GOE 446 AIRFOIL (goe446-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 446 AIRFOIL (goe446-il) Reynolds number: 200,000 Max Cl/Cd: 83.75 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe446-il-200000.txt Download as CSV file: xf-goe446-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.0293 0.09299 0.08923 -0.1034 0.9560 0.0632
-8.500 -0.0191 0.09030 0.08653 -0.1054 0.9466 0.0653
-8.250 -0.0280 0.08799 0.08423 -0.1155 0.9317 0.0683
-8.000 -0.0160 0.08331 0.07955 -0.1190 0.9267 0.0690
-7.750 0.0099 0.07979 0.07601 -0.1179 0.9254 0.0698
-7.500 0.0188 0.07768 0.07390 -0.1166 0.9157 0.0706
-7.250 0.0335 0.07498 0.07118 -0.1180 0.9109 0.0720
-7.000 0.0391 0.07283 0.06903 -0.1188 0.9011 0.0735
-6.750 0.0527 0.06958 0.06574 -0.1237 0.8952 0.0764
-6.500 0.0614 0.06375 0.05975 -0.1391 0.8827 0.0793
-6.250 0.0783 0.06112 0.05713 -0.1374 0.8797 0.0800
-6.000 0.0904 0.05933 0.05536 -0.1358 0.8728 0.0810
-5.750 0.1078 0.05722 0.05321 -0.1362 0.8675 0.0828
-5.500 0.1441 0.05285 0.04824 -0.1509 0.8612 0.0907
-5.250 0.1546 0.04873 0.04424 -0.1500 0.8546 0.0916
-5.000 0.1751 0.04622 0.04173 -0.1501 0.8503 0.0925
-4.750 0.1979 0.04402 0.03948 -0.1506 0.8458 0.0939
-4.500 0.2208 0.03189 0.02629 -0.1575 0.8379 0.0694
-4.250 0.2492 0.02913 0.02329 -0.1585 0.8333 0.0665
-4.000 0.2736 0.02610 0.01985 -0.1589 0.8269 0.0658
-3.750 0.2993 0.02326 0.01651 -0.1592 0.8208 0.0648
-3.500 0.3298 0.02104 0.01381 -0.1598 0.8168 0.0647
-3.250 0.3570 0.01981 0.01227 -0.1598 0.8119 0.0657
-3.000 0.3830 0.01893 0.01115 -0.1594 0.8062 0.0672
-2.750 0.4128 0.01805 0.01007 -0.1596 0.8018 0.0694
-2.500 0.4435 0.01769 0.00971 -0.1601 0.7980 0.0731
-2.250 0.4673 0.01746 0.00941 -0.1593 0.7914 0.0774
-2.000 0.4957 0.01695 0.00889 -0.1594 0.7867 0.0827
-1.750 0.5271 0.01651 0.00837 -0.1598 0.7829 0.0931
-1.500 0.5515 0.01642 0.00835 -0.1592 0.7766 0.1100
-1.250 0.5790 0.01633 0.00827 -0.1592 0.7710 0.1280
-1.000 0.6099 0.01612 0.00798 -0.1596 0.7667 0.1408
-0.750 0.6350 0.01617 0.00801 -0.1592 0.7606 0.1506
-0.500 0.6617 0.01602 0.00792 -0.1590 0.7548 0.1622
-0.250 0.6921 0.01582 0.00769 -0.1594 0.7504 0.1747
0.000 0.7175 0.01581 0.00770 -0.1590 0.7442 0.1847
0.250 0.7440 0.01560 0.00756 -0.1587 0.7379 0.1945
0.500 0.7750 0.01537 0.00730 -0.1592 0.7331 0.2070
0.750 0.7988 0.01530 0.00735 -0.1585 0.7258 0.2236
1.000 0.8266 0.01501 0.00725 -0.1585 0.7197 0.2712
1.250 0.8538 0.01337 0.00718 -0.1578 0.7151 1.0000
1.500 0.8762 0.01356 0.00730 -0.1567 0.7070 1.0000
1.750 0.9057 0.01359 0.00719 -0.1569 0.7011 1.0000
2.000 0.9307 0.01374 0.00727 -0.1563 0.6936 1.0000
2.250 0.9578 0.01379 0.00724 -0.1560 0.6862 1.0000
2.500 0.9850 0.01389 0.00725 -0.1558 0.6791 1.0000
2.750 1.0101 0.01399 0.00731 -0.1553 0.6707 1.0000
3.000 1.0385 0.01406 0.00729 -0.1553 0.6640 1.0000
3.250 1.0621 0.01419 0.00742 -0.1545 0.6548 1.0000
3.500 1.0901 0.01428 0.00742 -0.1544 0.6475 1.0000
3.750 1.1137 0.01441 0.00754 -0.1536 0.6378 1.0000
4.000 1.1398 0.01453 0.00761 -0.1533 0.6295 1.0000
4.250 1.1646 0.01466 0.00772 -0.1527 0.6204 1.0000
4.500 1.1895 0.01485 0.00788 -0.1522 0.6118 1.0000
4.750 1.2152 0.01500 0.00799 -0.1518 0.6033 1.0000
5.000 1.2390 0.01522 0.00822 -0.1511 0.5944 1.0000
5.250 1.2652 0.01539 0.00832 -0.1508 0.5864 1.0000
5.500 1.2875 0.01564 0.00859 -0.1498 0.5769 1.0000
5.750 1.3147 0.01579 0.00864 -0.1497 0.5687 1.0000
6.000 1.3342 0.01605 0.00896 -0.1482 0.5583 1.0000
6.250 1.3581 0.01628 0.00915 -0.1476 0.5493 1.0000
6.500 1.3794 0.01647 0.00930 -0.1464 0.5382 1.0000
6.750 1.3976 0.01673 0.00959 -0.1446 0.5265 1.0000
7.000 1.4199 0.01702 0.00983 -0.1437 0.5174 1.0000
7.250 1.4408 0.01735 0.01022 -0.1426 0.5097 1.0000
7.500 1.4654 0.01769 0.01053 -0.1422 0.5030 1.0000
7.750 1.4839 0.01806 0.01098 -0.1407 0.4951 1.0000
8.000 1.5063 0.01840 0.01128 -0.1398 0.4869 1.0000
8.250 1.5208 0.01877 0.01172 -0.1375 0.4767 1.0000
8.500 1.5360 0.01916 0.01213 -0.1354 0.4662 1.0000
8.750 1.5514 0.01955 0.01246 -0.1332 0.4555 1.0000
9.000 1.5594 0.02002 0.01302 -0.1299 0.4451 1.0000
9.250 1.5717 0.02053 0.01356 -0.1274 0.4348 1.0000
9.500 1.5838 0.02107 0.01409 -0.1249 0.4245 1.0000
9.750 1.5921 0.02169 0.01482 -0.1219 0.4139 1.0000
10.000 1.6011 0.02237 0.01553 -0.1191 0.4027 1.0000
10.250 1.6080 0.02315 0.01632 -0.1161 0.3902 1.0000
10.500 1.6128 0.02404 0.01730 -0.1130 0.3767 1.0000
10.750 1.6171 0.02506 0.01838 -0.1100 0.3621 1.0000
11.000 1.6197 0.02626 0.01962 -0.1069 0.3452 1.0000
11.250 1.6202 0.02769 0.02106 -0.1038 0.3246 1.0000
11.500 1.6171 0.02950 0.02282 -0.1006 0.2988 1.0000
11.750 1.6093 0.03180 0.02501 -0.0972 0.2705 1.0000
12.000 1.5983 0.03454 0.02761 -0.0939 0.2434 1.0000
12.250 1.5874 0.03748 0.03042 -0.0909 0.2214 1.0000
12.500 1.5804 0.04030 0.03317 -0.0885 0.2027 1.0000
12.750 1.5745 0.04313 0.03596 -0.0864 0.1866 1.0000
13.000 1.5695 0.04600 0.03880 -0.0846 0.1721 1.0000
13.250 1.5643 0.04899 0.04176 -0.0829 0.1577 1.0000
13.500 1.5591 0.05209 0.04483 -0.0814 0.1438 1.0000
13.750 1.5540 0.05527 0.04800 -0.0801 0.1302 1.0000
14.000 1.5469 0.05876 0.05146 -0.0788 0.1146 1.0000
14.250 1.5380 0.06258 0.05522 -0.0777 0.0977 1.0000
14.500 1.5285 0.06656 0.05911 -0.0767 0.0758 1.0000
14.750 1.5144 0.07116 0.06357 -0.0759 0.0562 1.0000
15.250 1.4948 0.07970 0.07209 -0.0748 0.0455 1.0000
15.500 1.4862 0.08396 0.07641 -0.0746 0.0432 1.0000
15.750 1.4778 0.08830 0.08083 -0.0745 0.0415 1.0000
16.000 1.4725 0.09230 0.08496 -0.0745 0.0402 1.0000
16.250 1.4665 0.09645 0.08922 -0.0747 0.0391 1.0000
16.500 1.4599 0.10068 0.09356 -0.0750 0.0381 1.0000
16.750 1.4527 0.10503 0.09799 -0.0754 0.0373 1.0000
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