GOE 494 AIRFOIL (goe494-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 494 AIRFOIL (goe494-il) Reynolds number: 500,000 Max Cl/Cd: 121.92 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe494-il-500000-n5.txt Download as CSV file: xf-goe494-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3316 0.09708 0.09484 -0.0347 0.9974 0.0054
-8.250 -0.3189 0.09294 0.09071 -0.0384 0.9942 0.0054
-8.000 -0.3059 0.08912 0.08690 -0.0420 0.9905 0.0054
-7.750 -0.2919 0.08466 0.08244 -0.0466 0.9867 0.0055
-7.500 -0.2806 0.08035 0.07816 -0.0507 0.9800 0.0057
-7.250 -0.2645 0.07605 0.07384 -0.0558 0.9741 0.0057
-7.000 -0.2439 0.07317 0.07095 -0.0605 0.9696 0.0062
-6.750 -0.2186 0.06962 0.06739 -0.0667 0.9666 0.0070
-6.500 -0.1950 0.06479 0.06254 -0.0740 0.9595 0.0073
-6.250 -0.1616 0.05852 0.05623 -0.0849 0.9550 0.0075
-6.000 -0.1276 0.05156 0.04921 -0.0966 0.9471 0.0078
-5.750 -0.0768 0.04108 0.03858 -0.1151 0.9407 0.0086
-5.500 -0.0166 0.02557 0.02252 -0.1369 0.9322 0.0098
-5.250 0.0263 0.01420 0.00972 -0.1459 0.9274 0.0141
-5.000 0.0535 0.01500 0.01061 -0.1457 0.9217 0.0150
-4.750 0.0817 0.01522 0.01080 -0.1458 0.9164 0.0168
-4.500 0.1109 0.01444 0.00976 -0.1463 0.9112 0.0204
-4.250 0.1390 0.01407 0.00916 -0.1464 0.9050 0.0226
-3.750 0.1950 0.01248 0.00721 -0.1472 0.8923 0.0261
-3.500 0.2228 0.01216 0.00679 -0.1473 0.8860 0.0281
-3.250 0.2503 0.01168 0.00616 -0.1473 0.8791 0.0296
-3.000 0.2782 0.01112 0.00544 -0.1474 0.8725 0.0303
-2.750 0.3056 0.01060 0.00479 -0.1473 0.8642 0.0306
-2.500 0.3330 0.01024 0.00431 -0.1472 0.8553 0.0314
-2.250 0.3603 0.00981 0.00377 -0.1470 0.8453 0.0314
-2.000 0.3876 0.00938 0.00325 -0.1469 0.8349 0.0310
-1.750 0.4148 0.00903 0.00281 -0.1467 0.8242 0.0306
-1.500 0.4420 0.00874 0.00243 -0.1465 0.8132 0.0303
-1.250 0.4692 0.00851 0.00212 -0.1463 0.8030 0.0300
-1.000 0.4966 0.00830 0.00187 -0.1462 0.7939 0.0298
-0.750 0.5239 0.00814 0.00165 -0.1460 0.7861 0.0296
-0.500 0.5513 0.00802 0.00148 -0.1459 0.7785 0.0295
-0.250 0.5787 0.00792 0.00134 -0.1458 0.7717 0.0294
0.000 0.6061 0.00785 0.00124 -0.1456 0.7651 0.0295
0.250 0.6335 0.00782 0.00116 -0.1455 0.7594 0.0298
0.500 0.6607 0.00780 0.00112 -0.1453 0.7519 0.0303
0.750 0.6876 0.00781 0.00109 -0.1450 0.7433 0.0314
1.000 0.7145 0.00784 0.00109 -0.1447 0.7343 0.0334
1.250 0.7415 0.00779 0.00114 -0.1445 0.7256 0.0713
1.500 0.7679 0.00755 0.00128 -0.1444 0.7122 0.2461
1.750 0.7934 0.00756 0.00141 -0.1439 0.6919 0.3127
2.000 0.8191 0.00755 0.00155 -0.1435 0.6725 0.3889
2.250 0.8446 0.00723 0.00177 -0.1432 0.6545 0.6122
2.750 0.8876 0.00728 0.00201 -0.1404 0.5366 1.0000
3.000 0.9077 0.00801 0.00235 -0.1390 0.4541 1.0000
3.250 0.9216 0.00955 0.00299 -0.1368 0.2698 1.0000
3.500 0.9410 0.01055 0.00350 -0.1356 0.1691 1.0000
3.750 0.9592 0.01172 0.00410 -0.1342 0.0537 1.0000
4.000 0.9826 0.01224 0.00456 -0.1334 0.0315 1.0000
4.250 1.0068 0.01264 0.00496 -0.1327 0.0210 1.0000
4.500 1.0309 0.01307 0.00537 -0.1320 0.0146 1.0000
4.750 1.0541 0.01364 0.00602 -0.1310 0.0115 1.0000
5.000 1.0775 0.01415 0.00662 -0.1302 0.0101 1.0000
5.250 1.1009 0.01462 0.00713 -0.1294 0.0085 1.0000
5.500 1.1210 0.01558 0.00816 -0.1280 0.0071 1.0000
5.750 1.1428 0.01627 0.00893 -0.1269 0.0067 1.0000
6.000 1.1636 0.01712 0.00988 -0.1256 0.0062 1.0000
6.250 1.1836 0.01809 0.01094 -0.1242 0.0057 1.0000
6.500 1.2036 0.01907 0.01205 -0.1228 0.0054 1.0000
6.750 1.2249 0.01978 0.01279 -0.1218 0.0049 1.0000
7.000 1.2432 0.02115 0.01424 -0.1203 0.0044 1.0000
7.250 1.2633 0.02236 0.01561 -0.1190 0.0041 1.0000
7.500 1.2831 0.02401 0.01745 -0.1175 0.0039 1.0000
7.750 1.3031 0.02603 0.01971 -0.1161 0.0036 1.0000
8.000 1.3226 0.02847 0.02244 -0.1146 0.0034 1.0000
8.250 1.3404 0.03136 0.02566 -0.1128 0.0032 1.0000
8.500 1.3546 0.03506 0.02976 -0.1106 0.0031 1.0000
8.750 1.3622 0.04057 0.03580 -0.1072 0.0031 1.0000
9.000 1.3616 0.04707 0.04284 -0.1029 0.0031 1.0000
9.250 1.3561 0.05281 0.04905 -0.0987 0.0032 1.0000
9.500 1.3468 0.05789 0.05448 -0.0946 0.0033 1.0000
9.750 1.3330 0.06231 0.05917 -0.0903 0.0033 1.0000
10.000 1.3144 0.06591 0.06297 -0.0858 0.0034 1.0000
10.250 1.2938 0.06988 0.06709 -0.0823 0.0034 1.0000
10.500 1.2727 0.07434 0.07173 -0.0802 0.0034 1.0000
10.750 1.2509 0.07945 0.07701 -0.0795 0.0034 1.0000
11.000 1.2297 0.08508 0.08280 -0.0803 0.0034 1.0000
11.250 1.2062 0.09199 0.08985 -0.0827 0.0035 1.0000
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Polar data table (+)
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