SD2083 (9.0%) (sd2083-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD2083 (9.0%) (sd2083-il) Reynolds number: 50,000 Max Cl/Cd: 37.42 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd2083-il-50000.txt Download as CSV file: xf-sd2083-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: SD2083 (9.0%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3762 0.09629 0.08975 -0.0233 1.0000 0.2522
-7.750 -0.3863 0.09440 0.08801 -0.0229 1.0000 0.2620
-7.500 -0.3981 0.09315 0.08690 -0.0215 1.0000 0.2735
-7.250 -0.3918 0.08992 0.08370 -0.0196 1.0000 0.2867
-7.000 -0.3903 0.08716 0.08102 -0.0173 1.0000 0.2996
-6.750 -0.3932 0.08486 0.07882 -0.0147 1.0000 0.3114
-6.500 -0.4030 0.08302 0.07710 -0.0114 1.0000 0.3242
-6.250 -0.4122 0.08122 0.07541 -0.0083 1.0000 0.3376
-6.000 -0.4185 0.07923 0.07351 -0.0049 1.0000 0.3544
-5.750 -0.4305 0.07767 0.07206 -0.0015 1.0000 0.3725
-5.500 -0.4364 0.07550 0.06998 0.0022 1.0000 0.3929
-4.250 -0.4203 0.05330 0.04712 -0.0243 1.0000 0.2484
-4.000 -0.4279 0.05422 0.04847 -0.0130 1.0000 0.3252
-3.750 -0.3462 0.03930 0.03073 -0.0354 1.0000 0.1292
-3.500 -0.3240 0.03647 0.02756 -0.0350 1.0000 0.1259
-3.250 -0.2989 0.03380 0.02432 -0.0347 1.0000 0.1218
-3.000 -0.2733 0.03158 0.02157 -0.0341 1.0000 0.1205
-2.750 -0.2485 0.02981 0.01939 -0.0334 1.0000 0.1219
-2.500 -0.2240 0.02839 0.01762 -0.0326 1.0000 0.1280
-2.250 -0.2004 0.02710 0.01621 -0.0318 1.0000 0.1398
-2.000 -0.1758 0.02585 0.01485 -0.0308 1.0000 0.1549
-1.750 -0.1495 0.02452 0.01363 -0.0301 1.0000 0.1955
-1.500 -0.1091 0.01976 0.01204 -0.0297 1.0000 1.0000
-1.250 -0.0885 0.02003 0.01168 -0.0289 1.0000 1.0000
-1.000 -0.0685 0.02033 0.01154 -0.0282 1.0000 1.0000
-0.750 -0.0488 0.02067 0.01151 -0.0276 1.0000 1.0000
-0.500 -0.0291 0.02104 0.01157 -0.0270 1.0000 1.0000
-0.250 -0.0096 0.02145 0.01167 -0.0264 1.0000 1.0000
0.000 0.0098 0.02189 0.01187 -0.0259 1.0000 1.0000
0.250 0.0291 0.02237 0.01214 -0.0255 1.0000 1.0000
0.500 0.0481 0.02289 0.01247 -0.0250 1.0000 1.0000
0.750 0.0670 0.02344 0.01285 -0.0246 1.0000 1.0000
1.000 0.0856 0.02404 0.01330 -0.0243 1.0000 1.0000
1.250 0.1041 0.02468 0.01382 -0.0239 1.0000 1.0000
1.500 0.1222 0.02537 0.01440 -0.0237 1.0000 1.0000
1.750 0.1401 0.02611 0.01504 -0.0234 1.0000 1.0000
2.000 0.1729 0.02730 0.01616 -0.0262 0.9932 1.0000
2.250 0.2210 0.02883 0.01764 -0.0317 0.9765 1.0000
2.500 0.2691 0.03034 0.01912 -0.0370 0.9593 1.0000
2.750 0.3139 0.03168 0.02046 -0.0415 0.9411 1.0000
3.000 0.3532 0.03280 0.02161 -0.0447 0.9217 1.0000
3.250 0.4000 0.03397 0.02287 -0.0490 0.9023 1.0000
3.500 0.4358 0.03487 0.02385 -0.0511 0.8812 1.0000
3.750 0.4813 0.03571 0.02481 -0.0545 0.8602 1.0000
4.000 0.5168 0.03639 0.02564 -0.0560 0.8376 1.0000
4.250 0.5682 0.03677 0.02621 -0.0594 0.8162 1.0000
4.500 0.6007 0.03713 0.02673 -0.0599 0.7919 1.0000
4.750 0.6433 0.03713 0.02700 -0.0613 0.7684 1.0000
5.000 0.7007 0.03632 0.02650 -0.0637 0.7459 1.0000
5.250 0.7419 0.03564 0.02609 -0.0638 0.7202 1.0000
5.500 0.7866 0.03432 0.02512 -0.0633 0.6946 1.0000
5.750 0.8357 0.03231 0.02344 -0.0625 0.6676 1.0000
6.000 0.8849 0.02993 0.02136 -0.0611 0.6362 1.0000
6.250 0.9255 0.02806 0.01971 -0.0588 0.5976 1.0000
6.500 0.9596 0.02684 0.01850 -0.0562 0.5514 1.0000
6.750 0.9855 0.02656 0.01810 -0.0533 0.5007 1.0000
7.000 1.0078 0.02693 0.01820 -0.0506 0.4486 1.0000
7.250 1.0246 0.02795 0.01908 -0.0478 0.3977 1.0000
7.500 1.0426 0.02922 0.02001 -0.0454 0.3484 1.0000
7.750 1.0565 0.03082 0.02145 -0.0428 0.3021 1.0000
8.000 1.0704 0.03260 0.02306 -0.0402 0.2584 1.0000
8.250 1.0833 0.03460 0.02486 -0.0377 0.2172 1.0000
8.500 1.0944 0.03674 0.02673 -0.0351 0.1782 1.0000
8.750 1.1002 0.03882 0.02883 -0.0321 0.1450 1.0000
9.000 1.1104 0.04140 0.03135 -0.0297 0.1189 1.0000
9.250 1.1259 0.04431 0.03426 -0.0281 0.1018 1.0000
9.500 1.1405 0.04823 0.03862 -0.0262 0.0939 1.0000
9.750 1.1608 0.05216 0.04250 -0.0256 0.0868 1.0000
10.000 1.1592 0.05577 0.04677 -0.0225 0.0843 1.0000
10.250 1.1555 0.05961 0.05113 -0.0197 0.0825 1.0000
10.500 1.1480 0.06356 0.05550 -0.0170 0.0814 1.0000
10.750 1.1352 0.06753 0.05982 -0.0144 0.0808 1.0000
11.000 1.1168 0.07143 0.06400 -0.0116 0.0811 1.0000
11.250 1.0958 0.07569 0.06849 -0.0098 0.0820 1.0000
11.500 1.0725 0.08044 0.07344 -0.0092 0.0828 1.0000
11.750 1.0490 0.08581 0.07896 -0.0097 0.0837 1.0000
12.000 1.0277 0.09171 0.08497 -0.0114 0.0848 1.0000
12.250 1.0090 0.09814 0.09147 -0.0137 0.0858 1.0000
12.500 0.9969 0.10467 0.09804 -0.0160 0.0865 1.0000
12.750 0.9006 0.13105 0.12428 -0.0382 0.1099 1.0000
13.000 0.9011 0.13737 0.13059 -0.0399 0.1117 1.0000
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Polar data table (+)
Polar graphs
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