GOE 498 AIRFOIL (goe498-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 498 AIRFOIL (goe498-il) Reynolds number: 50,000 Max Cl/Cd: 24.75 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe498-il-50000-n5.txt Download as CSV file: xf-goe498-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 498 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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3091 0.12374 0.11620 -0.0419 1.0000 0.1003
-10.500 -0.3184 0.12116 0.11369 -0.0412 1.0000 0.1002
-10.000 -0.3514 0.11456 0.10723 -0.0408 1.0000 0.0989
-9.750 -0.3504 0.11060 0.10330 -0.0431 0.9968 0.0989
-9.500 -0.3259 0.10832 0.10101 -0.0454 0.9913 0.1009
-9.250 -0.3123 0.10459 0.09727 -0.0492 0.9846 0.1026
-9.000 -0.3047 0.10008 0.09274 -0.0536 0.9775 0.1038
-8.750 -0.3003 0.09500 0.08765 -0.0586 0.9700 0.1045
-8.500 -0.3034 0.08986 0.08251 -0.0628 0.9603 0.1054
-8.250 -0.3161 0.08373 0.07638 -0.0679 0.9497 0.1067
-8.000 -0.3615 0.07034 0.06289 -0.0805 0.9340 0.1078
-7.750 -0.3890 0.05671 0.04871 -0.0954 0.9206 0.1096
-7.500 -0.3715 0.05533 0.04731 -0.0957 0.9114 0.1119
-7.250 -0.3492 0.05100 0.04263 -0.1012 0.9052 0.1157
-7.000 -0.3439 0.04600 0.03693 -0.1045 0.8942 0.1196
-6.750 -0.3129 0.04509 0.03606 -0.1058 0.8885 0.1230
-6.500 -0.2907 0.04343 0.03418 -0.1068 0.8808 0.1273
-6.250 -0.2674 0.04105 0.03133 -0.1086 0.8729 0.1324
-6.000 -0.2338 0.04028 0.03060 -0.1101 0.8679 0.1373
-5.750 -0.2141 0.03898 0.02898 -0.1101 0.8591 0.1430
-5.500 -0.1861 0.03799 0.02790 -0.1109 0.8522 0.1485
-5.000 -0.1332 0.03627 0.02589 -0.1117 0.8382 0.1626
-4.750 -0.1026 0.03559 0.02515 -0.1125 0.8320 0.1713
-4.500 -0.0653 0.03473 0.02424 -0.1143 0.8280 0.1818
-4.250 -0.0507 0.03442 0.02378 -0.1127 0.8176 0.1917
-4.000 -0.0180 0.03394 0.02337 -0.1135 0.8122 0.2045
-3.750 0.0113 0.03357 0.02300 -0.1139 0.8061 0.2187
-3.500 0.0322 0.03346 0.02287 -0.1130 0.7972 0.2329
-3.250 0.0679 0.03309 0.02246 -0.1142 0.7926 0.2513
-3.000 0.0889 0.03312 0.02243 -0.1133 0.7840 0.2671
-2.750 0.1176 0.03297 0.02221 -0.1134 0.7772 0.2848
-2.500 0.1547 0.03269 0.02191 -0.1146 0.7732 0.3059
-2.250 0.1693 0.03308 0.02229 -0.1127 0.7631 0.3230
-2.000 0.2008 0.03296 0.02217 -0.1131 0.7573 0.3450
-1.750 0.2397 0.03259 0.02179 -0.1143 0.7537 0.3660
-1.500 0.2495 0.03303 0.02228 -0.1117 0.7425 0.3767
-1.250 0.2848 0.03271 0.02189 -0.1125 0.7373 0.3946
-1.000 0.3271 0.03224 0.02134 -0.1143 0.7339 0.4142
-0.750 0.3339 0.03287 0.02200 -0.1113 0.7218 0.4252
-0.500 0.3714 0.03253 0.02163 -0.1123 0.7169 0.4440
-0.250 0.4013 0.03247 0.02154 -0.1123 0.7104 0.4617
0.000 0.4188 0.03282 0.02187 -0.1108 0.7003 0.4784
0.250 0.4587 0.03241 0.02145 -0.1120 0.6957 0.5007
0.500 0.4719 0.03293 0.02200 -0.1098 0.6855 0.5178
0.750 0.5016 0.03285 0.02193 -0.1096 0.6784 0.5413
1.000 0.5430 0.03233 0.02144 -0.1109 0.6742 0.5684
1.250 0.5466 0.03319 0.02237 -0.1076 0.6621 0.5865
1.500 0.5812 0.03287 0.02209 -0.1080 0.6565 0.6142
1.750 0.6243 0.03222 0.02149 -0.1095 0.6529 0.6465
2.000 0.6199 0.03334 0.02274 -0.1051 0.6396 0.6682
2.250 0.6563 0.03277 0.02230 -0.1056 0.6351 0.7102
2.500 0.6597 0.03351 0.02326 -0.1021 0.6243 0.7541
2.750 0.6897 0.03299 0.02301 -0.1017 0.6176 1.0000
3.000 0.7374 0.03262 0.02242 -0.1044 0.6138 1.0000
3.250 0.7331 0.03429 0.02404 -0.1009 0.6009 1.0000
3.500 0.7739 0.03404 0.02363 -0.1023 0.5962 1.0000
4.000 0.8085 0.03560 0.02505 -0.0999 0.5790 1.0000
4.250 0.8527 0.03516 0.02449 -0.1016 0.5754 1.0000
4.500 0.8407 0.03740 0.02675 -0.0974 0.5623 1.0000
4.750 0.8806 0.03703 0.02630 -0.0983 0.5581 1.0000
5.250 0.9086 0.03897 0.02820 -0.0952 0.5406 1.0000
5.500 0.9498 0.03842 0.02759 -0.0962 0.5362 1.0000
5.750 0.9361 0.04098 0.03020 -0.0923 0.5232 1.0000
6.000 0.9844 0.03978 0.02893 -0.0935 0.5190 1.0000
6.250 0.9653 0.04283 0.03204 -0.0894 0.5056 1.0000
6.500 1.0108 0.04161 0.03076 -0.0901 0.5008 1.0000
6.750 0.9947 0.04464 0.03385 -0.0867 0.4879 1.0000
7.000 1.0373 0.04341 0.03258 -0.0870 0.4824 1.0000
7.250 1.0243 0.04632 0.03555 -0.0840 0.4699 1.0000
7.500 1.0625 0.04531 0.03451 -0.0838 0.4640 1.0000
7.750 1.0512 0.04823 0.03750 -0.0812 0.4519 1.0000
8.000 1.0838 0.04765 0.03691 -0.0808 0.4458 1.0000
8.250 1.0727 0.05086 0.04020 -0.0786 0.4347 1.0000
8.500 1.0964 0.05105 0.04042 -0.0778 0.4282 1.0000
8.750 1.1420 0.04944 0.03880 -0.0779 0.4247 1.0000
9.000 1.1064 0.05498 0.04448 -0.0752 0.4108 1.0000
9.250 1.1511 0.05316 0.04265 -0.0749 0.4071 1.0000
9.500 1.1180 0.05890 0.04852 -0.0730 0.3931 1.0000
9.750 1.1631 0.05674 0.04635 -0.0724 0.3893 1.0000
10.000 1.1314 0.06267 0.05241 -0.0711 0.3751 1.0000
10.250 1.1765 0.06032 0.05007 -0.0701 0.3715 1.0000
10.500 1.1441 0.06666 0.05654 -0.0693 0.3570 1.0000
10.750 1.1880 0.06428 0.05416 -0.0682 0.3535 1.0000
11.000 1.1522 0.07147 0.06148 -0.0680 0.3389 1.0000
11.250 1.1934 0.06928 0.05932 -0.0667 0.3355 1.0000
11.500 1.1534 0.07751 0.06768 -0.0671 0.3207 1.0000
11.750 1.1934 0.07525 0.06544 -0.0657 0.3175 1.0000
12.250 1.1190 0.09291 0.08330 -0.0686 0.2906 1.0000
12.500 1.1272 0.09527 0.08573 -0.0684 0.2847 1.0000
12.750 1.1603 0.09348 0.08398 -0.0668 0.2821 1.0000
13.250 1.1096 0.10935 0.10000 -0.0711 0.2610 1.0000
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Polar data table (+)
Polar graphs
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