SD8000-089-88 (sd8000-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: SD8000-089-88 (sd8000-il) Reynolds number: 50,000 Max Cl/Cd: 34.55 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sd8000-il-50000-n5.txt Download as CSV file: xf-sd8000-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SD8000-089-88
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5130 0.09590 0.08868 -0.0220 1.0000 0.0525
-9.250 -0.5163 0.09105 0.08390 -0.0246 1.0000 0.0527
-9.000 -0.5215 0.08590 0.07884 -0.0276 1.0000 0.0531
-8.750 -0.5284 0.08053 0.07355 -0.0310 1.0000 0.0529
-8.500 -0.5398 0.07429 0.06740 -0.0358 1.0000 0.0527
-8.250 -0.5514 0.06814 0.06124 -0.0399 1.0000 0.0524
-8.000 -0.5615 0.06245 0.05544 -0.0428 1.0000 0.0525
-7.750 -0.5682 0.05711 0.04989 -0.0447 1.0000 0.0531
-7.500 -0.5714 0.05189 0.04430 -0.0457 1.0000 0.0542
-7.250 -0.5701 0.04689 0.03877 -0.0459 1.0000 0.0554
-7.000 -0.5633 0.04244 0.03374 -0.0454 1.0000 0.0567
-6.750 -0.5485 0.04066 0.03199 -0.0444 1.0000 0.0602
-6.500 -0.5342 0.03807 0.02903 -0.0435 1.0000 0.0649
-6.250 -0.5182 0.03468 0.02488 -0.0425 1.0000 0.0686
-6.000 -0.5004 0.03298 0.02319 -0.0415 1.0000 0.0735
-5.750 -0.4810 0.03100 0.02073 -0.0405 1.0000 0.0805
-5.500 -0.4612 0.02926 0.01887 -0.0394 1.0000 0.0862
-5.250 -0.4402 0.02780 0.01702 -0.0382 1.0000 0.0957
-5.000 -0.4199 0.02652 0.01577 -0.0371 1.0000 0.1039
-4.750 -0.3989 0.02538 0.01452 -0.0360 1.0000 0.1153
-4.500 -0.3774 0.02427 0.01326 -0.0349 1.0000 0.1271
-4.250 -0.3562 0.02336 0.01231 -0.0338 1.0000 0.1424
-4.000 -0.3347 0.02248 0.01139 -0.0328 1.0000 0.1593
-3.750 -0.3124 0.02169 0.01057 -0.0319 1.0000 0.1822
-3.500 -0.2908 0.02092 0.00984 -0.0310 1.0000 0.2086
-3.250 -0.2692 0.02018 0.00925 -0.0302 1.0000 0.2450
-3.000 -0.2477 0.01947 0.00876 -0.0295 1.0000 0.2961
-2.750 -0.2268 0.01878 0.00841 -0.0285 1.0000 0.3673
-2.500 -0.2071 0.01817 0.00822 -0.0271 1.0000 0.4583
-2.250 -0.1892 0.01769 0.00813 -0.0250 1.0000 0.5607
-2.000 -0.1733 0.01735 0.00814 -0.0221 1.0000 0.6605
-1.750 -0.1586 0.01710 0.00816 -0.0185 1.0000 0.7610
-1.500 -0.1312 0.01689 0.00811 -0.0173 1.0000 0.8876
-1.250 -0.0905 0.01677 0.00777 -0.0205 1.0000 1.0000
-1.000 -0.0710 0.01689 0.00764 -0.0199 1.0000 1.0000
-0.750 -0.0456 0.01709 0.00762 -0.0204 0.9975 1.0000
-0.500 -0.0027 0.01745 0.00774 -0.0241 0.9866 1.0000
-0.250 0.0395 0.01779 0.00790 -0.0276 0.9754 1.0000
0.000 0.0812 0.01810 0.00806 -0.0308 0.9634 1.0000
0.250 0.1228 0.01839 0.00824 -0.0339 0.9509 1.0000
0.500 0.1643 0.01864 0.00841 -0.0369 0.9378 1.0000
0.750 0.2058 0.01884 0.00856 -0.0397 0.9240 1.0000
1.000 0.2472 0.01899 0.00869 -0.0424 0.9096 1.0000
1.250 0.2876 0.01910 0.00880 -0.0446 0.8943 1.0000
1.500 0.3245 0.01916 0.00888 -0.0461 0.8776 1.0000
1.750 0.3603 0.01916 0.00891 -0.0472 0.8598 1.0000
2.000 0.3959 0.01911 0.00892 -0.0480 0.8415 1.0000
2.250 0.4276 0.01906 0.00891 -0.0480 0.8205 1.0000
2.500 0.4588 0.01897 0.00888 -0.0477 0.7982 1.0000
2.750 0.4881 0.01890 0.00888 -0.0471 0.7735 1.0000
3.000 0.5175 0.01882 0.00883 -0.0464 0.7475 1.0000
3.250 0.5456 0.01877 0.00881 -0.0454 0.7182 1.0000
3.500 0.5726 0.01878 0.00882 -0.0442 0.6855 1.0000
3.750 0.5990 0.01884 0.00887 -0.0429 0.6503 1.0000
4.000 0.6241 0.01902 0.00898 -0.0415 0.6115 1.0000
4.250 0.6484 0.01928 0.00914 -0.0400 0.5706 1.0000
4.500 0.6717 0.01966 0.00942 -0.0386 0.5281 1.0000
4.750 0.6941 0.02014 0.00976 -0.0371 0.4850 1.0000
5.000 0.7158 0.02072 0.01019 -0.0357 0.4421 1.0000
5.250 0.7371 0.02138 0.01073 -0.0344 0.4008 1.0000
5.500 0.7582 0.02212 0.01137 -0.0332 0.3623 1.0000
5.750 0.7793 0.02293 0.01207 -0.0321 0.3274 1.0000
6.000 0.8003 0.02380 0.01284 -0.0311 0.2956 1.0000
6.250 0.8217 0.02472 0.01371 -0.0301 0.2670 1.0000
6.500 0.8430 0.02568 0.01465 -0.0292 0.2405 1.0000
6.750 0.8644 0.02672 0.01569 -0.0284 0.2178 1.0000
7.000 0.8854 0.02779 0.01678 -0.0275 0.1967 1.0000
7.250 0.9061 0.02894 0.01789 -0.0266 0.1789 1.0000
7.500 0.9270 0.03015 0.01919 -0.0257 0.1617 1.0000
7.750 0.9474 0.03143 0.02061 -0.0248 0.1463 1.0000
8.000 0.9672 0.03282 0.02209 -0.0238 0.1325 1.0000
8.250 0.9864 0.03429 0.02363 -0.0228 0.1202 1.0000
8.500 1.0044 0.03579 0.02514 -0.0218 0.1091 1.0000
8.750 1.0218 0.03749 0.02713 -0.0207 0.0984 1.0000
9.000 1.0384 0.03946 0.02935 -0.0195 0.0893 1.0000
9.250 1.0539 0.04124 0.03114 -0.0185 0.0822 1.0000
9.500 1.0667 0.04361 0.03396 -0.0171 0.0751 1.0000
9.750 1.0810 0.04559 0.03586 -0.0161 0.0703 1.0000
10.000 1.0871 0.04867 0.03955 -0.0144 0.0656 1.0000
10.250 1.0937 0.05123 0.04237 -0.0130 0.0619 1.0000
10.500 1.1014 0.05379 0.04504 -0.0117 0.0595 1.0000
10.750 1.1005 0.05729 0.04883 -0.0102 0.0578 1.0000
11.000 1.0867 0.06119 0.05316 -0.0081 0.0567 1.0000
11.250 1.0696 0.06538 0.05767 -0.0069 0.0560 1.0000
11.500 1.0490 0.07019 0.06274 -0.0070 0.0557 1.0000
11.750 1.0255 0.07593 0.06872 -0.0087 0.0559 1.0000
12.000 0.9988 0.08305 0.07602 -0.0124 0.0563 1.0000
12.250 0.9706 0.09174 0.08482 -0.0180 0.0570 1.0000
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Polar data table (+)
Polar graphs
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