SG6041 (sg6041-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: SG6041 (sg6041-il) Reynolds number: 50,000 Max Cl/Cd: 35.08 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sg6041-il-50000-n5.txt Download as CSV file: xf-sg6041-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4495 0.09485 0.08768 -0.0421 1.0000 0.0455
-9.000 -0.4522 0.09096 0.08387 -0.0430 1.0000 0.0453
-8.750 -0.4583 0.08688 0.07987 -0.0444 1.0000 0.0451
-8.500 -0.4648 0.08333 0.07640 -0.0449 1.0000 0.0446
-8.250 -0.4765 0.07999 0.07315 -0.0448 1.0000 0.0442
-8.000 -0.4868 0.07666 0.06987 -0.0442 1.0000 0.0437
-7.750 -0.4978 0.07316 0.06639 -0.0436 1.0000 0.0434
-7.500 -0.5076 0.06976 0.06296 -0.0426 1.0000 0.0431
-7.250 -0.5158 0.06633 0.05947 -0.0414 1.0000 0.0428
-7.000 -0.5218 0.06289 0.05592 -0.0400 1.0000 0.0425
-6.750 -0.5252 0.05944 0.05230 -0.0384 1.0000 0.0422
-6.500 -0.5259 0.05590 0.04854 -0.0369 1.0000 0.0418
-6.250 -0.5238 0.05230 0.04465 -0.0353 1.0000 0.0416
-6.000 -0.5181 0.04888 0.04089 -0.0338 1.0000 0.0415
-5.750 -0.5092 0.04560 0.03721 -0.0323 1.0000 0.0416
-5.500 -0.4975 0.04242 0.03359 -0.0308 1.0000 0.0420
-5.250 -0.4829 0.03957 0.03027 -0.0293 1.0000 0.0430
-5.000 -0.4656 0.03691 0.02698 -0.0279 1.0000 0.0452
-4.750 -0.4480 0.03475 0.02459 -0.0268 1.0000 0.0478
-4.500 -0.4285 0.03291 0.02251 -0.0256 1.0000 0.0502
-4.250 -0.4071 0.03111 0.02036 -0.0244 1.0000 0.0536
-4.000 -0.3851 0.02953 0.01843 -0.0231 1.0000 0.0586
-3.750 -0.3636 0.02821 0.01704 -0.0220 1.0000 0.0641
-3.500 -0.3414 0.02701 0.01566 -0.0207 1.0000 0.0726
-3.250 -0.3199 0.02604 0.01453 -0.0193 1.0000 0.0834
-3.000 -0.2988 0.02508 0.01356 -0.0182 1.0000 0.0992
-2.750 -0.2779 0.02417 0.01268 -0.0173 1.0000 0.1214
-2.500 -0.2573 0.02325 0.01186 -0.0164 1.0000 0.1565
-2.250 -0.2368 0.02191 0.01113 -0.0159 1.0000 0.2435
-2.000 -0.2289 0.02001 0.01133 -0.0116 1.0000 0.6368
-1.750 -0.2082 0.02005 0.01165 -0.0080 0.9947 0.8321
-1.500 -0.1231 0.02035 0.01165 -0.0172 0.9961 1.0000
-1.250 -0.0891 0.02054 0.01149 -0.0196 0.9879 1.0000
-1.000 -0.0557 0.02076 0.01139 -0.0217 0.9798 1.0000
-0.750 -0.0199 0.02105 0.01141 -0.0242 0.9720 1.0000
-0.500 0.0113 0.02125 0.01136 -0.0257 0.9627 1.0000
-0.250 0.0457 0.02152 0.01143 -0.0277 0.9541 1.0000
0.000 0.0810 0.02180 0.01152 -0.0299 0.9452 1.0000
0.250 0.1124 0.02202 0.01159 -0.0312 0.9350 1.0000
0.500 0.1481 0.02228 0.01173 -0.0332 0.9259 1.0000
0.750 0.1835 0.02251 0.01187 -0.0351 0.9159 1.0000
1.000 0.2145 0.02272 0.01199 -0.0361 0.9045 1.0000
1.250 0.2485 0.02291 0.01213 -0.0375 0.8935 1.0000
1.500 0.2896 0.02305 0.01225 -0.0402 0.8840 1.0000
1.750 0.3212 0.02316 0.01235 -0.0410 0.8710 1.0000
2.000 0.3531 0.02324 0.01244 -0.0417 0.8577 1.0000
2.250 0.3863 0.02327 0.01249 -0.0426 0.8441 1.0000
2.500 0.4203 0.02322 0.01250 -0.0434 0.8299 1.0000
2.750 0.4541 0.02312 0.01246 -0.0440 0.8149 1.0000
3.000 0.4870 0.02295 0.01236 -0.0443 0.7989 1.0000
3.250 0.5202 0.02270 0.01222 -0.0445 0.7820 1.0000
3.500 0.5496 0.02247 0.01207 -0.0440 0.7625 1.0000
3.750 0.5779 0.02222 0.01191 -0.0431 0.7406 1.0000
4.000 0.6076 0.02191 0.01172 -0.0424 0.7171 1.0000
4.250 0.6382 0.02159 0.01147 -0.0418 0.6908 1.0000
4.500 0.6655 0.02141 0.01134 -0.0406 0.6590 1.0000
4.750 0.6935 0.02127 0.01123 -0.0396 0.6224 1.0000
5.000 0.7205 0.02126 0.01116 -0.0384 0.5803 1.0000
5.250 0.7450 0.02144 0.01120 -0.0370 0.5334 1.0000
5.500 0.7666 0.02185 0.01144 -0.0353 0.4848 1.0000
5.750 0.7854 0.02245 0.01183 -0.0334 0.4369 1.0000
6.000 0.8026 0.02320 0.01236 -0.0315 0.3922 1.0000
6.250 0.8191 0.02404 0.01302 -0.0296 0.3511 1.0000
6.500 0.8357 0.02496 0.01378 -0.0279 0.3150 1.0000
6.750 0.8524 0.02592 0.01464 -0.0263 0.2829 1.0000
7.000 0.8698 0.02694 0.01555 -0.0249 0.2557 1.0000
7.250 0.8876 0.02798 0.01652 -0.0236 0.2320 1.0000
7.500 0.9071 0.02906 0.01759 -0.0226 0.2113 1.0000
7.750 0.9266 0.03017 0.01874 -0.0216 0.1926 1.0000
8.000 0.9470 0.03134 0.01994 -0.0207 0.1770 1.0000
8.250 0.9680 0.03258 0.02124 -0.0199 0.1634 1.0000
8.500 0.9879 0.03385 0.02259 -0.0190 0.1506 1.0000
8.750 1.0093 0.03526 0.02411 -0.0183 0.1403 1.0000
9.000 1.0291 0.03666 0.02552 -0.0175 0.1308 1.0000
9.250 1.0470 0.03821 0.02735 -0.0164 0.1212 1.0000
9.500 1.0662 0.03991 0.02917 -0.0156 0.1138 1.0000
9.750 1.0813 0.04154 0.03100 -0.0143 0.1062 1.0000
10.000 1.0963 0.04347 0.03317 -0.0131 0.0998 1.0000
10.250 1.1086 0.04545 0.03542 -0.0116 0.0940 1.0000
10.500 1.1216 0.04731 0.03732 -0.0104 0.0890 1.0000
10.750 1.1256 0.04999 0.04049 -0.0082 0.0847 1.0000
11.000 1.1304 0.05240 0.04316 -0.0062 0.0813 1.0000
11.250 1.1400 0.05431 0.04508 -0.0048 0.0779 1.0000
11.500 1.1320 0.05740 0.04854 -0.0021 0.0757 1.0000
11.750 1.1184 0.06084 0.05237 0.0005 0.0739 1.0000
12.000 1.1035 0.06453 0.05638 0.0023 0.0724 1.0000
12.250 1.0860 0.06869 0.06080 0.0033 0.0714 1.0000
12.500 1.0641 0.07361 0.06597 0.0033 0.0708 1.0000
12.750 1.0351 0.07990 0.07250 0.0016 0.0709 1.0000
13.000 0.9952 0.08884 0.08163 -0.0028 0.0719 1.0000
13.250 0.9492 0.10119 0.09408 -0.0105 0.0738 1.0000
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