SG6041 (sg6041-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: SG6041 (sg6041-il) Reynolds number: 100,000 Max Cl/Cd: 49.77 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sg6041-il-100000-n5.txt Download as CSV file: xf-sg6041-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4378 0.09073 0.08561 -0.0389 1.0000 0.0261
-9.000 -0.4428 0.08668 0.08163 -0.0400 1.0000 0.0255
-8.750 -0.4511 0.08230 0.07734 -0.0415 1.0000 0.0249
-8.500 -0.4628 0.07783 0.07296 -0.0434 1.0000 0.0243
-8.250 -0.4846 0.07325 0.06847 -0.0449 1.0000 0.0238
-7.750 -0.5397 0.06147 0.05645 -0.0437 1.0000 0.0218
-7.500 -0.5484 0.05854 0.05344 -0.0414 1.0000 0.0216
-7.250 -0.5555 0.05531 0.05009 -0.0392 1.0000 0.0215
-7.000 -0.5591 0.05209 0.04669 -0.0371 1.0000 0.0214
-6.750 -0.5601 0.04868 0.04306 -0.0350 1.0000 0.0212
-6.500 -0.5580 0.04516 0.03924 -0.0331 1.0000 0.0211
-6.250 -0.5473 0.04100 0.03464 -0.0324 0.9984 0.0211
-6.000 -0.5237 0.03673 0.02978 -0.0337 0.9944 0.0211
-5.750 -0.4997 0.03304 0.02548 -0.0342 0.9904 0.0213
-5.500 -0.4725 0.02985 0.02161 -0.0346 0.9869 0.0219
-5.250 -0.4432 0.02810 0.01966 -0.0358 0.9839 0.0231
-5.000 -0.4161 0.02687 0.01822 -0.0362 0.9796 0.0257
-4.750 -0.3861 0.02510 0.01602 -0.0365 0.9761 0.0276
-4.500 -0.3554 0.02350 0.01428 -0.0373 0.9731 0.0294
-4.250 -0.3261 0.02246 0.01314 -0.0378 0.9694 0.0327
-4.000 -0.2985 0.02149 0.01206 -0.0379 0.9648 0.0376
-3.750 -0.2678 0.02066 0.01117 -0.0386 0.9609 0.0444
-3.500 -0.2353 0.01983 0.01033 -0.0398 0.9578 0.0553
-3.250 -0.2106 0.01918 0.00964 -0.0394 0.9519 0.0697
-3.000 -0.1807 0.01851 0.00907 -0.0401 0.9473 0.0939
-2.750 -0.1477 0.01783 0.00858 -0.0415 0.9439 0.1358
-2.500 -0.1248 0.01699 0.00819 -0.0410 0.9374 0.2316
-2.250 -0.1023 0.01552 0.00808 -0.0405 0.9327 0.5345
-2.000 -0.0744 0.01524 0.00830 -0.0395 0.9290 0.7142
-1.750 -0.0543 0.01524 0.00834 -0.0372 0.9213 0.7759
-1.500 -0.0245 0.01523 0.00832 -0.0367 0.9166 0.8244
-1.250 0.0050 0.01528 0.00839 -0.0357 0.9120 0.8776
-1.000 0.0514 0.01548 0.00856 -0.0380 0.9090 0.9344
-0.750 0.1028 0.01553 0.00847 -0.0424 0.9057 0.9538
-0.250 0.1993 0.01535 0.00804 -0.0507 0.8985 0.9685
0.000 0.2395 0.01527 0.00790 -0.0535 0.8906 0.9766
0.250 0.2854 0.01509 0.00764 -0.0571 0.8856 0.9825
0.500 0.3255 0.01496 0.00747 -0.0597 0.8768 0.9904
0.750 0.3702 0.01471 0.00719 -0.0630 0.8702 0.9958
1.000 0.3994 0.01457 0.00703 -0.0634 0.8583 1.0000
1.250 0.4219 0.01441 0.00685 -0.0623 0.8457 1.0000
1.500 0.4453 0.01426 0.00668 -0.0613 0.8327 1.0000
1.750 0.4686 0.01411 0.00653 -0.0602 0.8188 1.0000
2.000 0.4911 0.01399 0.00639 -0.0589 0.8033 1.0000
2.250 0.5135 0.01388 0.00627 -0.0576 0.7862 1.0000
2.500 0.5379 0.01377 0.00613 -0.0565 0.7677 1.0000
2.750 0.5616 0.01369 0.00605 -0.0553 0.7468 1.0000
3.000 0.5869 0.01362 0.00594 -0.0544 0.7236 1.0000
3.250 0.6117 0.01359 0.00587 -0.0534 0.6965 1.0000
3.500 0.6372 0.01361 0.00583 -0.0525 0.6648 1.0000
3.750 0.6617 0.01371 0.00581 -0.0514 0.6278 1.0000
4.000 0.6851 0.01391 0.00584 -0.0502 0.5862 1.0000
4.250 0.7068 0.01421 0.00595 -0.0488 0.5413 1.0000
4.500 0.7271 0.01461 0.00616 -0.0472 0.4949 1.0000
4.750 0.7465 0.01508 0.00642 -0.0455 0.4490 1.0000
5.000 0.7651 0.01561 0.00674 -0.0439 0.4033 1.0000
5.250 0.7835 0.01620 0.00713 -0.0422 0.3604 1.0000
5.500 0.8017 0.01681 0.00756 -0.0406 0.3203 1.0000
5.750 0.8205 0.01743 0.00802 -0.0392 0.2848 1.0000
6.000 0.8394 0.01807 0.00853 -0.0378 0.2539 1.0000
6.250 0.8584 0.01872 0.00909 -0.0365 0.2275 1.0000
6.500 0.8775 0.01938 0.00967 -0.0352 0.2044 1.0000
6.750 0.8965 0.02006 0.01029 -0.0339 0.1850 1.0000
7.000 0.9157 0.02075 0.01096 -0.0327 0.1686 1.0000
7.250 0.9346 0.02146 0.01168 -0.0314 0.1538 1.0000
7.500 0.9531 0.02221 0.01241 -0.0301 0.1412 1.0000
7.750 0.9709 0.02302 0.01321 -0.0288 0.1306 1.0000
8.000 0.9898 0.02378 0.01405 -0.0275 0.1204 1.0000
8.250 1.0076 0.02462 0.01493 -0.0262 0.1115 1.0000
8.500 1.0241 0.02552 0.01584 -0.0247 0.1038 1.0000
8.750 1.0423 0.02639 0.01684 -0.0234 0.0960 1.0000
9.000 1.0574 0.02736 0.01778 -0.0219 0.0895 1.0000
9.250 1.0749 0.02826 0.01887 -0.0206 0.0828 1.0000
9.500 1.0881 0.02930 0.01992 -0.0188 0.0777 1.0000
9.750 1.1042 0.03038 0.02120 -0.0173 0.0725 1.0000
10.000 1.1172 0.03142 0.02232 -0.0155 0.0679 1.0000
10.250 1.1295 0.03269 0.02366 -0.0138 0.0641 1.0000
10.500 1.1430 0.03399 0.02518 -0.0121 0.0599 1.0000
10.750 1.1544 0.03532 0.02661 -0.0104 0.0568 1.0000
11.000 1.1641 0.03688 0.02820 -0.0087 0.0542 1.0000
11.250 1.1748 0.03851 0.03015 -0.0070 0.0513 1.0000
11.500 1.1827 0.04013 0.03198 -0.0051 0.0485 1.0000
11.750 1.1897 0.04184 0.03384 -0.0034 0.0466 1.0000
12.000 1.1957 0.04364 0.03572 -0.0018 0.0450 1.0000
12.250 1.2005 0.04590 0.03810 -0.0003 0.0435 1.0000
12.500 1.1997 0.04840 0.04098 0.0015 0.0420 1.0000
12.750 1.1968 0.05107 0.04395 0.0030 0.0405 1.0000
13.000 1.1924 0.05389 0.04703 0.0042 0.0392 1.0000
13.250 1.1868 0.05692 0.05028 0.0051 0.0382 1.0000
13.500 1.1797 0.06024 0.05380 0.0055 0.0375 1.0000
13.750 1.1710 0.06393 0.05771 0.0054 0.0369 1.0000
14.000 1.1609 0.06796 0.06192 0.0048 0.0364 1.0000
14.250 1.1507 0.07224 0.06634 0.0038 0.0358 1.0000
14.500 1.1362 0.07742 0.07170 0.0019 0.0355 1.0000
14.750 1.1184 0.08353 0.07800 -0.0009 0.0353 1.0000
15.000 1.0855 0.09300 0.08777 -0.0067 0.0356 1.0000
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Polar data table (+)
Polar graphs
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