GOE 494 AIRFOIL (goe494-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
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Airfoil: GOE 494 AIRFOIL (goe494-il) Reynolds number: 1,000,000 Max Cl/Cd: 164.34 at α=2.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe494-il-1000000.txt Download as CSV file: xf-goe494-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3638 0.10843 0.10678 -0.0285 1.0000 0.0082
-9.250 -0.3608 0.10608 0.10444 -0.0282 1.0000 0.0083
-9.000 -0.3594 0.10374 0.10213 -0.0278 1.0000 0.0084
-8.750 -0.3588 0.10186 0.10027 -0.0268 1.0000 0.0087
-8.500 -0.3557 0.09959 0.09801 -0.0269 0.9997 0.0090
-8.250 -0.3404 0.09588 0.09431 -0.0307 0.9986 0.0092
-8.000 -0.3243 0.09228 0.09070 -0.0347 0.9969 0.0097
-7.750 -0.3072 0.08835 0.08677 -0.0393 0.9949 0.0106
-7.500 -0.2896 0.08410 0.08253 -0.0462 0.9901 0.0115
-7.250 -0.2680 0.07943 0.07785 -0.0529 0.9863 0.0116
-7.000 -0.2435 0.07468 0.07309 -0.0599 0.9841 0.0116
-6.750 -0.2233 0.06808 0.06649 -0.0685 0.9795 0.0119
-6.500 -0.2014 0.06447 0.06287 -0.0733 0.9759 0.0123
-6.250 -0.1760 0.06257 0.06095 -0.0767 0.9737 0.0133
-6.000 -0.1417 0.05829 0.05666 -0.0852 0.9716 0.0147
-5.750 -0.0914 0.05224 0.05054 -0.0991 0.9686 0.0164
-5.500 -0.0453 0.02713 0.02545 -0.1013 0.9409 0.0152
-5.250 -0.0164 0.02060 0.01879 -0.1111 0.9321 0.0148
-5.000 0.0396 0.00587 0.00311 -0.1339 0.9298 0.0163
-4.750 0.0777 0.01524 0.01183 -0.1444 0.9408 0.0179
-4.500 0.1040 0.01535 0.01195 -0.1444 0.9345 0.0187
-4.000 0.1598 0.01374 0.01000 -0.1449 0.9221 0.0219
-3.250 0.2420 0.01130 0.00706 -0.1454 0.9000 0.0280
-3.000 0.2692 0.01057 0.00618 -0.1453 0.8914 0.0295
-2.750 0.2966 0.01016 0.00565 -0.1452 0.8831 0.0318
-2.500 0.3241 0.00945 0.00478 -0.1450 0.8743 0.0322
-2.250 0.3514 0.00879 0.00400 -0.1448 0.8642 0.0321
-2.000 0.3786 0.00820 0.00330 -0.1446 0.8541 0.0317
-1.750 0.4058 0.00776 0.00277 -0.1444 0.8440 0.0315
-1.500 0.4330 0.00741 0.00236 -0.1442 0.8334 0.0317
-1.250 0.4603 0.00705 0.00194 -0.1440 0.8226 0.0313
-1.000 0.4876 0.00679 0.00161 -0.1438 0.8123 0.0315
-0.750 0.5149 0.00662 0.00136 -0.1436 0.8029 0.0324
-0.500 0.5422 0.00652 0.00122 -0.1434 0.7936 0.0336
-0.250 0.5693 0.00647 0.00114 -0.1432 0.7839 0.0342
0.000 0.5964 0.00639 0.00099 -0.1430 0.7739 0.0349
0.250 0.6235 0.00635 0.00090 -0.1427 0.7649 0.0355
0.500 0.6508 0.00633 0.00084 -0.1425 0.7568 0.0361
0.750 0.6777 0.00634 0.00081 -0.1423 0.7474 0.0372
1.000 0.7041 0.00639 0.00080 -0.1419 0.7341 0.0388
1.250 0.7304 0.00645 0.00081 -0.1414 0.7168 0.0409
1.500 0.7572 0.00626 0.00088 -0.1413 0.7056 0.1712
1.750 0.7837 0.00599 0.00105 -0.1412 0.6922 0.3729
2.000 0.8100 0.00574 0.00121 -0.1410 0.6780 0.5573
2.250 0.8332 0.00507 0.00134 -0.1400 0.6515 1.0000
2.500 0.8574 0.00534 0.00141 -0.1392 0.5965 1.0000
2.750 0.8775 0.00607 0.00167 -0.1377 0.4968 1.0000
3.000 0.8932 0.00742 0.00218 -0.1358 0.3144 1.0000
3.250 0.9115 0.00857 0.00268 -0.1343 0.1785 1.0000
3.500 0.9297 0.00979 0.00327 -0.1328 0.0436 1.0000
3.750 0.9543 0.01018 0.00363 -0.1321 0.0289 1.0000
4.000 0.9794 0.01052 0.00398 -0.1316 0.0222 1.0000
4.250 1.0041 0.01090 0.00434 -0.1309 0.0180 1.0000
4.500 1.0273 0.01150 0.00502 -0.1299 0.0153 1.0000
4.750 1.0520 0.01185 0.00542 -0.1293 0.0143 1.0000
5.000 1.0766 0.01222 0.00580 -0.1287 0.0128 1.0000
5.250 1.1004 0.01268 0.00626 -0.1279 0.0113 1.0000
5.500 1.1163 0.01430 0.00805 -0.1256 0.0100 1.0000
5.750 1.1400 0.01476 0.00855 -0.1248 0.0097 1.0000
6.000 1.1628 0.01537 0.00921 -0.1239 0.0093 1.0000
6.250 1.1849 0.01610 0.01002 -0.1228 0.0087 1.0000
6.500 1.2064 0.01699 0.01097 -0.1216 0.0081 1.0000
6.750 1.2279 0.01794 0.01198 -0.1205 0.0076 1.0000
7.000 1.2503 0.01860 0.01268 -0.1196 0.0071 1.0000
7.250 1.2711 0.01967 0.01379 -0.1186 0.0066 1.0000
7.500 1.2898 0.02244 0.01676 -0.1170 0.0064 1.0000
7.750 1.3087 0.02640 0.02107 -0.1153 0.0062 1.0000
8.000 1.3278 0.02836 0.02328 -0.1138 0.0061 1.0000
8.250 1.3472 0.02996 0.02509 -0.1124 0.0058 1.0000
8.500 1.3631 0.03306 0.02852 -0.1102 0.0056 1.0000
8.750 1.3683 0.03946 0.03546 -0.1063 0.0054 1.0000
9.000 1.3594 0.04650 0.04303 -0.1014 0.0058 1.0000
10.500 1.3075 0.06761 0.06529 -0.0801 0.0065 1.0000
10.750 1.2873 0.07170 0.06953 -0.0779 0.0065 1.0000
11.000 1.2651 0.07654 0.07452 -0.0770 0.0065 1.0000
11.250 1.2438 0.08199 0.08011 -0.0775 0.0065 1.0000
11.500 1.2235 0.08816 0.08643 -0.0794 0.0065 1.0000
11.750 1.2013 0.09566 0.09407 -0.0830 0.0066 1.0000
12.000 1.1769 0.10538 0.10393 -0.0891 0.0067 1.0000
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Polar data table (+)
Polar graphs
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