GOE 484 AIRFOIL (goe484-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 484 AIRFOIL (goe484-il) Reynolds number: 200,000 Max Cl/Cd: 93.35 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe484-il-200000.txt Download as CSV file: xf-goe484-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 484 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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3726 0.09934 0.09589 -0.0228 1.0000 0.0403
-7.500 -0.3884 0.09884 0.09546 -0.0204 1.0000 0.0409
-7.250 -0.4061 0.09850 0.09519 -0.0181 1.0000 0.0413
-7.000 -0.4145 0.09729 0.09403 -0.0202 1.0000 0.0416
-6.750 -0.4138 0.09505 0.09181 -0.0241 1.0000 0.0419
-6.500 -0.4037 0.08953 0.08630 -0.0261 0.9981 0.0424
-6.250 -0.3882 0.08576 0.08253 -0.0241 0.9957 0.0435
-6.000 -0.3655 0.08230 0.07905 -0.0269 0.9921 0.0452
-5.750 -0.3402 0.07862 0.07534 -0.0327 0.9876 0.0481
-5.500 -0.2699 0.07158 0.06805 -0.0607 0.9811 0.0526
-5.250 -0.2655 0.06760 0.06414 -0.0570 0.9775 0.0536
-5.000 -0.2462 0.06493 0.06147 -0.0571 0.9742 0.0552
-4.750 -0.2132 0.06159 0.05809 -0.0624 0.9716 0.0582
-4.500 -0.1558 0.05492 0.05110 -0.0795 0.9656 0.0653
-4.250 -0.1386 0.05267 0.04892 -0.0785 0.9619 0.0670
-4.000 -0.1051 0.04996 0.04616 -0.0823 0.9591 0.0704
-3.750 -0.0451 0.04439 0.04020 -0.0950 0.9568 0.0791
-3.500 -0.0280 0.04251 0.03837 -0.0943 0.9503 0.0811
-3.250 0.0096 0.04011 0.03584 -0.0983 0.9470 0.0876
-3.000 0.0538 0.03668 0.03219 -0.1042 0.9448 0.0954
-2.750 0.0975 0.03427 0.02940 -0.1091 0.9415 0.1075
-2.500 0.1215 0.03231 0.02749 -0.1094 0.9353 0.1102
-2.250 0.1647 0.03025 0.02509 -0.1134 0.9322 0.1227
-2.000 0.2180 0.02472 0.01848 -0.1173 0.9309 0.0777
-1.750 0.2599 0.02114 0.01429 -0.1199 0.9296 0.0647
-1.500 0.2868 0.02011 0.01306 -0.1196 0.9229 0.0645
-1.250 0.3235 0.01852 0.01127 -0.1212 0.9192 0.0632
-1.000 0.3639 0.01735 0.00995 -0.1234 0.9167 0.0625
-0.750 0.4065 0.01639 0.00893 -0.1260 0.9148 0.0628
-0.500 0.4321 0.01589 0.00841 -0.1253 0.9065 0.0635
-0.250 0.4721 0.01513 0.00768 -0.1274 0.9034 0.0654
0.000 0.5149 0.01447 0.00712 -0.1301 0.9011 0.0717
0.250 0.5443 0.01413 0.00682 -0.1301 0.8934 0.0789
0.500 0.5824 0.01351 0.00643 -0.1318 0.8888 0.1184
0.750 0.6226 0.01269 0.00612 -0.1341 0.8856 0.2769
1.000 0.6562 0.01120 0.00614 -0.1351 0.8778 1.0000
1.250 0.6936 0.01095 0.00581 -0.1365 0.8722 1.0000
1.500 0.7233 0.01080 0.00559 -0.1363 0.8614 1.0000
1.750 0.7558 0.01053 0.00527 -0.1365 0.8499 1.0000
2.000 0.7862 0.01021 0.00488 -0.1360 0.8333 1.0000
2.250 0.8158 0.00994 0.00452 -0.1354 0.8133 1.0000
2.500 0.8416 0.00984 0.00436 -0.1342 0.7908 1.0000
2.750 0.8677 0.00979 0.00422 -0.1332 0.7666 1.0000
3.000 0.8916 0.00980 0.00416 -0.1318 0.7371 1.0000
3.250 0.9153 0.00988 0.00413 -0.1304 0.7037 1.0000
3.500 0.9391 0.01006 0.00417 -0.1291 0.6683 1.0000
3.750 0.9603 0.01044 0.00427 -0.1272 0.6210 1.0000
4.000 0.9771 0.01105 0.00451 -0.1245 0.5563 1.0000
4.250 0.9825 0.01221 0.00486 -0.1199 0.3919 1.0000
4.500 0.9743 0.01520 0.00614 -0.1141 0.1134 1.0000
4.750 0.9913 0.01624 0.00699 -0.1121 0.0843 1.0000
5.000 1.0103 0.01704 0.00777 -0.1104 0.0766 1.0000
5.250 1.0297 0.01775 0.00854 -0.1088 0.0720 1.0000
5.500 1.0485 0.01850 0.00932 -0.1071 0.0680 1.0000
5.750 1.0654 0.01946 0.01027 -0.1051 0.0651 1.0000
6.000 1.0799 0.02091 0.01171 -0.1028 0.0625 1.0000
6.250 1.1003 0.02177 0.01262 -0.1014 0.0605 1.0000
6.500 1.1213 0.02272 0.01362 -0.1001 0.0580 1.0000
6.750 1.1438 0.02390 0.01482 -0.0991 0.0560 1.0000
7.000 1.1673 0.02515 0.01609 -0.0984 0.0535 1.0000
7.250 1.1990 0.02801 0.01887 -0.0995 0.0502 1.0000
7.500 1.2256 0.02965 0.02068 -0.0990 0.0490 1.0000
7.750 1.2492 0.03092 0.02215 -0.0980 0.0474 1.0000
8.000 1.2722 0.03239 0.02384 -0.0970 0.0452 1.0000
8.250 1.2961 0.03451 0.02618 -0.0962 0.0439 1.0000
8.500 1.3184 0.03702 0.02896 -0.0951 0.0432 1.0000
8.750 1.3388 0.03933 0.03143 -0.0940 0.0418 1.0000
9.000 1.3582 0.04274 0.03490 -0.0935 0.0399 1.0000
9.250 1.3733 0.04631 0.03883 -0.0916 0.0398 1.0000
13.250 1.0747 0.14760 0.14427 -0.0896 0.0603 1.0000
13.500 1.0622 0.15709 0.15372 -0.0966 0.0579 1.0000
13.750 0.9223 0.15482 0.15191 -0.0849 0.0621 1.0000
14.000 0.9025 0.16292 0.15998 -0.0918 0.0617 1.0000
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Polar data table (+)
Polar graphs
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