SG6043 (sg6043-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: SG6043 (sg6043-il) Reynolds number: 200,000 Max Cl/Cd: 94.74 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sg6043-il-200000-n5.txt Download as CSV file: xf-sg6043-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SG6043
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.1259 0.09015 0.08642 -0.0818 0.9528 0.0278
-7.750 -0.1137 0.08678 0.08305 -0.0850 0.9489 0.0287
-7.500 -0.1082 0.08355 0.07984 -0.0876 0.9413 0.0298
-7.250 -0.1032 0.07957 0.07588 -0.0929 0.9343 0.0304
-7.000 -0.0947 0.07466 0.07098 -0.1001 0.9259 0.0306
-6.750 -0.0780 0.07336 0.06969 -0.0965 0.9251 0.0320
-6.250 -0.0495 0.05822 0.05445 -0.1159 0.9107 0.0215
-6.000 -0.0220 0.05452 0.05069 -0.1217 0.9087 0.0210
-5.750 -0.0095 0.05050 0.04661 -0.1254 0.8995 0.0205
-5.500 0.0252 0.04328 0.03917 -0.1360 0.8961 0.0199
-5.250 0.0685 0.03321 0.02853 -0.1483 0.8938 0.0192
-5.000 0.0903 0.02767 0.02242 -0.1510 0.8860 0.0198
-4.750 0.1285 0.02286 0.01675 -0.1556 0.8833 0.0208
-4.500 0.1661 0.02019 0.01348 -0.1584 0.8812 0.0211
-4.250 0.2034 0.01841 0.01126 -0.1607 0.8794 0.0214
-4.000 0.2312 0.01745 0.01017 -0.1610 0.8748 0.0220
-3.750 0.2600 0.01668 0.00929 -0.1613 0.8702 0.0227
-3.500 0.2934 0.01591 0.00840 -0.1625 0.8670 0.0237
-3.250 0.3288 0.01524 0.00757 -0.1641 0.8645 0.0256
-3.000 0.3596 0.01473 0.00706 -0.1648 0.8605 0.0274
-2.750 0.3866 0.01431 0.00660 -0.1647 0.8550 0.0289
-2.500 0.4195 0.01383 0.00605 -0.1657 0.8511 0.0312
-2.250 0.4549 0.01340 0.00557 -0.1672 0.8481 0.0357
-2.000 0.4814 0.01314 0.00534 -0.1670 0.8422 0.0450
-1.750 0.5113 0.01286 0.00509 -0.1674 0.8369 0.0640
-1.500 0.5451 0.01259 0.00484 -0.1686 0.8330 0.0891
-1.250 0.5731 0.01235 0.00477 -0.1688 0.8274 0.1306
-1.000 0.6017 0.01208 0.00468 -0.1691 0.8215 0.1928
-0.750 0.6348 0.01164 0.00458 -0.1705 0.8172 0.3184
-0.500 0.6616 0.01125 0.00470 -0.1705 0.8112 0.4995
-0.250 0.6879 0.01106 0.00475 -0.1700 0.8049 0.6111
0.000 0.7177 0.01086 0.00471 -0.1700 0.8001 0.6943
0.250 0.7369 0.01078 0.00480 -0.1679 0.7921 0.7644
0.500 0.7584 0.01057 0.00471 -0.1659 0.7858 0.8553
0.750 0.7833 0.01043 0.00462 -0.1649 0.7782 1.0000
1.000 0.8127 0.01048 0.00457 -0.1651 0.7709 1.0000
1.250 0.8399 0.01057 0.00459 -0.1650 0.7628 1.0000
1.500 0.8686 0.01063 0.00456 -0.1650 0.7546 1.0000
1.750 0.8946 0.01073 0.00461 -0.1646 0.7452 1.0000
2.000 0.9240 0.01079 0.00459 -0.1647 0.7366 1.0000
2.250 0.9485 0.01091 0.00467 -0.1640 0.7256 1.0000
2.500 0.9745 0.01100 0.00472 -0.1635 0.7146 1.0000
2.750 1.0010 0.01110 0.00477 -0.1631 0.7027 1.0000
3.000 1.0270 0.01121 0.00481 -0.1626 0.6899 1.0000
3.250 1.0516 0.01135 0.00490 -0.1618 0.6758 1.0000
3.500 1.0763 0.01150 0.00499 -0.1611 0.6605 1.0000
3.750 1.1005 0.01167 0.00511 -0.1602 0.6438 1.0000
4.000 1.1239 0.01187 0.00524 -0.1592 0.6251 1.0000
4.250 1.1464 0.01210 0.00540 -0.1581 0.6046 1.0000
4.500 1.1682 0.01238 0.00559 -0.1568 0.5828 1.0000
4.750 1.1888 0.01270 0.00580 -0.1553 0.5585 1.0000
5.250 1.2261 0.01348 0.00633 -0.1516 0.5053 1.0000
5.500 1.2431 0.01393 0.00667 -0.1495 0.4781 1.0000
5.750 1.2587 0.01442 0.00704 -0.1472 0.4512 1.0000
6.000 1.2726 0.01494 0.00744 -0.1446 0.4234 1.0000
6.250 1.2861 0.01551 0.00789 -0.1420 0.3961 1.0000
6.500 1.2988 0.01613 0.00839 -0.1393 0.3688 1.0000
6.750 1.3109 0.01681 0.00895 -0.1366 0.3421 1.0000
7.000 1.3239 0.01749 0.00953 -0.1341 0.3164 1.0000
7.250 1.3359 0.01824 0.01017 -0.1315 0.2914 1.0000
7.500 1.3476 0.01903 0.01085 -0.1290 0.2667 1.0000
7.750 1.3597 0.01983 0.01158 -0.1266 0.2437 1.0000
8.000 1.3716 0.02068 0.01234 -0.1242 0.2223 1.0000
8.250 1.3832 0.02157 0.01315 -0.1219 0.2035 1.0000
8.500 1.3957 0.02243 0.01396 -0.1198 0.1864 1.0000
8.750 1.4081 0.02333 0.01484 -0.1177 0.1713 1.0000
9.000 1.4201 0.02427 0.01575 -0.1157 0.1579 1.0000
9.250 1.4320 0.02524 0.01670 -0.1136 0.1459 1.0000
9.500 1.4444 0.02620 0.01768 -0.1118 0.1349 1.0000
9.750 1.4562 0.02722 0.01872 -0.1099 0.1256 1.0000
10.000 1.4667 0.02836 0.01986 -0.1079 0.1171 1.0000
10.250 1.4786 0.02942 0.02096 -0.1061 0.1092 1.0000
10.500 1.4888 0.03063 0.02220 -0.1043 0.1024 1.0000
10.750 1.4995 0.03183 0.02346 -0.1026 0.0957 1.0000
11.000 1.5088 0.03316 0.02483 -0.1008 0.0901 1.0000
11.250 1.5189 0.03446 0.02620 -0.0991 0.0847 1.0000
11.500 1.5259 0.03604 0.02780 -0.0973 0.0799 1.0000
11.750 1.5364 0.03737 0.02926 -0.0959 0.0753 1.0000
12.000 1.5438 0.03898 0.03093 -0.0943 0.0711 1.0000
12.250 1.5506 0.04069 0.03271 -0.0927 0.0674 1.0000
12.500 1.5590 0.04230 0.03443 -0.0914 0.0636 1.0000
12.750 1.5646 0.04421 0.03640 -0.0900 0.0604 1.0000
13.000 1.5697 0.04621 0.03848 -0.0886 0.0576 1.0000
13.250 1.5767 0.04808 0.04049 -0.0875 0.0546 1.0000
13.500 1.5813 0.05023 0.04273 -0.0863 0.0521 1.0000
13.750 1.5829 0.05278 0.04533 -0.0853 0.0499 1.0000
14.000 1.5884 0.05495 0.04766 -0.0844 0.0476 1.0000
14.250 1.5924 0.05735 0.05019 -0.0836 0.0454 1.0000
14.500 1.5944 0.06005 0.05298 -0.0829 0.0435 1.0000
14.750 1.5932 0.06322 0.05623 -0.0824 0.0419 1.0000
15.000 1.5958 0.06601 0.05918 -0.0820 0.0403 1.0000
15.250 1.5974 0.06899 0.06232 -0.0817 0.0387 1.0000
15.500 1.5975 0.07224 0.06571 -0.0816 0.0373 1.0000
15.750 1.5956 0.07585 0.06943 -0.0818 0.0361 1.0000
16.000 1.5911 0.07991 0.07358 -0.0821 0.0350 1.0000
16.250 1.5899 0.08362 0.07745 -0.0825 0.0339 1.0000
16.500 1.5883 0.08745 0.08146 -0.0831 0.0327 1.0000
16.750 1.5855 0.09154 0.08572 -0.0839 0.0316 1.0000
17.000 1.5816 0.09589 0.09020 -0.0851 0.0307 1.0000
17.250 1.5766 0.10050 0.09494 -0.0864 0.0299 1.0000
17.500 1.5701 0.10543 0.09996 -0.0881 0.0291 1.0000
17.750 1.5649 0.11022 0.10490 -0.0897 0.0284 1.0000
18.000 1.5603 0.11498 0.10985 -0.0915 0.0277 1.0000
18.250 1.5550 0.11992 0.11497 -0.0936 0.0270 1.0000
18.500 1.5494 0.12501 0.12021 -0.0959 0.0264 1.0000
18.750 1.5435 0.13020 0.12555 -0.0984 0.0258 1.0000
19.000 1.5377 0.13543 0.13092 -0.1012 0.0253 1.0000
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Polar data table (+)
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