SD2083 (9.0%) (sd2083-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD2083 (9.0%) (sd2083-il) Reynolds number: 200,000 Max Cl/Cd: 80.3 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd2083-il-200000.txt Download as CSV file: xf-sd2083-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3904 0.08798 0.08464 -0.0399 1.0000 0.0472
-8.250 -0.4013 0.08532 0.08208 -0.0421 1.0000 0.0476
-8.000 -0.4206 0.08358 0.08045 -0.0406 1.0000 0.0477
-7.750 -0.4424 0.08176 0.07869 -0.0393 1.0000 0.0478
-7.500 -0.4590 0.07950 0.07644 -0.0383 1.0000 0.0479
-7.250 -0.3909 0.06697 0.06423 -0.0291 0.9982 0.0517
-7.000 -0.4654 0.07250 0.06921 -0.0423 0.9970 0.0483
-6.750 -0.4554 0.06570 0.06258 -0.0431 0.9945 0.0499
-6.500 -0.4358 0.06406 0.06097 -0.0426 0.9911 0.0532
-6.250 -0.4097 0.05873 0.05548 -0.0496 0.9859 0.0573
-6.000 -0.3859 0.05083 0.04695 -0.0587 0.9781 0.0624
-5.750 -0.3618 0.04742 0.04362 -0.0604 0.9745 0.0643
-5.500 -0.3317 0.04421 0.04029 -0.0635 0.9714 0.0681
-5.250 -0.3101 0.04003 0.03551 -0.0657 0.9639 0.0765
-5.000 -0.2814 0.03712 0.03260 -0.0676 0.9605 0.0796
-4.750 -0.2480 0.03404 0.02907 -0.0705 0.9575 0.0912
-4.500 -0.2234 0.02556 0.01938 -0.0676 0.9510 0.0425
-4.250 -0.1905 0.02332 0.01672 -0.0686 0.9474 0.0429
-4.000 -0.1536 0.02065 0.01348 -0.0697 0.9451 0.0399
-3.750 -0.1142 0.01890 0.01143 -0.0716 0.9435 0.0393
-3.500 -0.0913 0.01793 0.01035 -0.0705 0.9365 0.0398
-3.250 -0.0559 0.01689 0.00925 -0.0719 0.9333 0.0414
-3.000 -0.0195 0.01603 0.00835 -0.0735 0.9306 0.0450
-2.750 0.0058 0.01544 0.00773 -0.0730 0.9246 0.0507
-2.500 0.0357 0.01472 0.00701 -0.0733 0.9196 0.0648
-2.250 0.0648 0.01320 0.00640 -0.0739 0.9162 0.2664
-2.000 0.0812 0.01238 0.00642 -0.0721 0.9085 0.4908
-1.750 0.1002 0.01139 0.00652 -0.0693 0.9039 0.7761
-1.500 0.2033 0.01099 0.00625 -0.0834 0.9098 0.9793
-1.250 0.2654 0.01081 0.00588 -0.0905 0.9085 1.0000
-1.000 0.2920 0.01073 0.00568 -0.0901 0.9024 1.0000
-0.750 0.3116 0.01079 0.00565 -0.0885 0.8933 1.0000
-0.500 0.3376 0.01071 0.00545 -0.0878 0.8875 1.0000
-0.250 0.3572 0.01078 0.00544 -0.0861 0.8779 1.0000
0.000 0.3822 0.01069 0.00527 -0.0851 0.8717 1.0000
0.250 0.4031 0.01072 0.00525 -0.0836 0.8621 1.0000
0.500 0.4260 0.01070 0.00516 -0.0823 0.8541 1.0000
0.750 0.4497 0.01062 0.00502 -0.0810 0.8460 1.0000
1.000 0.4720 0.01062 0.00498 -0.0796 0.8364 1.0000
1.250 0.4968 0.01050 0.00480 -0.0784 0.8290 1.0000
1.500 0.5197 0.01047 0.00475 -0.0771 0.8186 1.0000
1.750 0.5431 0.01044 0.00470 -0.0759 0.8085 1.0000
2.000 0.5680 0.01036 0.00458 -0.0748 0.7996 1.0000
2.250 0.5923 0.01031 0.00451 -0.0738 0.7892 1.0000
2.500 0.6163 0.01030 0.00452 -0.0727 0.7779 1.0000
2.750 0.6410 0.01028 0.00450 -0.0718 0.7667 1.0000
3.000 0.6659 0.01025 0.00446 -0.0708 0.7550 1.0000
3.250 0.6908 0.01022 0.00443 -0.0699 0.7420 1.0000
3.500 0.7155 0.01021 0.00444 -0.0689 0.7273 1.0000
3.750 0.7399 0.01021 0.00445 -0.0679 0.7106 1.0000
4.000 0.7645 0.01022 0.00446 -0.0669 0.6921 1.0000
4.250 0.7888 0.01027 0.00449 -0.0659 0.6710 1.0000
4.500 0.8127 0.01035 0.00453 -0.0648 0.6465 1.0000
4.750 0.8360 0.01048 0.00465 -0.0636 0.6175 1.0000
5.000 0.8584 0.01069 0.00480 -0.0624 0.5826 1.0000
5.250 0.8800 0.01099 0.00498 -0.0610 0.5418 1.0000
5.500 0.9001 0.01142 0.00523 -0.0594 0.4945 1.0000
5.750 0.9188 0.01197 0.00559 -0.0577 0.4439 1.0000
6.000 0.9367 0.01262 0.00601 -0.0560 0.3939 1.0000
6.250 0.9544 0.01330 0.00650 -0.0544 0.3491 1.0000
6.500 0.9726 0.01398 0.00703 -0.0529 0.3088 1.0000
6.750 0.9901 0.01470 0.00759 -0.0513 0.2683 1.0000
7.000 1.0073 0.01545 0.00818 -0.0498 0.2275 1.0000
7.250 1.0241 0.01623 0.00878 -0.0483 0.1866 1.0000
7.500 1.0408 0.01705 0.00941 -0.0468 0.1473 1.0000
7.750 1.0571 0.01793 0.01013 -0.0453 0.1137 1.0000
8.000 1.0697 0.01920 0.01113 -0.0432 0.0680 1.0000
8.250 1.0744 0.02125 0.01292 -0.0398 0.0349 1.0000
8.500 1.0836 0.02271 0.01443 -0.0371 0.0282 1.0000
8.750 1.0951 0.02385 0.01567 -0.0347 0.0254 1.0000
9.000 1.1037 0.02514 0.01703 -0.0320 0.0235 1.0000
9.250 1.1092 0.02692 0.01886 -0.0290 0.0221 1.0000
9.500 1.1192 0.02910 0.02112 -0.0268 0.0212 1.0000
9.750 1.1354 0.03079 0.02296 -0.0253 0.0208 1.0000
10.000 1.1532 0.03277 0.02511 -0.0240 0.0202 1.0000
10.250 1.1717 0.03511 0.02768 -0.0230 0.0200 1.0000
10.500 1.1879 0.03782 0.03069 -0.0217 0.0199 1.0000
10.750 1.1979 0.04061 0.03379 -0.0198 0.0199 1.0000
11.000 1.2017 0.04300 0.03646 -0.0174 0.0195 1.0000
11.250 1.2017 0.04566 0.03941 -0.0148 0.0193 1.0000
11.500 1.1978 0.04833 0.04235 -0.0122 0.0189 1.0000
11.750 1.1922 0.05088 0.04515 -0.0100 0.0183 1.0000
12.000 1.1808 0.05453 0.04910 -0.0079 0.0185 1.0000
12.250 1.1659 0.05860 0.05346 -0.0064 0.0188 1.0000
12.500 1.1497 0.06281 0.05793 -0.0056 0.0189 1.0000
12.750 1.1309 0.06771 0.06308 -0.0057 0.0192 1.0000
13.000 1.1117 0.07296 0.06855 -0.0066 0.0194 1.0000
13.250 1.0900 0.07902 0.07482 -0.0087 0.0196 1.0000
13.500 1.0685 0.08560 0.08159 -0.0119 0.0196 1.0000
13.750 1.0474 0.09285 0.08899 -0.0160 0.0199 1.0000
14.000 1.0245 0.10134 0.09764 -0.0214 0.0201 1.0000
14.250 1.0011 0.11107 0.10750 -0.0279 0.0204 1.0000
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Polar data table (+)
Polar graphs
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