SG6041 (sg6041-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: SG6041 (sg6041-il) Reynolds number: 200,000 Max Cl/Cd: 63.89 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sg6041-il-200000-n5.txt Download as CSV file: xf-sg6041-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SG6041
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4479 0.08786 0.08419 -0.0385 1.0000 0.0122
-9.250 -0.4528 0.08380 0.08019 -0.0399 1.0000 0.0121
-9.000 -0.4617 0.07926 0.07571 -0.0415 1.0000 0.0119
-8.750 -0.4756 0.07434 0.07086 -0.0435 1.0000 0.0118
-8.500 -0.4961 0.06990 0.06650 -0.0453 1.0000 0.0115
-8.250 -0.5240 0.06668 0.06331 -0.0435 1.0000 0.0115
-8.000 -0.5455 0.06310 0.05971 -0.0415 1.0000 0.0113
-7.750 -0.5427 0.05410 0.05042 -0.0480 0.9935 0.0110
-7.500 -0.5390 0.04450 0.04034 -0.0519 0.9863 0.0107
-7.250 -0.5310 0.03694 0.03216 -0.0532 0.9799 0.0108
-7.000 -0.5143 0.03198 0.02659 -0.0538 0.9748 0.0109
-6.750 -0.4894 0.02892 0.02304 -0.0548 0.9720 0.0118
-6.500 -0.4701 0.02599 0.01952 -0.0540 0.9666 0.0126
-6.250 -0.4448 0.02354 0.01653 -0.0539 0.9628 0.0130
-6.000 -0.4166 0.02168 0.01441 -0.0545 0.9602 0.0134
-5.750 -0.3859 0.02031 0.01287 -0.0555 0.9583 0.0139
-5.500 -0.3619 0.01929 0.01172 -0.0549 0.9535 0.0146
-5.250 -0.3344 0.01827 0.01057 -0.0550 0.9497 0.0154
-5.000 -0.3042 0.01729 0.00944 -0.0556 0.9470 0.0167
-4.750 -0.2723 0.01650 0.00861 -0.0567 0.9448 0.0188
-4.500 -0.2429 0.01593 0.00796 -0.0572 0.9415 0.0220
-4.250 -0.2180 0.01530 0.00732 -0.0567 0.9363 0.0253
-4.000 -0.1878 0.01472 0.00673 -0.0574 0.9331 0.0312
-3.750 -0.1558 0.01420 0.00621 -0.0583 0.9305 0.0424
-3.500 -0.1266 0.01378 0.00578 -0.0587 0.9268 0.0572
-3.250 -0.1012 0.01339 0.00545 -0.0583 0.9213 0.0746
-3.000 -0.0709 0.01294 0.00510 -0.0590 0.9176 0.1044
-2.750 -0.0396 0.01236 0.00475 -0.0599 0.9147 0.1635
-2.500 -0.0181 0.01171 0.00453 -0.0590 0.9080 0.2724
-2.250 0.0052 0.01076 0.00429 -0.0586 0.9030 0.4591
-2.000 0.0309 0.01013 0.00428 -0.0579 0.8994 0.6323
-1.750 0.0527 0.01003 0.00431 -0.0562 0.8920 0.6984
-1.500 0.0813 0.00992 0.00425 -0.0559 0.8870 0.7392
-1.250 0.1086 0.00984 0.00418 -0.0553 0.8813 0.7699
-1.000 0.1330 0.00979 0.00418 -0.0540 0.8740 0.8053
-0.750 0.1599 0.00971 0.00416 -0.0530 0.8688 0.8416
-0.500 0.1824 0.00968 0.00415 -0.0513 0.8599 0.8632
-0.250 0.2123 0.00960 0.00402 -0.0513 0.8534 0.8758
0.000 0.2383 0.00955 0.00395 -0.0506 0.8437 0.8863
0.250 0.2667 0.00949 0.00384 -0.0505 0.8348 0.8960
0.500 0.2973 0.00941 0.00373 -0.0507 0.8253 0.9042
0.750 0.3254 0.00937 0.00367 -0.0505 0.8133 0.9141
1.000 0.3561 0.00933 0.00360 -0.0509 0.8008 0.9230
1.250 0.3878 0.00929 0.00353 -0.0515 0.7869 0.9319
1.500 0.4198 0.00926 0.00346 -0.0521 0.7703 0.9413
1.750 0.4547 0.00923 0.00338 -0.0534 0.7511 0.9489
2.000 0.4878 0.00925 0.00333 -0.0543 0.7284 0.9582
2.250 0.5224 0.00929 0.00327 -0.0556 0.7020 0.9663
2.500 0.5558 0.00938 0.00325 -0.0567 0.6687 0.9753
2.750 0.5883 0.00955 0.00324 -0.0576 0.6300 0.9850
3.000 0.6208 0.00980 0.00329 -0.0587 0.5858 0.9947
3.250 0.6446 0.01009 0.00339 -0.0581 0.5433 1.0000
3.500 0.6608 0.01041 0.00352 -0.0559 0.5030 1.0000
3.750 0.6776 0.01078 0.00369 -0.0538 0.4626 1.0000
4.000 0.6948 0.01119 0.00389 -0.0518 0.4213 1.0000
4.250 0.7128 0.01162 0.00412 -0.0500 0.3805 1.0000
4.500 0.7313 0.01209 0.00441 -0.0484 0.3395 1.0000
4.750 0.7505 0.01255 0.00470 -0.0470 0.3039 1.0000
5.000 0.7705 0.01300 0.00500 -0.0457 0.2714 1.0000
5.250 0.7908 0.01346 0.00535 -0.0445 0.2430 1.0000
5.500 0.8115 0.01392 0.00569 -0.0433 0.2176 1.0000
5.750 0.8327 0.01435 0.00606 -0.0423 0.1965 1.0000
6.000 0.8538 0.01481 0.00644 -0.0413 0.1773 1.0000
6.250 0.8746 0.01529 0.00687 -0.0402 0.1597 1.0000
6.500 0.8957 0.01576 0.00730 -0.0392 0.1453 1.0000
6.750 0.9169 0.01622 0.00775 -0.0382 0.1332 1.0000
7.000 0.9379 0.01670 0.00823 -0.0372 0.1217 1.0000
7.250 0.9585 0.01721 0.00875 -0.0361 0.1115 1.0000
7.500 0.9783 0.01777 0.00928 -0.0350 0.1024 1.0000
7.750 0.9988 0.01828 0.00982 -0.0339 0.0936 1.0000
8.000 1.0186 0.01883 0.01040 -0.0327 0.0860 1.0000
8.250 1.0377 0.01942 0.01101 -0.0315 0.0791 1.0000
8.500 1.0569 0.01999 0.01165 -0.0303 0.0735 1.0000
8.750 1.0754 0.02061 0.01229 -0.0290 0.0678 1.0000
9.000 1.0929 0.02127 0.01301 -0.0276 0.0633 1.0000
9.250 1.1101 0.02189 0.01373 -0.0260 0.0589 1.0000
9.500 1.1245 0.02267 0.01452 -0.0242 0.0550 1.0000
9.750 1.1400 0.02339 0.01535 -0.0224 0.0515 1.0000
10.000 1.1553 0.02412 0.01618 -0.0208 0.0478 1.0000
10.250 1.1677 0.02502 0.01710 -0.0188 0.0447 1.0000
10.500 1.1806 0.02596 0.01815 -0.0169 0.0422 1.0000
10.750 1.1938 0.02687 0.01921 -0.0152 0.0397 1.0000
11.000 1.2059 0.02781 0.02024 -0.0134 0.0373 1.0000
11.250 1.2141 0.02904 0.02151 -0.0114 0.0353 1.0000
11.500 1.2246 0.03021 0.02282 -0.0096 0.0337 1.0000
11.750 1.2344 0.03144 0.02421 -0.0078 0.0322 1.0000
12.000 1.2431 0.03272 0.02562 -0.0061 0.0307 1.0000
12.250 1.2506 0.03410 0.02711 -0.0044 0.0296 1.0000
12.500 1.2558 0.03564 0.02875 -0.0028 0.0283 1.0000
12.750 1.2585 0.03754 0.03075 -0.0012 0.0273 1.0000
13.000 1.2638 0.03932 0.03273 0.0002 0.0264 1.0000
13.250 1.2672 0.04130 0.03489 0.0015 0.0255 1.0000
13.500 1.2691 0.04346 0.03723 0.0025 0.0247 1.0000
13.750 1.2700 0.04577 0.03969 0.0034 0.0239 1.0000
14.000 1.2698 0.04824 0.04231 0.0039 0.0233 1.0000
14.250 1.2678 0.05100 0.04519 0.0041 0.0225 1.0000
14.500 1.2640 0.05413 0.04844 0.0040 0.0220 1.0000
14.750 1.2572 0.05783 0.05226 0.0036 0.0216 1.0000
15.000 1.2499 0.06185 0.05646 0.0028 0.0212 1.0000
15.250 1.2414 0.06630 0.06114 0.0014 0.0208 1.0000
15.500 1.2309 0.07132 0.06638 -0.0005 0.0205 1.0000
15.750 1.2185 0.07695 0.07221 -0.0031 0.0203 1.0000
16.000 1.2044 0.08322 0.07869 -0.0063 0.0201 1.0000
16.250 1.1880 0.09026 0.08593 -0.0102 0.0199 1.0000
16.500 1.1695 0.09809 0.09395 -0.0147 0.0198 1.0000
16.750 1.1481 0.10693 0.10299 -0.0200 0.0198 1.0000
17.000 1.1236 0.11684 0.11309 -0.0260 0.0199 1.0000
17.250 1.0926 0.12888 0.12531 -0.0334 0.0200 1.0000
17.500 1.0495 0.14484 0.14144 -0.0432 0.0204 1.0000
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