GOE 493 AIRFOIL (goe493-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 493 AIRFOIL (goe493-il) Reynolds number: 50,000 Max Cl/Cd: 24.25 at α=11° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe493-il-50000.txt Download as CSV file: xf-goe493-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 493 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3847 0.11344 0.10662 -0.0246 1.0000 0.3413
-9.000 -0.3653 0.10923 0.10237 -0.0229 1.0000 0.3532
-8.750 -0.4014 0.10919 0.10249 -0.0202 1.0000 0.3578
-8.500 -0.6697 0.07418 0.06789 -0.0452 1.0000 0.1517
-8.250 -0.6807 0.07023 0.06390 -0.0435 1.0000 0.1526
-8.000 -0.6902 0.06639 0.05997 -0.0420 1.0000 0.1539
-7.750 -0.6972 0.06270 0.05615 -0.0405 1.0000 0.1561
-7.500 -0.7044 0.05861 0.05181 -0.0393 1.0000 0.1591
-7.250 -0.7114 0.05384 0.04656 -0.0386 1.0000 0.1629
-7.000 -0.7118 0.04939 0.04153 -0.0377 1.0000 0.1680
-6.750 -0.6993 0.04780 0.03991 -0.0361 1.0000 0.1781
-6.500 -0.6883 0.04551 0.03746 -0.0348 1.0000 0.1882
-6.250 -0.6775 0.04292 0.03444 -0.0338 1.0000 0.2002
-6.000 -0.6639 0.04105 0.03225 -0.0326 1.0000 0.2142
-5.750 -0.6488 0.03963 0.03063 -0.0313 1.0000 0.2290
-5.500 -0.6330 0.03841 0.02932 -0.0300 1.0000 0.2446
-5.250 -0.6168 0.03734 0.02815 -0.0287 1.0000 0.2608
-5.000 -0.6002 0.03637 0.02708 -0.0275 1.0000 0.2770
-4.750 -0.5832 0.03552 0.02613 -0.0264 1.0000 0.2933
-4.500 -0.5659 0.03478 0.02537 -0.0252 1.0000 0.3101
-4.250 -0.5486 0.03415 0.02473 -0.0240 1.0000 0.3274
-4.000 -0.5313 0.03366 0.02428 -0.0227 1.0000 0.3460
-3.750 -0.5139 0.03321 0.02385 -0.0214 1.0000 0.3661
-3.500 -0.4961 0.03277 0.02329 -0.0203 1.0000 0.3907
-3.250 -0.4796 0.03258 0.02327 -0.0187 1.0000 0.4155
-3.000 -0.4624 0.03238 0.02314 -0.0173 1.0000 0.4457
-2.750 -0.4459 0.03231 0.02317 -0.0156 1.0000 0.4803
-2.500 -0.4306 0.03227 0.02320 -0.0136 1.0000 0.5193
-2.250 -0.4166 0.03228 0.02333 -0.0113 1.0000 0.5598
-2.000 -0.4033 0.03231 0.02348 -0.0086 1.0000 0.6013
-1.750 -0.3899 0.03240 0.02365 -0.0060 1.0000 0.6434
-1.500 -0.3772 0.03253 0.02387 -0.0031 1.0000 0.6843
-1.250 -0.3650 0.03266 0.02404 -0.0002 1.0000 0.7266
-1.000 -0.3536 0.03275 0.02421 0.0030 1.0000 0.7695
-0.750 -0.3415 0.03278 0.02433 0.0060 1.0000 0.8172
-0.500 -0.3204 0.03289 0.02458 0.0072 1.0000 0.8779
-0.250 -0.2390 0.03425 0.02596 -0.0049 1.0000 0.9669
0.000 -0.2134 0.03411 0.02555 -0.0095 1.0000 1.0000
0.250 -0.1973 0.03421 0.02536 -0.0109 1.0000 1.0000
0.500 -0.1779 0.03474 0.02561 -0.0122 1.0000 1.0000
0.750 -0.1585 0.03542 0.02605 -0.0131 1.0000 1.0000
1.000 -0.1397 0.03619 0.02660 -0.0137 1.0000 1.0000
1.250 -0.1214 0.03703 0.02725 -0.0141 1.0000 1.0000
1.500 -0.1034 0.03793 0.02798 -0.0145 1.0000 1.0000
1.750 -0.0858 0.03887 0.02878 -0.0147 1.0000 1.0000
2.000 -0.0685 0.03987 0.02964 -0.0149 1.0000 1.0000
2.250 -0.0509 0.04094 0.03061 -0.0153 0.9997 1.0000
2.500 -0.0065 0.04371 0.03324 -0.0207 0.9862 1.0000
2.750 0.1658 0.04807 0.03736 -0.0438 0.8573 1.0000
3.000 0.1982 0.04929 0.03850 -0.0456 0.8434 1.0000
3.250 0.2322 0.05050 0.03965 -0.0475 0.8292 1.0000
3.500 0.2519 0.05151 0.04064 -0.0475 0.8172 1.0000
3.750 0.2723 0.05259 0.04169 -0.0476 0.8042 1.0000
4.000 0.2961 0.05378 0.04286 -0.0481 0.7914 1.0000
4.250 0.3240 0.05502 0.04409 -0.0492 0.7789 1.0000
4.500 0.3616 0.05632 0.04539 -0.0513 0.7668 1.0000
4.750 0.3678 0.05756 0.04665 -0.0498 0.7554 1.0000
5.000 0.3848 0.05895 0.04806 -0.0497 0.7441 1.0000
5.250 0.4131 0.06032 0.04945 -0.0507 0.7328 1.0000
5.500 0.4296 0.06182 0.05098 -0.0506 0.7229 1.0000
5.750 0.4402 0.06350 0.05269 -0.0500 0.7134 1.0000
6.000 0.4760 0.06492 0.05417 -0.0516 0.7034 1.0000
6.250 0.4695 0.06700 0.05628 -0.0498 0.6964 1.0000
6.500 0.5054 0.06861 0.05797 -0.0515 0.6878 1.0000
6.750 0.4956 0.07093 0.06032 -0.0496 0.6827 1.0000
7.000 0.5033 0.07317 0.06263 -0.0494 0.6785 1.0000
7.250 0.5298 0.07517 0.06471 -0.0504 0.6711 1.0000
7.500 0.5289 0.07779 0.06739 -0.0498 0.6699 1.0000
7.750 0.5351 0.08060 0.07027 -0.0500 0.6707 1.0000
8.000 0.5461 0.08357 0.07332 -0.0506 0.6721 1.0000
8.250 0.5635 0.08500 0.07486 -0.0503 0.6557 1.0000
8.500 0.6090 0.08498 0.07498 -0.0506 0.6248 1.0000
8.750 0.5940 0.08751 0.07756 -0.0489 0.6181 1.0000
9.000 0.6428 0.08764 0.07787 -0.0494 0.5917 1.0000
9.250 0.6646 0.08900 0.07938 -0.0491 0.5761 1.0000
9.500 0.6834 0.09041 0.08092 -0.0486 0.5600 1.0000
9.750 0.6992 0.09192 0.08259 -0.0480 0.5436 1.0000
10.000 0.7116 0.09354 0.08436 -0.0472 0.5262 1.0000
10.250 0.7256 0.09487 0.08584 -0.0462 0.5061 1.0000
10.500 0.7704 0.09296 0.08420 -0.0443 0.4779 1.0000
10.750 0.8244 0.08856 0.08013 -0.0412 0.4466 1.0000
11.000 1.0825 0.04464 0.03631 -0.0216 0.2912 1.0000
11.250 1.0656 0.04759 0.03863 -0.0178 0.2374 1.0000
11.500 1.0603 0.05029 0.04075 -0.0152 0.2040 1.0000
11.750 1.0688 0.05246 0.04258 -0.0133 0.1796 1.0000
12.000 1.1063 0.05363 0.04348 -0.0124 0.1582 1.0000
12.250 1.1585 0.05511 0.04490 -0.0129 0.1424 1.0000
12.500 1.2161 0.05759 0.04736 -0.0147 0.1313 1.0000
12.750 1.2249 0.06051 0.05069 -0.0133 0.1273 1.0000
13.000 1.2781 0.06421 0.05428 -0.0158 0.1192 1.0000
13.250 1.2681 0.06736 0.05783 -0.0130 0.1183 1.0000
13.500 1.2567 0.07087 0.06170 -0.0106 0.1176 1.0000
13.750 1.2408 0.07469 0.06586 -0.0084 0.1171 1.0000
14.000 1.2211 0.07889 0.07038 -0.0067 0.1170 1.0000
14.250 1.1978 0.08356 0.07533 -0.0055 0.1170 1.0000
14.500 1.1713 0.08882 0.08084 -0.0050 0.1174 1.0000
14.750 1.1436 0.09467 0.08691 -0.0054 0.1179 1.0000
15.000 1.1157 0.10123 0.09366 -0.0066 0.1186 1.0000
15.250 1.0897 0.10834 0.10092 -0.0085 0.1193 1.0000
15.500 0.8787 0.15316 0.14574 -0.0372 0.1469 1.0000
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Polar data table (+)
Polar graphs
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