GOE 494 AIRFOIL (goe494-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 494 AIRFOIL (goe494-il) Reynolds number: 100,000 Max Cl/Cd: 69.52 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe494-il-100000.txt Download as CSV file: xf-goe494-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 494 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3513 0.09905 0.09429 -0.0281 1.0000 0.0577
-7.250 -0.3634 0.09861 0.09396 -0.0264 1.0000 0.0584
-7.000 -0.3712 0.09816 0.09366 -0.0278 1.0000 0.0590
-6.750 -0.3725 0.09715 0.09272 -0.0311 1.0000 0.0594
-6.500 -0.3691 0.09489 0.09053 -0.0347 1.0000 0.0597
-6.250 -0.3712 0.08888 0.08450 -0.0224 1.0000 0.0630
-6.000 -0.3708 0.08674 0.08241 -0.0212 1.0000 0.0662
-5.750 -0.3697 0.08473 0.08045 -0.0222 1.0000 0.0696
-5.500 -0.3467 0.08341 0.07910 -0.0376 1.0000 0.0730
-5.250 -0.3501 0.07914 0.07491 -0.0335 1.0000 0.0741
-5.000 -0.3529 0.07642 0.07224 -0.0281 1.0000 0.0762
-4.750 -0.3464 0.07390 0.06973 -0.0277 1.0000 0.0799
-4.500 -0.3030 0.06938 0.06507 -0.0444 1.0000 0.0876
-4.250 -0.3073 0.06679 0.06255 -0.0383 1.0000 0.0897
-4.000 -0.2937 0.06414 0.05988 -0.0390 1.0000 0.0961
-3.750 -0.2289 0.05924 0.05462 -0.0581 1.0000 0.1150
-3.500 -0.2376 0.05680 0.05234 -0.0504 1.0000 0.1179
-3.250 -0.2097 0.05361 0.04907 -0.0546 1.0000 0.1318
-3.000 -0.1804 0.05056 0.04591 -0.0586 1.0000 0.1459
-2.750 -0.1535 0.04787 0.04315 -0.0613 1.0000 0.1613
-2.500 -0.1133 0.04498 0.04009 -0.0672 0.9986 0.1872
-2.250 -0.0710 0.04302 0.03797 -0.0721 0.9946 0.2254
-2.000 -0.0324 0.04042 0.03528 -0.0761 0.9904 0.2567
-1.750 0.0892 0.02829 0.02107 -0.0981 0.9931 0.1111
-1.500 0.1343 0.02592 0.01804 -0.1017 0.9897 0.1051
-1.250 0.1773 0.02449 0.01601 -0.1044 0.9859 0.0978
-1.000 0.2186 0.02344 0.01463 -0.1070 0.9826 0.0950
-0.750 0.2526 0.02273 0.01368 -0.1083 0.9772 0.0945
-0.500 0.2902 0.02224 0.01308 -0.1102 0.9727 0.0962
-0.250 0.3269 0.02198 0.01276 -0.1121 0.9683 0.1017
0.000 0.3585 0.02170 0.01258 -0.1133 0.9622 0.1117
0.250 0.3982 0.02157 0.01245 -0.1158 0.9578 0.1226
0.500 0.4337 0.02121 0.01255 -0.1177 0.9524 0.2299
0.750 0.4657 0.01985 0.01279 -0.1186 0.9472 1.0000
1.000 0.5053 0.02030 0.01299 -0.1211 0.9422 1.0000
1.250 0.5322 0.02070 0.01327 -0.1214 0.9339 1.0000
1.500 0.5737 0.02110 0.01357 -0.1242 0.9291 1.0000
1.750 0.5979 0.02153 0.01396 -0.1240 0.9200 1.0000
2.000 0.6379 0.02189 0.01430 -0.1266 0.9146 1.0000
2.250 0.6639 0.02232 0.01477 -0.1266 0.9053 1.0000
2.500 0.6972 0.02270 0.01520 -0.1279 0.8978 1.0000
2.750 0.7352 0.02289 0.01546 -0.1298 0.8896 1.0000
3.000 0.7743 0.02279 0.01547 -0.1314 0.8773 1.0000
3.250 0.8265 0.02197 0.01488 -0.1343 0.8632 1.0000
3.500 0.8756 0.02112 0.01425 -0.1366 0.8502 1.0000
3.750 0.9461 0.01754 0.01098 -0.1383 0.8197 1.0000
4.000 0.9840 0.01547 0.00902 -0.1356 0.7770 1.0000
4.250 1.0081 0.01450 0.00797 -0.1313 0.7023 1.0000
4.500 1.0090 0.01568 0.00743 -0.1234 0.3839 1.0000
4.750 1.0058 0.01942 0.00912 -0.1187 0.0997 1.0000
5.000 1.0220 0.02104 0.01051 -0.1164 0.0740 1.0000
5.250 1.0397 0.02240 0.01199 -0.1143 0.0652 1.0000
5.500 1.0542 0.02437 0.01393 -0.1119 0.0609 1.0000
5.750 1.0758 0.02608 0.01569 -0.1102 0.0587 1.0000
6.000 1.1008 0.02789 0.01754 -0.1092 0.0541 1.0000
6.250 1.1294 0.03021 0.01989 -0.1088 0.0515 1.0000
6.500 1.1609 0.03287 0.02274 -0.1083 0.0517 1.0000
6.750 1.1909 0.03590 0.02629 -0.1073 0.0540 1.0000
7.000 1.2179 0.03974 0.03059 -0.1059 0.0576 1.0000
7.250 1.2400 0.04375 0.03500 -0.1044 0.0590 1.0000
10.500 0.9372 0.13192 0.12813 -0.0989 0.1730 1.0000
10.750 0.9407 0.13632 0.13256 -0.0990 0.1679 1.0000
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Polar data table (+)
Polar graphs
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