GOE 446 AIRFOIL (goe446-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 446 AIRFOIL (goe446-il) Reynolds number: 500,000 Max Cl/Cd: 111.66 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe446-il-500000-n5.txt Download as CSV file: xf-goe446-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 446 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.0878 0.08920 0.08627 -0.0963 0.8685 0.0236
-8.750 -0.2143 0.02703 0.02275 -0.1517 0.8052 0.0256
-8.500 -0.1955 0.02431 0.01968 -0.1530 0.7976 0.0258
-8.250 -0.1739 0.02252 0.01759 -0.1535 0.7903 0.0260
-8.000 -0.1508 0.02109 0.01590 -0.1539 0.7841 0.0261
-7.750 -0.1267 0.01989 0.01447 -0.1541 0.7782 0.0264
-7.500 -0.1019 0.01887 0.01324 -0.1543 0.7727 0.0266
-7.250 -0.0765 0.01798 0.01215 -0.1544 0.7676 0.0268
-7.000 -0.0505 0.01718 0.01117 -0.1545 0.7623 0.0270
-6.750 -0.0243 0.01647 0.01030 -0.1546 0.7573 0.0272
-6.250 0.0292 0.01526 0.00879 -0.1548 0.7482 0.0277
-6.000 0.0562 0.01476 0.00816 -0.1548 0.7425 0.0280
-5.750 0.0833 0.01435 0.00761 -0.1548 0.7369 0.0283
-5.500 0.1109 0.01398 0.00714 -0.1548 0.7320 0.0286
-5.250 0.1385 0.01365 0.00670 -0.1549 0.7268 0.0288
-5.000 0.1655 0.01314 0.00611 -0.1549 0.7218 0.0291
-4.750 0.1929 0.01271 0.00561 -0.1549 0.7171 0.0295
-4.500 0.2205 0.01236 0.00523 -0.1550 0.7118 0.0299
-4.250 0.2480 0.01209 0.00490 -0.1550 0.7061 0.0302
-4.000 0.2757 0.01186 0.00461 -0.1550 0.7016 0.0306
-3.750 0.3039 0.01162 0.00435 -0.1551 0.6978 0.0311
-3.500 0.3320 0.01141 0.00411 -0.1552 0.6938 0.0316
-3.250 0.3600 0.01123 0.00389 -0.1553 0.6897 0.0321
-3.000 0.3880 0.01108 0.00369 -0.1553 0.6856 0.0326
-2.750 0.4163 0.01092 0.00351 -0.1554 0.6815 0.0332
-2.500 0.4445 0.01080 0.00336 -0.1555 0.6772 0.0337
-2.250 0.4725 0.01063 0.00318 -0.1556 0.6731 0.0350
-2.000 0.5004 0.01053 0.00304 -0.1556 0.6692 0.0365
-1.750 0.5287 0.01042 0.00293 -0.1557 0.6652 0.0381
-1.500 0.5568 0.01032 0.00283 -0.1558 0.6604 0.0400
-1.250 0.5846 0.01022 0.00273 -0.1558 0.6555 0.0448
-1.000 0.6122 0.01011 0.00270 -0.1559 0.6507 0.0671
-0.750 0.6402 0.01007 0.00271 -0.1559 0.6454 0.0800
-0.500 0.6680 0.01006 0.00271 -0.1559 0.6400 0.0884
-0.250 0.6955 0.01007 0.00270 -0.1559 0.6350 0.0943
0.000 0.7234 0.01005 0.00272 -0.1559 0.6294 0.1009
0.250 0.7508 0.01007 0.00272 -0.1559 0.6232 0.1047
0.500 0.7780 0.01007 0.00273 -0.1558 0.6173 0.1110
0.750 0.8054 0.01008 0.00275 -0.1557 0.6101 0.1169
1.000 0.8319 0.01012 0.00277 -0.1555 0.6026 0.1230
1.250 0.8589 0.01013 0.00281 -0.1554 0.5941 0.1338
1.500 0.8851 0.01017 0.00286 -0.1551 0.5856 0.1467
1.750 0.9116 0.01020 0.00291 -0.1550 0.5765 0.1636
2.000 0.9375 0.01022 0.00300 -0.1547 0.5675 0.1955
2.250 0.9632 0.01018 0.00311 -0.1545 0.5573 0.2764
2.500 0.9878 0.00950 0.00337 -0.1545 0.5475 0.6683
2.750 1.0070 0.00908 0.00351 -0.1523 0.5374 1.0000
3.000 1.0318 0.00926 0.00362 -0.1518 0.5258 1.0000
3.250 1.0563 0.00946 0.00375 -0.1512 0.5146 1.0000
3.500 1.0801 0.00968 0.00390 -0.1505 0.5040 1.0000
3.750 1.1042 0.00989 0.00405 -0.1499 0.4940 1.0000
4.000 1.1278 0.01013 0.00423 -0.1492 0.4839 1.0000
4.250 1.1501 0.01041 0.00443 -0.1482 0.4729 1.0000
4.500 1.1728 0.01066 0.00463 -0.1474 0.4621 1.0000
4.750 1.1955 0.01092 0.00484 -0.1465 0.4539 1.0000
5.000 1.2183 0.01116 0.00506 -0.1457 0.4463 1.0000
5.250 1.2398 0.01144 0.00529 -0.1446 0.4386 1.0000
5.500 1.2606 0.01170 0.00553 -0.1434 0.4301 1.0000
5.750 1.2799 0.01201 0.00580 -0.1419 0.4211 1.0000
6.000 1.2987 0.01236 0.00610 -0.1404 0.4102 1.0000
6.250 1.3193 0.01265 0.00638 -0.1392 0.4021 1.0000
6.500 1.3404 0.01294 0.00668 -0.1382 0.3962 1.0000
6.750 1.3601 0.01329 0.00701 -0.1369 0.3910 1.0000
7.000 1.3823 0.01354 0.00729 -0.1360 0.3853 1.0000
7.250 1.4011 0.01392 0.00766 -0.1347 0.3768 1.0000
7.500 1.4192 0.01434 0.00806 -0.1332 0.3640 1.0000
7.750 1.4352 0.01486 0.00852 -0.1314 0.3479 1.0000
8.000 1.4505 0.01543 0.00904 -0.1296 0.3313 1.0000
8.250 1.4634 0.01613 0.00966 -0.1274 0.3112 1.0000
8.500 1.4717 0.01711 0.01049 -0.1247 0.2817 1.0000
8.750 1.4746 0.01844 0.01162 -0.1213 0.2465 1.0000
9.000 1.4769 0.01988 0.01289 -0.1180 0.2153 1.0000
9.250 1.4807 0.02130 0.01418 -0.1150 0.1903 1.0000
9.500 1.4859 0.02269 0.01546 -0.1124 0.1681 1.0000
9.750 1.4908 0.02416 0.01684 -0.1099 0.1490 1.0000
10.000 1.4975 0.02555 0.01817 -0.1077 0.1349 1.0000
10.250 1.5058 0.02688 0.01947 -0.1058 0.1240 1.0000
10.500 1.5143 0.02822 0.02081 -0.1040 0.1155 1.0000
10.750 1.5222 0.02964 0.02221 -0.1023 0.1079 1.0000
11.000 1.5312 0.03101 0.02360 -0.1008 0.1010 1.0000
11.250 1.5374 0.03265 0.02523 -0.0990 0.0930 1.0000
11.500 1.5432 0.03437 0.02693 -0.0974 0.0830 1.0000
11.750 1.5406 0.03685 0.02929 -0.0952 0.0614 1.0000
12.000 1.5249 0.04061 0.03289 -0.0923 0.0332 1.0000
12.250 1.5263 0.04294 0.03525 -0.0907 0.0284 1.0000
12.500 1.5305 0.04503 0.03741 -0.0894 0.0260 1.0000
12.750 1.5344 0.04720 0.03963 -0.0882 0.0242 1.0000
13.000 1.5401 0.04923 0.04173 -0.0872 0.0229 1.0000
13.250 1.5443 0.05145 0.04401 -0.0862 0.0216 1.0000
13.500 1.5472 0.05383 0.04646 -0.0851 0.0205 1.0000
13.750 1.5509 0.05615 0.04886 -0.0842 0.0197 1.0000
14.000 1.5549 0.05850 0.05128 -0.0834 0.0189 1.0000
14.250 1.5581 0.06097 0.05382 -0.0827 0.0181 1.0000
14.500 1.5600 0.06364 0.05656 -0.0820 0.0175 1.0000
14.750 1.5606 0.06649 0.05948 -0.0813 0.0169 1.0000
15.000 1.5602 0.06947 0.06254 -0.0807 0.0165 1.0000
15.250 1.5618 0.07228 0.06544 -0.0802 0.0160 1.0000
15.500 1.5626 0.07523 0.06848 -0.0798 0.0156 1.0000
15.750 1.5631 0.07826 0.07159 -0.0795 0.0152 1.0000
16.000 1.5629 0.08139 0.07481 -0.0793 0.0148 1.0000
16.250 1.5618 0.08468 0.07817 -0.0791 0.0144 1.0000
16.500 1.5597 0.08813 0.08171 -0.0791 0.0140 1.0000
16.750 1.5565 0.09176 0.08541 -0.0791 0.0137 1.0000
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