E182 (8.47%) (e182-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: E182 (8.47%) (e182-il) Reynolds number: 200,000 Max Cl/Cd: 64.1 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e182-il-200000.txt Download as CSV file: xf-e182-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: E182 (8.47%)
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4820 0.09802 0.09512 0.0131 1.0000 0.0473
-9.000 -0.4810 0.09371 0.09082 0.0114 1.0000 0.0487
-8.750 -0.5882 0.09467 0.09161 0.0089 1.0000 0.0443
-8.500 -0.5769 0.09217 0.08909 0.0101 1.0000 0.0464
-8.250 -0.5748 0.08837 0.08532 0.0079 1.0000 0.0476
-8.000 -0.5756 0.08423 0.08123 0.0049 1.0000 0.0488
-7.750 -0.5795 0.07975 0.07680 0.0008 1.0000 0.0499
-7.500 -0.5794 0.07422 0.07126 -0.0051 1.0000 0.0516
-7.250 -0.5817 0.06745 0.06413 -0.0152 1.0000 0.0545
-6.750 -0.5656 0.05638 0.05299 -0.0179 1.0000 0.0568
-6.500 -0.5495 0.05337 0.04999 -0.0184 1.0000 0.0587
-6.250 -0.5327 0.04986 0.04637 -0.0197 1.0000 0.0618
-6.000 -0.5188 0.04461 0.04049 -0.0221 1.0000 0.0691
-5.750 -0.4969 0.04128 0.03724 -0.0231 1.0000 0.0712
-5.500 -0.4692 0.03826 0.03404 -0.0252 0.9776 0.0760
-5.250 -0.4381 0.02750 0.02188 -0.0250 0.9526 0.0383
-5.000 -0.4110 0.02455 0.01805 -0.0232 0.9322 0.0315
-4.750 -0.3910 0.02166 0.01476 -0.0215 0.9148 0.0306
-4.500 -0.3695 0.01987 0.01263 -0.0197 0.8995 0.0305
-4.250 -0.3467 0.01897 0.01145 -0.0182 0.8862 0.0320
-4.000 -0.3245 0.01705 0.00936 -0.0168 0.8747 0.0335
-3.750 -0.3008 0.01588 0.00811 -0.0156 0.8632 0.0343
-3.500 -0.2770 0.01498 0.00713 -0.0145 0.8526 0.0362
-3.250 -0.2534 0.01427 0.00633 -0.0134 0.8433 0.0393
-3.000 -0.2294 0.01350 0.00547 -0.0123 0.8339 0.0461
-2.750 -0.2076 0.01207 0.00464 -0.0112 0.8248 0.1652
-2.500 -0.1867 0.01118 0.00437 -0.0102 0.8171 0.3248
-2.250 -0.1672 0.01024 0.00420 -0.0088 0.8080 0.5196
-2.000 -0.1489 0.00911 0.00427 -0.0055 0.8012 0.8213
-1.750 -0.0664 0.00922 0.00432 -0.0153 0.7949 0.9642
-1.500 -0.0008 0.00928 0.00409 -0.0229 0.7891 0.9982
-1.250 0.0276 0.00927 0.00394 -0.0233 0.7804 1.0000
-1.000 0.0513 0.00929 0.00381 -0.0225 0.7734 1.0000
-0.750 0.0762 0.00932 0.00371 -0.0221 0.7651 1.0000
-0.500 0.1006 0.00938 0.00364 -0.0214 0.7584 1.0000
-0.250 0.1259 0.00943 0.00361 -0.0210 0.7506 1.0000
0.000 0.1507 0.00951 0.00358 -0.0204 0.7441 1.0000
0.250 0.1763 0.00958 0.00359 -0.0200 0.7365 1.0000
0.500 0.2014 0.00967 0.00360 -0.0194 0.7302 1.0000
0.750 0.2273 0.00976 0.00365 -0.0191 0.7225 1.0000
1.000 0.2523 0.00986 0.00368 -0.0185 0.7164 1.0000
1.250 0.2785 0.00996 0.00377 -0.0182 0.7084 1.0000
1.500 0.3037 0.01006 0.00381 -0.0176 0.7019 1.0000
1.750 0.3296 0.01015 0.00390 -0.0172 0.6933 1.0000
2.000 0.3551 0.01025 0.00397 -0.0166 0.6856 1.0000
2.250 0.3806 0.01032 0.00404 -0.0160 0.6770 1.0000
2.500 0.4064 0.01041 0.00414 -0.0156 0.6678 1.0000
2.750 0.4315 0.01047 0.00416 -0.0147 0.6596 1.0000
3.000 0.4574 0.01052 0.00425 -0.0143 0.6488 1.0000
3.250 0.4831 0.01058 0.00436 -0.0137 0.6382 1.0000
3.500 0.5086 0.01062 0.00441 -0.0130 0.6277 1.0000
3.750 0.5340 0.01064 0.00443 -0.0123 0.6166 1.0000
4.000 0.5597 0.01065 0.00449 -0.0116 0.6035 1.0000
4.250 0.5855 0.01065 0.00458 -0.0110 0.5895 1.0000
4.500 0.6110 0.01063 0.00462 -0.0103 0.5720 1.0000
4.750 0.6360 0.01052 0.00452 -0.0094 0.5427 1.0000
5.000 0.6609 0.01051 0.00448 -0.0086 0.5043 1.0000
5.250 0.6852 0.01069 0.00456 -0.0078 0.4459 1.0000
5.500 0.7064 0.01152 0.00482 -0.0071 0.3203 1.0000
5.750 0.7254 0.01304 0.00564 -0.0067 0.1864 1.0000
6.000 0.7401 0.01550 0.00717 -0.0059 0.0452 1.0000
6.250 0.7610 0.01669 0.00842 -0.0049 0.0353 1.0000
6.500 0.7817 0.01774 0.00952 -0.0041 0.0304 1.0000
6.750 0.8001 0.01911 0.01095 -0.0029 0.0278 1.0000
7.000 0.8197 0.02031 0.01224 -0.0018 0.0265 1.0000
7.250 0.8393 0.02165 0.01366 -0.0005 0.0257 1.0000
7.500 0.8594 0.02318 0.01527 0.0007 0.0250 1.0000
7.750 0.8805 0.02491 0.01715 0.0019 0.0248 1.0000
8.000 0.9020 0.02703 0.01945 0.0031 0.0249 1.0000
8.250 0.9229 0.02954 0.02224 0.0042 0.0254 1.0000
8.500 0.9415 0.03256 0.02560 0.0054 0.0263 1.0000
8.750 0.9563 0.03639 0.02981 0.0067 0.0274 1.0000
9.000 0.9680 0.04211 0.03579 0.0077 0.0288 1.0000
9.250 0.9800 0.04484 0.03883 0.0089 0.0290 1.0000
9.500 0.9932 0.04626 0.04060 0.0105 0.0299 1.0000
13.500 0.7857 0.15037 0.14672 -0.0257 0.0496 1.0000
13.750 0.7837 0.15604 0.15237 -0.0295 0.0494 1.0000
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Polar data table (+)
Polar graphs
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