SG6041 (sg6041-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: SG6041 (sg6041-il) Reynolds number: 1,000,000 Max Cl/Cd: 87.96 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sg6041-il-1000000-n5.txt Download as CSV file: xf-sg6041-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.6356 0.06184 0.06020 -0.0560 1.0000 0.0034
-10.500 -0.7754 0.03042 0.02762 -0.0669 0.9894 0.0032
-10.250 -0.7647 0.02583 0.02254 -0.0682 0.9856 0.0032
-10.000 -0.7498 0.02247 0.01875 -0.0686 0.9818 0.0033
-9.750 -0.7305 0.02021 0.01619 -0.0687 0.9773 0.0034
-9.500 -0.7054 0.01876 0.01453 -0.0693 0.9742 0.0034
-9.250 -0.6777 0.01765 0.01325 -0.0701 0.9719 0.0035
-9.000 -0.6551 0.01675 0.01222 -0.0696 0.9661 0.0036
-8.750 -0.6288 0.01594 0.01130 -0.0699 0.9617 0.0037
-8.500 -0.6015 0.01509 0.01033 -0.0703 0.9581 0.0038
-8.250 -0.5767 0.01452 0.00968 -0.0700 0.9523 0.0039
-8.000 -0.5509 0.01387 0.00891 -0.0699 0.9468 0.0041
-7.750 -0.5247 0.01329 0.00824 -0.0698 0.9420 0.0043
-7.500 -0.5001 0.01273 0.00759 -0.0694 0.9357 0.0044
-7.250 -0.4742 0.01225 0.00702 -0.0691 0.9301 0.0046
-7.000 -0.4492 0.01177 0.00645 -0.0687 0.9243 0.0047
-6.750 -0.4238 0.01136 0.00596 -0.0683 0.9184 0.0048
-6.500 -0.3980 0.01100 0.00552 -0.0680 0.9132 0.0049
-6.250 -0.3730 0.01056 0.00502 -0.0675 0.9073 0.0051
-6.000 -0.3477 0.01015 0.00453 -0.0670 0.9017 0.0054
-5.750 -0.3218 0.00983 0.00417 -0.0667 0.8967 0.0057
-5.500 -0.2958 0.00955 0.00385 -0.0664 0.8915 0.0061
-5.250 -0.2695 0.00930 0.00356 -0.0661 0.8865 0.0064
-5.000 -0.2430 0.00909 0.00331 -0.0658 0.8819 0.0071
-4.750 -0.2168 0.00882 0.00301 -0.0655 0.8765 0.0080
-4.500 -0.1902 0.00861 0.00278 -0.0652 0.8712 0.0093
-4.250 -0.1636 0.00840 0.00254 -0.0650 0.8662 0.0110
-4.000 -0.1369 0.00822 0.00234 -0.0647 0.8607 0.0131
-3.750 -0.1102 0.00804 0.00215 -0.0645 0.8555 0.0169
-3.500 -0.0834 0.00785 0.00199 -0.0643 0.8500 0.0233
-3.250 -0.0568 0.00767 0.00184 -0.0640 0.8437 0.0344
-3.000 -0.0300 0.00752 0.00171 -0.0638 0.8375 0.0447
-2.750 -0.0031 0.00737 0.00159 -0.0636 0.8305 0.0574
-2.500 0.0237 0.00724 0.00148 -0.0634 0.8237 0.0716
-2.250 0.0505 0.00707 0.00137 -0.0632 0.8156 0.0929
-2.000 0.0765 0.00684 0.00126 -0.0629 0.8071 0.1393
-1.750 0.1026 0.00662 0.00117 -0.0626 0.7971 0.1887
-1.500 0.1284 0.00636 0.00107 -0.0623 0.7866 0.2539
-1.000 0.1786 0.00579 0.00091 -0.0614 0.7583 0.4171
-0.750 0.2027 0.00546 0.00084 -0.0608 0.7416 0.5260
-0.500 0.2268 0.00524 0.00083 -0.0600 0.7231 0.6186
-0.250 0.2521 0.00522 0.00084 -0.0594 0.7006 0.6601
0.000 0.2769 0.00526 0.00087 -0.0587 0.6736 0.6991
0.250 0.3016 0.00533 0.00092 -0.0580 0.6452 0.7302
0.500 0.3266 0.00544 0.00096 -0.0573 0.6163 0.7502
0.750 0.3516 0.00557 0.00102 -0.0567 0.5854 0.7665
1.000 0.3764 0.00574 0.00108 -0.0560 0.5493 0.7794
1.250 0.4009 0.00596 0.00116 -0.0554 0.5096 0.7892
1.500 0.4254 0.00619 0.00124 -0.0547 0.4690 0.7965
1.750 0.4507 0.00639 0.00133 -0.0542 0.4370 0.8039
2.000 0.4759 0.00659 0.00142 -0.0537 0.4061 0.8109
2.250 0.5008 0.00681 0.00152 -0.0532 0.3717 0.8187
2.500 0.5261 0.00701 0.00162 -0.0527 0.3448 0.8262
2.750 0.5510 0.00722 0.00175 -0.0522 0.3156 0.8348
3.000 0.5751 0.00749 0.00189 -0.0515 0.2788 0.8435
3.500 0.6241 0.00795 0.00217 -0.0503 0.2253 0.8639
3.750 0.6486 0.00814 0.00232 -0.0497 0.2049 0.8755
4.250 0.6967 0.00853 0.00263 -0.0483 0.1690 0.9044
4.500 0.7206 0.00870 0.00280 -0.0475 0.1541 0.9243
4.750 0.7472 0.00888 0.00297 -0.0473 0.1415 0.9479
5.000 0.7810 0.00912 0.00318 -0.0488 0.1285 0.9708
5.250 0.8161 0.00939 0.00340 -0.0506 0.1163 0.9919
5.500 0.8436 0.00964 0.00360 -0.0508 0.1058 1.0000
5.750 0.8676 0.00987 0.00380 -0.0501 0.0971 1.0000
6.000 0.8911 0.01014 0.00402 -0.0494 0.0873 1.0000
6.250 0.9145 0.01044 0.00426 -0.0487 0.0772 1.0000
6.500 0.9384 0.01069 0.00449 -0.0481 0.0705 1.0000
6.750 0.9620 0.01097 0.00474 -0.0474 0.0646 1.0000
7.000 0.9860 0.01121 0.00499 -0.0468 0.0604 1.0000
7.250 1.0093 0.01152 0.00527 -0.0461 0.0553 1.0000
7.500 1.0331 0.01178 0.00553 -0.0454 0.0520 1.0000
7.750 1.0563 0.01207 0.00583 -0.0447 0.0480 1.0000
8.000 1.0791 0.01241 0.00615 -0.0440 0.0439 1.0000
8.250 1.1024 0.01268 0.00645 -0.0433 0.0418 1.0000
8.500 1.1250 0.01301 0.00678 -0.0425 0.0383 1.0000
8.750 1.1469 0.01338 0.00715 -0.0416 0.0344 1.0000
9.000 1.1691 0.01371 0.00750 -0.0408 0.0318 1.0000
9.250 1.1902 0.01413 0.00790 -0.0398 0.0283 1.0000
9.500 1.2116 0.01451 0.00830 -0.0388 0.0261 1.0000
9.750 1.2321 0.01493 0.00873 -0.0377 0.0235 1.0000
10.000 1.2519 0.01540 0.00921 -0.0366 0.0213 1.0000
10.250 1.2721 0.01580 0.00965 -0.0354 0.0203 1.0000
10.500 1.2911 0.01624 0.01013 -0.0341 0.0191 1.0000
10.750 1.3082 0.01672 0.01062 -0.0325 0.0178 1.0000
11.000 1.3239 0.01726 0.01120 -0.0306 0.0166 1.0000
11.250 1.3404 0.01772 0.01172 -0.0289 0.0161 1.0000
11.500 1.3568 0.01820 0.01227 -0.0272 0.0156 1.0000
11.750 1.3725 0.01871 0.01283 -0.0255 0.0149 1.0000
12.000 1.3874 0.01929 0.01344 -0.0237 0.0139 1.0000
12.250 1.4011 0.01994 0.01413 -0.0218 0.0131 1.0000
12.500 1.4137 0.02067 0.01491 -0.0198 0.0124 1.0000
12.750 1.4281 0.02127 0.01558 -0.0182 0.0120 1.0000
13.000 1.4418 0.02192 0.01630 -0.0165 0.0114 1.0000
13.250 1.4544 0.02265 0.01709 -0.0148 0.0107 1.0000
13.500 1.4655 0.02348 0.01797 -0.0130 0.0100 1.0000
13.750 1.4755 0.02442 0.01896 -0.0111 0.0095 1.0000
14.000 1.4859 0.02534 0.01996 -0.0094 0.0091 1.0000
14.250 1.4958 0.02632 0.02101 -0.0077 0.0086 1.0000
14.500 1.5046 0.02739 0.02216 -0.0061 0.0083 1.0000
14.750 1.5124 0.02858 0.02343 -0.0045 0.0079 1.0000
15.000 1.5187 0.02991 0.02482 -0.0029 0.0073 1.0000
15.250 1.5241 0.03138 0.02636 -0.0014 0.0070 1.0000
15.500 1.5289 0.03293 0.02801 -0.0001 0.0065 1.0000
15.750 1.5328 0.03463 0.02980 0.0012 0.0064 1.0000
16.000 1.5358 0.03648 0.03176 0.0022 0.0062 1.0000
16.250 1.5373 0.03855 0.03391 0.0031 0.0057 1.0000
16.500 1.5369 0.04091 0.03637 0.0038 0.0055 1.0000
16.750 1.5344 0.04364 0.03918 0.0042 0.0050 1.0000
17.000 1.5308 0.04664 0.04229 0.0042 0.0048 1.0000
17.250 1.5259 0.04998 0.04576 0.0039 0.0048 1.0000
17.500 1.5206 0.05360 0.04950 0.0032 0.0046 1.0000
17.750 1.5127 0.05780 0.05382 0.0020 0.0045 1.0000
18.000 1.5024 0.06259 0.05875 0.0003 0.0044 1.0000
18.250 1.4886 0.06824 0.06454 -0.0022 0.0043 1.0000
18.500 1.4727 0.07453 0.07098 -0.0052 0.0042 1.0000
18.750 1.4518 0.08202 0.07863 -0.0091 0.0041 1.0000
19.000 1.4260 0.09077 0.08755 -0.0139 0.0041 1.0000
19.250 1.3947 0.10091 0.09786 -0.0196 0.0042 1.0000
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Polar data table (+)
Polar graphs
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