GOE 447 AIRFOIL (goe447-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 447 AIRFOIL (goe447-il) Reynolds number: 500,000 Max Cl/Cd: 116.17 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe447-il-500000-n5.txt Download as CSV file: xf-goe447-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 447 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
------ -------- --------- --------- -------- -------- --------
-10.000 0.0264 0.09762 0.09401 -0.1057 0.7685 0.0242
-9.750 0.0334 0.09463 0.09099 -0.1071 0.7648 0.0239
-9.500 0.0406 0.09170 0.08803 -0.1086 0.7614 0.0237
-9.250 0.0484 0.08885 0.08519 -0.1102 0.7579 0.0238
-9.000 0.0567 0.08616 0.08249 -0.1117 0.7541 0.0239
-8.750 0.0655 0.08360 0.07992 -0.1132 0.7502 0.0245
-8.500 0.0733 0.08083 0.07712 -0.1148 0.7465 0.0249
-7.000 0.0892 0.02102 0.01588 -0.1767 0.7244 0.0272
-6.750 0.1141 0.01917 0.01374 -0.1777 0.7211 0.0274
-6.500 0.1399 0.01792 0.01224 -0.1782 0.7178 0.0277
-6.250 0.1662 0.01693 0.01104 -0.1785 0.7147 0.0280
-5.750 0.2199 0.01540 0.00915 -0.1790 0.7081 0.0285
-5.500 0.2471 0.01478 0.00838 -0.1792 0.7038 0.0288
-5.250 0.2743 0.01425 0.00769 -0.1793 0.6994 0.0292
-5.000 0.3017 0.01381 0.00709 -0.1793 0.6956 0.0295
-4.750 0.3294 0.01339 0.00657 -0.1795 0.6922 0.0298
-4.500 0.3573 0.01302 0.00612 -0.1796 0.6885 0.0301
-4.250 0.3851 0.01273 0.00573 -0.1796 0.6849 0.0304
-4.000 0.4127 0.01238 0.00530 -0.1797 0.6812 0.0310
-3.750 0.4404 0.01210 0.00497 -0.1798 0.6777 0.0316
-3.500 0.4683 0.01186 0.00471 -0.1799 0.6738 0.0322
-3.250 0.4962 0.01166 0.00446 -0.1799 0.6698 0.0328
-3.000 0.5240 0.01148 0.00423 -0.1800 0.6660 0.0334
-2.500 0.5798 0.01119 0.00384 -0.1801 0.6586 0.0348
-2.250 0.6077 0.01106 0.00368 -0.1801 0.6545 0.0355
-2.000 0.6355 0.01092 0.00352 -0.1801 0.6508 0.0369
-1.750 0.6632 0.01083 0.00340 -0.1801 0.6473 0.0385
-1.250 0.7189 0.01066 0.00326 -0.1803 0.6404 0.0456
-1.000 0.7467 0.01065 0.00330 -0.1803 0.6369 0.0538
-0.750 0.7743 0.01068 0.00332 -0.1803 0.6334 0.0607
-0.500 0.8018 0.01074 0.00335 -0.1802 0.6300 0.0655
-0.250 0.8295 0.01075 0.00336 -0.1803 0.6267 0.0686
0.000 0.8570 0.01076 0.00339 -0.1803 0.6229 0.0715
0.250 0.8843 0.01078 0.00341 -0.1802 0.6188 0.0745
0.500 0.9111 0.01084 0.00343 -0.1801 0.6146 0.0772
0.750 0.9382 0.01080 0.00342 -0.1801 0.6105 0.0806
1.000 0.9651 0.01081 0.00344 -0.1800 0.6055 0.0831
1.250 0.9911 0.01084 0.00346 -0.1797 0.5993 0.0855
1.500 1.0171 0.01089 0.00348 -0.1794 0.5927 0.0873
1.750 1.0429 0.01091 0.00350 -0.1791 0.5853 0.0891
2.000 1.0683 0.01095 0.00353 -0.1787 0.5792 0.0910
2.250 1.0946 0.01098 0.00359 -0.1786 0.5731 0.0934
2.500 1.1197 0.01105 0.00365 -0.1781 0.5665 0.0959
2.750 1.1450 0.01113 0.00373 -0.1777 0.5597 0.0983
3.000 1.1690 0.01124 0.00382 -0.1771 0.5503 0.1009
3.250 1.1926 0.01135 0.00393 -0.1764 0.5396 0.1081
3.500 1.2150 0.01147 0.00408 -0.1755 0.5283 0.1312
3.750 1.2374 0.01150 0.00434 -0.1748 0.5170 0.2635
4.000 1.2594 0.01163 0.00456 -0.1739 0.5054 0.3221
4.250 1.2802 0.01171 0.00483 -0.1728 0.4933 0.4393
4.500 1.2941 0.01114 0.00517 -0.1701 0.4811 1.0000
5.000 1.3272 0.01185 0.00574 -0.1661 0.4569 1.0000
5.250 1.3448 0.01222 0.00605 -0.1644 0.4481 1.0000
5.500 1.3631 0.01259 0.00638 -0.1628 0.4398 1.0000
5.750 1.3810 0.01297 0.00673 -0.1613 0.4329 1.0000
6.000 1.4002 0.01333 0.00707 -0.1599 0.4262 1.0000
6.500 1.4354 0.01419 0.00790 -0.1569 0.4121 1.0000
6.750 1.4513 0.01471 0.00838 -0.1551 0.4042 1.0000
7.000 1.4690 0.01517 0.00884 -0.1537 0.3974 1.0000
7.250 1.4865 0.01564 0.00932 -0.1523 0.3907 1.0000
7.500 1.5025 0.01621 0.00987 -0.1507 0.3854 1.0000
7.750 1.5216 0.01664 0.01034 -0.1496 0.3807 1.0000
8.000 1.5387 0.01718 0.01090 -0.1483 0.3741 1.0000
8.250 1.5526 0.01790 0.01161 -0.1466 0.3656 1.0000
8.500 1.5661 0.01867 0.01236 -0.1448 0.3542 1.0000
8.750 1.5787 0.01952 0.01319 -0.1431 0.3414 1.0000
9.000 1.5886 0.02056 0.01419 -0.1410 0.3260 1.0000
9.250 1.5934 0.02197 0.01551 -0.1384 0.3046 1.0000
9.500 1.5931 0.02380 0.01721 -0.1354 0.2764 1.0000
9.750 1.5879 0.02603 0.01928 -0.1320 0.2467 1.0000
10.000 1.5857 0.02813 0.02126 -0.1290 0.2241 1.0000
10.250 1.5869 0.03005 0.02310 -0.1266 0.2075 1.0000
10.500 1.5904 0.03183 0.02484 -0.1245 0.1956 1.0000
10.750 1.5951 0.03358 0.02657 -0.1226 0.1860 1.0000
11.000 1.6032 0.03508 0.02809 -0.1210 0.1792 1.0000
11.250 1.6095 0.03675 0.02976 -0.1194 0.1727 1.0000
11.500 1.6165 0.03839 0.03142 -0.1179 0.1666 1.0000
11.750 1.6231 0.04010 0.03315 -0.1165 0.1599 1.0000
12.000 1.6279 0.04201 0.03506 -0.1149 0.1538 1.0000
12.250 1.6360 0.04365 0.03674 -0.1137 0.1471 1.0000
12.500 1.6391 0.04576 0.03885 -0.1122 0.1383 1.0000
12.750 1.6385 0.04826 0.04128 -0.1105 0.1189 1.0000
13.000 1.6173 0.05286 0.04564 -0.1077 0.0821 1.0000
13.250 1.6118 0.05602 0.04878 -0.1060 0.0710 1.0000
13.500 1.6074 0.05914 0.05189 -0.1045 0.0570 1.0000
13.750 1.5903 0.06370 0.05632 -0.1025 0.0335 1.0000
14.000 1.5861 0.06698 0.05961 -0.1013 0.0270 1.0000
14.250 1.5856 0.06985 0.06254 -0.1003 0.0238 1.0000
14.500 1.5864 0.07265 0.06539 -0.0995 0.0217 1.0000
14.750 1.5868 0.07551 0.06831 -0.0987 0.0201 1.0000
15.000 1.5874 0.07839 0.07125 -0.0981 0.0189 1.0000
15.250 1.5887 0.08123 0.07417 -0.0975 0.0180 1.0000
15.500 1.5894 0.08413 0.07715 -0.0970 0.0172 1.0000
15.750 1.5884 0.08728 0.08037 -0.0965 0.0165 1.0000
16.000 1.5869 0.09054 0.08370 -0.0961 0.0159 1.0000
16.250 1.5861 0.09374 0.08698 -0.0958 0.0155 1.0000
16.500 1.5857 0.09693 0.09026 -0.0956 0.0150 1.0000
16.750 1.5852 0.10014 0.09357 -0.0955 0.0146 1.0000
17.000 1.5833 0.10356 0.09707 -0.0955 0.0141 1.0000
17.250 1.5811 0.10704 0.10063 -0.0956 0.0137 1.0000
17.500 1.5783 0.11064 0.10430 -0.0958 0.0133 1.0000
17.750 1.5742 0.11447 0.10822 -0.0961 0.0130 1.0000
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