235
-1.250 0.3917 0.01235 0.00529 -0.1210 0.8772 0.2530
-1.000 0.4197 0.01215 0.00508 -0.1208 0.8679 0.2742
-0.750 0.4511 0.01178 0.00471 -0.1212 0.8612 0.2937
-0.500 0.4766 0.01151 0.00452 -0.1206 0.8503 0.3219
-0.250 0.5022 0.01108 0.00435 -0.1200 0.8401 0.3916
0.000 0.5471 0.00957 0.00407 -0.1232 0.8340 1.0000
0.250 0.5728 0.00963 0.00398 -0.1225 0.8226 1.0000
0.500 0.5990 0.00969 0.00392 -0.1220 0.8115 1.0000
0.750 0.6256 0.00976 0.00387 -0.1215 0.8011 1.0000
1.000 0.6525 0.00981 0.00380 -0.1211 0.7904 1.0000
1.250 0.6790 0.00984 0.00374 -0.1205 0.7785 1.0000
1.500 0.7049 0.00989 0.00369 -0.1199 0.7659 1.0000
1.750 0.7304 0.00995 0.00369 -0.1192 0.7530 1.0000
2.000 0.7558 0.01003 0.00371 -0.1185 0.7402 1.0000
2.250 0.7812 0.01012 0.00375 -0.1179 0.7275 1.0000
2.500 0.8065 0.01021 0.00382 -0.1172 0.7141 1.0000
2.750 0.8319 0.01032 0.00390 -0.1165 0.7014 1.0000
3.000 0.8575 0.01046 0.00403 -0.1160 0.6900 1.0000
3.250 0.8832 0.01062 0.00418 -0.1154 0.6793 1.0000
3.500 0.9092 0.01079 0.00433 -0.1150 0.6690 1.0000
3.750 0.9345 0.01095 0.00455 -0.1143 0.6567 1.0000
4.000 0.9564 0.01106 0.00460 -0.1128 0.6311 1.0000
4.250 0.9784 0.01122 0.00474 -0.1114 0.6062 1.0000
4.500 0.9989 0.01142 0.00484 -0.1096 0.5728 1.0000
4.750 1.0171 0.01168 0.00499 -0.1075 0.5257 1.0000
5.000 1.0298 0.01228 0.00523 -0.1043 0.4304 1.0000
5.250 1.0248 0.01452 0.00618 -0.0990 0.2309 1.0000
5.500 1.0241 0.01695 0.00748 -0.0948 0.0514 1.0000
5.750 1.0397 0.01804 0.00852 -0.0925 0.0332 1.0000
6.000 1.0583 0.01884 0.00952 -0.0907 0.0304 1.0000
6.250 1.0758 0.01971 0.01057 -0.0888 0.0283 1.0000
6.500 1.0905 0.02074 0.01175 -0.0865 0.0253 1.0000
6.750 1.1017 0.02197 0.01310 -0.0837 0.0243 1.0000
7.000 1.1108 0.02331 0.01457 -0.0807 0.0238 1.0000
7.250 1.1198 0.02473 0.01605 -0.0775 0.0236 1.0000
7.500 1.1331 0.02624 0.01761 -0.0750 0.0239 1.0000
7.750 1.1555 0.02803 0.01947 -0.0738 0.0251 1.0000
8.000 1.1925 0.03062 0.02218 -0.0746 0.0278 1.0000
8.250 1.2227 0.03300 0.02472 -0.0745 0.0271 1.0000
14.250 0.8462 0.16224 0.15951 -0.0815 0.0690 1.0000
14.500 0.8586 0.16372 0.16102 -0.0796 0.0645 1.0000
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Polar data table (+)
Polar graphs
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