SG6051 (sg6051-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: SG6051 (sg6051-il) Reynolds number: 100,000 Max Cl/Cd: 57.11 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sg6051-il-100000-n5.txt Download as CSV file: xf-sg6051-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SG6051
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4177 0.09411 0.08925 -0.0472 1.0000 0.0243
-9.500 -0.4234 0.08929 0.08451 -0.0495 1.0000 0.0241
-9.250 -0.4334 0.08459 0.07991 -0.0513 1.0000 0.0240
-9.000 -0.4518 0.08085 0.07629 -0.0512 1.0000 0.0238
-8.750 -0.4799 0.07845 0.07402 -0.0487 1.0000 0.0235
-8.500 -0.4870 0.06695 0.06244 -0.0620 0.9881 0.0230
-8.250 -0.4914 0.05710 0.05225 -0.0702 0.9783 0.0227
-8.000 -0.4862 0.04891 0.04353 -0.0756 0.9717 0.0230
-7.750 -0.4771 0.04279 0.03680 -0.0777 0.9638 0.0236
-7.500 -0.4597 0.03664 0.02969 -0.0797 0.9589 0.0257
-7.250 -0.4363 0.03465 0.02742 -0.0807 0.9532 0.0278
-7.000 -0.4103 0.03253 0.02492 -0.0816 0.9481 0.0306
-6.750 -0.3820 0.02961 0.02137 -0.0827 0.9444 0.0345
-6.500 -0.3555 0.02874 0.02037 -0.0833 0.9389 0.0388
-6.250 -0.3279 0.02717 0.01842 -0.0838 0.9339 0.0443
-6.000 -0.2974 0.02620 0.01726 -0.0849 0.9301 0.0499
-5.750 -0.2692 0.02490 0.01562 -0.0851 0.9253 0.0546
-5.500 -0.2423 0.02398 0.01468 -0.0855 0.9198 0.0594
-5.250 -0.2119 0.02299 0.01349 -0.0861 0.9159 0.0639
-5.000 -0.1832 0.02210 0.01249 -0.0865 0.9117 0.0689
-4.750 -0.1577 0.02144 0.01180 -0.0863 0.9057 0.0737
-4.500 -0.1285 0.02081 0.01102 -0.0866 0.9014 0.0793
-4.250 -0.1002 0.02015 0.01038 -0.0870 0.8973 0.0869
-4.000 -0.0751 0.01971 0.00984 -0.0867 0.8910 0.0946
-3.750 -0.0466 0.01919 0.00928 -0.0870 0.8865 0.1074
-3.500 -0.0182 0.01861 0.00880 -0.0874 0.8824 0.1300
-3.250 0.0066 0.01807 0.00843 -0.0872 0.8760 0.1754
-3.000 0.0324 0.01711 0.00823 -0.0874 0.8716 0.3367
-2.750 0.0601 0.01676 0.00808 -0.0875 0.8676 0.4414
-2.500 0.0841 0.01655 0.00807 -0.0868 0.8611 0.5066
-2.250 0.1099 0.01623 0.00799 -0.0863 0.8566 0.5822
-2.000 0.1344 0.01588 0.00796 -0.0850 0.8527 0.6768
-1.750 0.1533 0.01568 0.00816 -0.0822 0.8461 0.7994
-1.500 0.1932 0.01556 0.00815 -0.0835 0.8425 0.9319
-1.250 0.2431 0.01552 0.00794 -0.0880 0.8396 0.9859
-1.000 0.2765 0.01559 0.00786 -0.0897 0.8338 1.0000
-0.750 0.3006 0.01566 0.00779 -0.0892 0.8280 1.0000
-0.500 0.3272 0.01566 0.00764 -0.0890 0.8239 1.0000
-0.250 0.3501 0.01586 0.00775 -0.0885 0.8166 1.0000
0.000 0.3764 0.01592 0.00770 -0.0883 0.8115 1.0000
0.250 0.4026 0.01601 0.00769 -0.0881 0.8064 1.0000
0.500 0.4273 0.01618 0.00780 -0.0877 0.7995 1.0000
0.750 0.4550 0.01620 0.00775 -0.0876 0.7950 1.0000
1.000 0.4797 0.01641 0.00792 -0.0873 0.7880 1.0000
1.250 0.5065 0.01650 0.00796 -0.0871 0.7824 1.0000
1.500 0.5340 0.01656 0.00799 -0.0871 0.7775 1.0000
1.750 0.5587 0.01679 0.00822 -0.0867 0.7701 1.0000
2.000 0.5870 0.01681 0.00821 -0.0867 0.7654 1.0000
2.250 0.6117 0.01704 0.00848 -0.0864 0.7577 1.0000
2.500 0.6394 0.01708 0.00852 -0.0863 0.7519 1.0000
2.750 0.6651 0.01724 0.00871 -0.0860 0.7445 1.0000
3.000 0.6924 0.01729 0.00879 -0.0858 0.7377 1.0000
3.250 0.7183 0.01742 0.00896 -0.0855 0.7298 1.0000
3.500 0.7458 0.01744 0.00901 -0.0853 0.7225 1.0000
3.750 0.7712 0.01757 0.00921 -0.0848 0.7132 1.0000
4.000 0.8000 0.01747 0.00915 -0.0847 0.7057 1.0000
4.250 0.8245 0.01762 0.00939 -0.0841 0.6943 1.0000
4.500 0.8501 0.01769 0.00954 -0.0835 0.6832 1.0000
4.750 0.8764 0.01769 0.00963 -0.0831 0.6717 1.0000
5.000 0.9026 0.01769 0.00969 -0.0825 0.6590 1.0000
5.250 0.9280 0.01772 0.00980 -0.0818 0.6443 1.0000
5.500 0.9525 0.01779 0.00997 -0.0810 0.6273 1.0000
5.750 0.9770 0.01785 0.01011 -0.0802 0.6079 1.0000
6.000 1.0011 0.01792 0.01022 -0.0792 0.5858 1.0000
6.250 1.0240 0.01805 0.01037 -0.0781 0.5585 1.0000
6.500 1.0451 0.01830 0.01062 -0.0767 0.5242 1.0000
6.750 1.0648 0.01866 0.01087 -0.0750 0.4819 1.0000
7.000 1.0815 0.01924 0.01125 -0.0730 0.4308 1.0000
7.250 1.0942 0.02011 0.01183 -0.0705 0.3727 1.0000
7.500 1.1033 0.02123 0.01264 -0.0676 0.3144 1.0000
7.750 1.1105 0.02248 0.01360 -0.0647 0.2609 1.0000
8.000 1.1172 0.02377 0.01464 -0.0618 0.2146 1.0000
8.250 1.1230 0.02506 0.01573 -0.0588 0.1767 1.0000
8.500 1.1282 0.02634 0.01687 -0.0558 0.1461 1.0000
8.750 1.1343 0.02771 0.01813 -0.0530 0.1220 1.0000
9.000 1.1414 0.02910 0.01949 -0.0506 0.1032 1.0000
9.250 1.1482 0.03057 0.02092 -0.0483 0.0888 1.0000
9.500 1.1552 0.03208 0.02245 -0.0461 0.0780 1.0000
9.750 1.1608 0.03375 0.02410 -0.0439 0.0706 1.0000
10.000 1.1686 0.03530 0.02575 -0.0420 0.0636 1.0000
10.250 1.1738 0.03708 0.02756 -0.0400 0.0583 1.0000
10.500 1.1818 0.03871 0.02933 -0.0383 0.0533 1.0000
10.750 1.1861 0.04067 0.03131 -0.0365 0.0494 1.0000
11.000 1.1945 0.04237 0.03318 -0.0350 0.0454 1.0000
11.250 1.2016 0.04419 0.03510 -0.0335 0.0419 1.0000
11.500 1.2052 0.04636 0.03728 -0.0320 0.0392 1.0000
11.750 1.2140 0.04823 0.03935 -0.0306 0.0365 1.0000
12.000 1.2210 0.05024 0.04151 -0.0293 0.0340 1.0000
12.250 1.2258 0.05239 0.04374 -0.0282 0.0319 1.0000
12.500 1.2302 0.05478 0.04618 -0.0269 0.0302 1.0000
12.750 1.2376 0.05710 0.04880 -0.0257 0.0287 1.0000
13.000 1.2435 0.05962 0.05154 -0.0245 0.0273 1.0000
13.250 1.2469 0.06228 0.05439 -0.0235 0.0262 1.0000
13.500 1.2484 0.06503 0.05729 -0.0227 0.0251 1.0000
13.750 1.2487 0.06791 0.06026 -0.0221 0.0242 1.0000
14.000 1.2473 0.07126 0.06374 -0.0215 0.0234 1.0000
14.250 1.2413 0.07518 0.06800 -0.0212 0.0227 1.0000
14.500 1.2333 0.07946 0.07259 -0.0212 0.0221 1.0000
14.750 1.2235 0.08414 0.07756 -0.0216 0.0217 1.0000
15.000 1.2114 0.08931 0.08301 -0.0225 0.0214 1.0000
15.250 1.1973 0.09502 0.08899 -0.0240 0.0211 1.0000
15.500 1.1810 0.10140 0.09562 -0.0263 0.0210 1.0000
15.750 1.1626 0.10855 0.10303 -0.0295 0.0209 1.0000
16.000 1.1418 0.11670 0.11143 -0.0338 0.0210 1.0000
16.250 1.1183 0.12618 0.12115 -0.0395 0.0211 1.0000
16.500 1.0909 0.13773 0.13291 -0.0469 0.0215 1.0000
16.750 1.0588 0.15221 0.14755 -0.0565 0.0220 1.0000
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