GOE 447 AIRFOIL (goe447-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 447 AIRFOIL (goe447-il) Reynolds number: 500,000 Max Cl/Cd: 129.36 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe447-il-500000.txt Download as CSV file: xf-goe447-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 0.0605 0.09183 0.08851 -0.1104 0.8076 0.0323
-9.000 0.0687 0.08917 0.08584 -0.1121 0.8027 0.0335
-8.750 0.0617 0.08561 0.08224 -0.1190 0.7973 0.0344
-8.500 0.0749 0.08259 0.07920 -0.1183 0.7936 0.0347
-8.250 0.0891 0.08042 0.07703 -0.1181 0.7895 0.0350
-8.000 0.1015 0.07839 0.07499 -0.1187 0.7853 0.0354
-7.750 0.1128 0.07630 0.07287 -0.1198 0.7814 0.0359
-7.500 0.1236 0.07406 0.07061 -0.1212 0.7775 0.0366
-7.250 0.1331 0.07168 0.06825 -0.1230 0.7734 0.0376
-7.000 0.1438 0.06600 0.06254 -0.1378 0.7683 0.0396
-6.750 0.1556 0.06364 0.06015 -0.1368 0.7649 0.0399
-6.500 0.1716 0.06181 0.05828 -0.1369 0.7613 0.0402
-6.250 0.1886 0.05985 0.05633 -0.1382 0.7574 0.0407
-6.000 0.2072 0.05770 0.05417 -0.1405 0.7532 0.0414
-5.750 0.2278 0.05529 0.05171 -0.1437 0.7493 0.0427
-5.500 0.2619 0.04856 0.04480 -0.1572 0.7454 0.0458
-5.250 0.2809 0.04697 0.04322 -0.1576 0.7417 0.0462
-5.000 0.3022 0.04529 0.04152 -0.1587 0.7377 0.0468
-4.750 0.3263 0.04330 0.03948 -0.1609 0.7340 0.0478
-4.500 0.3654 0.01783 0.01211 -0.1809 0.7316 0.0394
-4.250 0.3923 0.01605 0.00990 -0.1814 0.7282 0.0396
-4.000 0.4184 0.01456 0.00816 -0.1815 0.7246 0.0401
-3.750 0.4457 0.01388 0.00737 -0.1816 0.7208 0.0407
-3.500 0.4736 0.01343 0.00684 -0.1817 0.7174 0.0414
-3.250 0.5019 0.01310 0.00641 -0.1819 0.7141 0.0424
-3.000 0.5301 0.01280 0.00600 -0.1820 0.7106 0.0436
-2.750 0.5576 0.01242 0.00556 -0.1819 0.7066 0.0448
-2.500 0.5854 0.01199 0.00506 -0.1819 0.7027 0.0459
-2.250 0.6135 0.01177 0.00482 -0.1820 0.6994 0.0475
-2.000 0.6423 0.01167 0.00466 -0.1822 0.6963 0.0495
-1.750 0.6703 0.01151 0.00447 -0.1822 0.6932 0.0518
-1.500 0.6981 0.01142 0.00443 -0.1823 0.6898 0.0552
-1.250 0.7262 0.01137 0.00437 -0.1823 0.6864 0.0603
-1.000 0.7547 0.01147 0.00446 -0.1824 0.6832 0.0666
-0.750 0.7834 0.01149 0.00446 -0.1826 0.6799 0.0734
-0.500 0.8109 0.01145 0.00441 -0.1826 0.6765 0.0795
-0.250 0.8381 0.01138 0.00438 -0.1826 0.6726 0.0843
0.000 0.8658 0.01138 0.00437 -0.1826 0.6689 0.0885
0.250 0.8937 0.01122 0.00418 -0.1827 0.6655 0.0928
0.500 0.9218 0.01119 0.00415 -0.1829 0.6621 0.0968
0.750 0.9485 0.01116 0.00416 -0.1828 0.6582 0.1010
1.000 0.9755 0.01107 0.00408 -0.1827 0.6539 0.1048
1.250 1.0028 0.01097 0.00399 -0.1827 0.6495 0.1091
1.500 1.0301 0.01096 0.00396 -0.1826 0.6450 0.1115
1.750 1.0562 0.01092 0.00396 -0.1824 0.6399 0.1141
2.000 1.0829 0.01090 0.00393 -0.1822 0.6350 0.1168
2.250 1.1100 0.01092 0.00392 -0.1821 0.6298 0.1224
2.500 1.1353 0.01088 0.00397 -0.1817 0.6239 0.1318
2.750 1.1613 0.01074 0.00408 -0.1816 0.6182 0.2366
3.000 1.1874 0.01061 0.00424 -0.1815 0.6129 0.3838
3.250 1.2086 0.00964 0.00443 -0.1802 0.6070 1.0000
3.500 1.2339 0.00976 0.00449 -0.1798 0.6008 1.0000
3.750 1.2587 0.00988 0.00458 -0.1793 0.5941 1.0000
4.000 1.2828 0.01000 0.00467 -0.1787 0.5863 1.0000
4.250 1.3068 0.01014 0.00478 -0.1780 0.5790 1.0000
4.500 1.3302 0.01029 0.00490 -0.1773 0.5705 1.0000
4.750 1.3531 0.01046 0.00504 -0.1765 0.5619 1.0000
5.000 1.3748 0.01065 0.00520 -0.1754 0.5519 1.0000
5.250 1.3964 0.01084 0.00538 -0.1743 0.5415 1.0000
5.500 1.4164 0.01109 0.00558 -0.1730 0.5308 1.0000
5.750 1.4346 0.01138 0.00580 -0.1712 0.5187 1.0000
6.000 1.4516 0.01166 0.00606 -0.1693 0.5067 1.0000
6.250 1.4679 0.01199 0.00636 -0.1673 0.4958 1.0000
6.500 1.4827 0.01241 0.00671 -0.1650 0.4846 1.0000
6.750 1.4979 0.01284 0.00709 -0.1629 0.4732 1.0000
7.000 1.5140 0.01327 0.00751 -0.1610 0.4635 1.0000
7.250 1.5290 0.01377 0.00796 -0.1590 0.4553 1.0000
7.500 1.5473 0.01417 0.00837 -0.1576 0.4486 1.0000
7.750 1.5630 0.01468 0.00886 -0.1558 0.4413 1.0000
8.000 1.5788 0.01519 0.00938 -0.1540 0.4334 1.0000
8.250 1.5925 0.01581 0.00997 -0.1520 0.4247 1.0000
8.500 1.6076 0.01638 0.01056 -0.1503 0.4166 1.0000
8.750 1.6209 0.01707 0.01123 -0.1484 0.4083 1.0000
9.000 1.6356 0.01770 0.01190 -0.1467 0.4002 1.0000
9.250 1.6468 0.01854 0.01272 -0.1446 0.3908 1.0000
9.500 1.6618 0.01922 0.01344 -0.1431 0.3824 1.0000
9.750 1.6722 0.02017 0.01437 -0.1411 0.3734 1.0000
10.000 1.6853 0.02101 0.01526 -0.1395 0.3623 1.0000
10.250 1.6949 0.02208 0.01633 -0.1375 0.3498 1.0000
10.500 1.7019 0.02338 0.01760 -0.1353 0.3338 1.0000
10.750 1.7043 0.02503 0.01918 -0.1327 0.3129 1.0000
11.000 1.7007 0.02717 0.02120 -0.1296 0.2859 1.0000
11.250 1.6922 0.02977 0.02364 -0.1262 0.2578 1.0000
11.500 1.6838 0.03246 0.02621 -0.1230 0.2346 1.0000
11.750 1.6808 0.03483 0.02851 -0.1204 0.2178 1.0000
12.250 1.6808 0.03923 0.03284 -0.1162 0.1941 1.0000
12.500 1.6826 0.04136 0.03497 -0.1144 0.1842 1.0000
12.750 1.6822 0.04374 0.03733 -0.1125 0.1745 1.0000
13.000 1.6818 0.04617 0.03974 -0.1108 0.1630 1.0000
13.250 1.6811 0.04869 0.04224 -0.1091 0.1496 1.0000
13.500 1.6748 0.05182 0.04527 -0.1072 0.1253 1.0000
13.750 1.6477 0.05713 0.05027 -0.1043 0.0827 1.0000
14.000 1.6281 0.06187 0.05493 -0.1021 0.0596 1.0000
14.250 1.6088 0.06676 0.05969 -0.1002 0.0377 1.0000
14.500 1.6006 0.07052 0.06345 -0.0989 0.0316 1.0000
14.750 1.5970 0.07382 0.06681 -0.0979 0.0288 1.0000
15.000 1.5945 0.07708 0.07014 -0.0971 0.0271 1.0000
15.250 1.5895 0.08068 0.07382 -0.0963 0.0257 1.0000
15.500 1.5860 0.08414 0.07736 -0.0957 0.0246 1.0000
15.750 1.5845 0.08738 0.08069 -0.0952 0.0238 1.0000
16.000 1.5813 0.09088 0.08429 -0.0948 0.0230 1.0000
16.250 1.5774 0.09453 0.08802 -0.0945 0.0223 1.0000
16.500 1.5711 0.09855 0.09212 -0.0944 0.0217 1.0000
16.750 1.5617 0.10307 0.09673 -0.0943 0.0212 1.0000
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