SD2083 (9.0%) (sd2083-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: SD2083 (9.0%) (sd2083-il) Reynolds number: 200,000 Max Cl/Cd: 74.03 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sd2083-il-200000-n5.txt Download as CSV file: xf-sd2083-il-200000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3908 0.08720 0.08376 -0.0373 1.0000 0.0246
-8.500 -0.3932 0.08343 0.08005 -0.0385 1.0000 0.0232
-8.250 -0.3991 0.07994 0.07664 -0.0395 1.0000 0.0229
-8.000 -0.4131 0.07717 0.07396 -0.0388 1.0000 0.0224
-7.750 -0.4127 0.07335 0.07019 -0.0429 0.9916 0.0238
-7.500 -0.3946 0.06604 0.06282 -0.0542 0.9831 0.0240
-7.000 -0.3661 0.04542 0.04155 -0.0731 0.9632 0.0184
-6.750 -0.3488 0.03984 0.03561 -0.0764 0.9568 0.0180
-6.500 -0.3341 0.03518 0.03055 -0.0773 0.9484 0.0177
-6.250 -0.3143 0.03088 0.02576 -0.0781 0.9428 0.0175
-6.000 -0.2970 0.02759 0.02198 -0.0774 0.9350 0.0174
-5.750 -0.2746 0.02476 0.01862 -0.0772 0.9299 0.0176
-5.500 -0.2530 0.02267 0.01612 -0.0763 0.9235 0.0178
-5.250 -0.2288 0.02094 0.01401 -0.0757 0.9182 0.0181
-5.000 -0.2033 0.01960 0.01237 -0.0753 0.9137 0.0185
-4.750 -0.1797 0.01835 0.01087 -0.0745 0.9076 0.0196
-4.500 -0.1546 0.01716 0.00956 -0.0741 0.9029 0.0207
-4.250 -0.1298 0.01624 0.00851 -0.0735 0.8978 0.0210
-4.000 -0.1051 0.01545 0.00760 -0.0728 0.8921 0.0213
-3.750 -0.0795 0.01475 0.00681 -0.0722 0.8878 0.0219
-3.500 -0.0550 0.01420 0.00619 -0.0716 0.8819 0.0225
-3.250 -0.0295 0.01372 0.00561 -0.0710 0.8767 0.0236
-3.000 -0.0033 0.01331 0.00510 -0.0705 0.8724 0.0250
-2.750 0.0222 0.01299 0.00469 -0.0700 0.8661 0.0273
-2.500 0.0484 0.01260 0.00428 -0.0695 0.8613 0.0351
-2.250 0.0738 0.01218 0.00400 -0.0691 0.8559 0.0715
-2.000 0.0984 0.01168 0.00379 -0.0686 0.8500 0.1473
-1.750 0.1227 0.01104 0.00361 -0.0682 0.8455 0.2777
-1.500 0.1462 0.01059 0.00352 -0.0675 0.8387 0.3902
-1.250 0.1669 0.00989 0.00347 -0.0661 0.8332 0.5752
-1.000 0.1856 0.00920 0.00355 -0.0634 0.8271 0.7876
-0.750 0.2467 0.00895 0.00348 -0.0695 0.8235 0.9502
-0.500 0.2940 0.00889 0.00331 -0.0734 0.8187 0.9843
-0.250 0.3350 0.00886 0.00318 -0.0763 0.8117 1.0000
0.000 0.3590 0.00885 0.00306 -0.0754 0.8042 1.0000
0.250 0.3828 0.00888 0.00302 -0.0746 0.7948 1.0000
0.500 0.4070 0.00889 0.00296 -0.0737 0.7863 1.0000
0.750 0.4314 0.00891 0.00290 -0.0729 0.7769 1.0000
1.000 0.4557 0.00894 0.00288 -0.0721 0.7661 1.0000
1.250 0.4802 0.00897 0.00285 -0.0713 0.7552 1.0000
1.500 0.5048 0.00901 0.00283 -0.0705 0.7439 1.0000
1.750 0.5294 0.00905 0.00283 -0.0697 0.7317 1.0000
2.000 0.5541 0.00911 0.00284 -0.0689 0.7189 1.0000
2.250 0.5789 0.00917 0.00286 -0.0682 0.7056 1.0000
2.500 0.6038 0.00925 0.00291 -0.0675 0.6916 1.0000
2.750 0.6286 0.00934 0.00299 -0.0668 0.6761 1.0000
3.000 0.6533 0.00945 0.00307 -0.0661 0.6591 1.0000
3.250 0.6779 0.00957 0.00314 -0.0653 0.6399 1.0000
3.500 0.7022 0.00972 0.00324 -0.0645 0.6181 1.0000
3.750 0.7261 0.00991 0.00338 -0.0636 0.5926 1.0000
4.000 0.7495 0.01014 0.00352 -0.0627 0.5631 1.0000
4.250 0.7721 0.01043 0.00369 -0.0616 0.5285 1.0000
4.500 0.7939 0.01078 0.00390 -0.0604 0.4896 1.0000
4.750 0.8149 0.01121 0.00416 -0.0592 0.4486 1.0000
5.000 0.8354 0.01169 0.00451 -0.0580 0.4073 1.0000
5.250 0.8557 0.01221 0.00487 -0.0567 0.3682 1.0000
5.500 0.8759 0.01274 0.00526 -0.0555 0.3317 1.0000
5.750 0.8963 0.01327 0.00568 -0.0544 0.2977 1.0000
6.000 0.9165 0.01383 0.00612 -0.0533 0.2657 1.0000
6.250 0.9366 0.01439 0.00659 -0.0521 0.2357 1.0000
6.500 0.9560 0.01501 0.00713 -0.0509 0.2048 1.0000
6.750 0.9743 0.01574 0.00767 -0.0496 0.1659 1.0000
7.000 0.9912 0.01660 0.00826 -0.0482 0.1224 1.0000
7.250 1.0097 0.01732 0.00888 -0.0470 0.0969 1.0000
7.500 1.0270 0.01814 0.00957 -0.0456 0.0699 1.0000
7.750 1.0436 0.01903 0.01034 -0.0441 0.0460 1.0000
8.250 1.0737 0.02109 0.01232 -0.0406 0.0167 1.0000
8.500 1.0883 0.02210 0.01335 -0.0388 0.0130 1.0000
8.750 1.1037 0.02299 0.01437 -0.0370 0.0117 1.0000
9.000 1.1171 0.02392 0.01543 -0.0350 0.0108 1.0000
9.250 1.1280 0.02496 0.01659 -0.0327 0.0101 1.0000
9.500 1.1364 0.02617 0.01792 -0.0302 0.0096 1.0000
9.750 1.1426 0.02755 0.01944 -0.0276 0.0093 1.0000
10.000 1.1478 0.02908 0.02110 -0.0250 0.0090 1.0000
10.250 1.1547 0.03054 0.02271 -0.0228 0.0088 1.0000
10.500 1.1612 0.03210 0.02445 -0.0207 0.0087 1.0000
10.750 1.1671 0.03382 0.02632 -0.0187 0.0086 1.0000
11.000 1.1725 0.03570 0.02836 -0.0168 0.0084 1.0000
11.250 1.1777 0.03769 0.03052 -0.0151 0.0083 1.0000
11.500 1.1827 0.03973 0.03273 -0.0135 0.0082 1.0000
11.750 1.1862 0.04204 0.03523 -0.0120 0.0080 1.0000
12.000 1.1891 0.04426 0.03765 -0.0108 0.0077 1.0000
12.250 1.1900 0.04687 0.04046 -0.0096 0.0076 1.0000
12.500 1.1890 0.04960 0.04339 -0.0088 0.0073 1.0000
12.750 1.1864 0.05258 0.04658 -0.0082 0.0070 1.0000
13.000 1.1823 0.05579 0.05000 -0.0080 0.0068 1.0000
13.250 1.1749 0.05977 0.05421 -0.0080 0.0068 1.0000
13.500 1.1660 0.06397 0.05862 -0.0087 0.0067 1.0000
13.750 1.1554 0.06869 0.06355 -0.0099 0.0066 1.0000
14.000 1.1436 0.07390 0.06897 -0.0117 0.0066 1.0000
14.250 1.1300 0.07979 0.07509 -0.0143 0.0066 1.0000
14.500 1.1136 0.08668 0.08220 -0.0177 0.0066 1.0000
14.750 1.0976 0.09402 0.08973 -0.0218 0.0067 1.0000
15.000 1.0808 0.10207 0.09797 -0.0266 0.0067 1.0000
15.250 1.0612 0.11137 0.10746 -0.0322 0.0068 1.0000
15.500 1.0400 0.12171 0.11798 -0.0385 0.0069 1.0000
15.750 1.0167 0.13337 0.12978 -0.0456 0.0070 1.0000
16.000 0.9839 0.14910 0.14566 -0.0546 0.0074 1.0000
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Polar data table (+)
Polar graphs
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