E182 (8.47%) (e182-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: E182 (8.47%) (e182-il) Reynolds number: 50,000 Max Cl/Cd: 34.12 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e182-il-50000-n5.txt Download as CSV file: xf-e182-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5651 0.09276 0.08643 0.0023 1.0000 0.0459
-8.250 -0.5652 0.08797 0.08172 -0.0011 1.0000 0.0448
-8.000 -0.5671 0.08297 0.07678 -0.0052 1.0000 0.0437
-7.750 -0.5675 0.07755 0.07138 -0.0095 1.0000 0.0426
-7.500 -0.5673 0.07170 0.06547 -0.0136 1.0000 0.0414
-7.250 -0.5665 0.06553 0.05919 -0.0174 1.0000 0.0401
-7.000 -0.5646 0.05902 0.05230 -0.0206 1.0000 0.0385
-6.500 -0.5421 0.05010 0.04248 -0.0224 1.0000 0.0374
-6.250 -0.5275 0.04613 0.03812 -0.0226 1.0000 0.0374
-6.000 -0.5116 0.04232 0.03400 -0.0227 1.0000 0.0381
-5.750 -0.4936 0.03932 0.03076 -0.0227 1.0000 0.0396
-5.500 -0.4734 0.03678 0.02796 -0.0226 1.0000 0.0417
-5.250 -0.4519 0.03408 0.02484 -0.0222 1.0000 0.0431
-5.000 -0.4292 0.03151 0.02185 -0.0217 1.0000 0.0441
-4.750 -0.4062 0.02926 0.01922 -0.0210 1.0000 0.0455
-4.500 -0.3842 0.02737 0.01696 -0.0200 1.0000 0.0473
-4.250 -0.3646 0.02585 0.01515 -0.0185 1.0000 0.0495
-4.000 -0.3494 0.02460 0.01391 -0.0168 0.9995 0.0534
-3.750 -0.3113 0.02318 0.01230 -0.0191 0.9830 0.0652
-3.500 -0.2722 0.02161 0.01066 -0.0214 0.9696 0.0908
-3.250 -0.2368 0.01971 0.00951 -0.0240 0.9570 0.2096
-3.000 -0.2081 0.01801 0.00888 -0.0249 0.9441 0.4215
-2.750 -0.1795 0.01672 0.00875 -0.0234 0.9336 0.6991
-2.500 -0.0819 0.01636 0.00817 -0.0337 0.9376 0.9523
-2.250 -0.0182 0.01621 0.00749 -0.0410 0.9308 1.0000
-2.000 0.0124 0.01627 0.00717 -0.0422 0.9144 1.0000
-1.750 0.0400 0.01638 0.00697 -0.0426 0.8992 1.0000
-1.500 0.0656 0.01652 0.00685 -0.0426 0.8854 1.0000
-1.250 0.0900 0.01669 0.00679 -0.0422 0.8726 1.0000
-1.000 0.1138 0.01688 0.00675 -0.0416 0.8609 1.0000
-0.750 0.1369 0.01709 0.00678 -0.0409 0.8491 1.0000
-0.500 0.1601 0.01731 0.00684 -0.0403 0.8381 1.0000
-0.250 0.1834 0.01754 0.00694 -0.0396 0.8281 1.0000
0.000 0.2065 0.01778 0.00705 -0.0387 0.8186 1.0000
0.250 0.2299 0.01805 0.00723 -0.0381 0.8084 1.0000
0.500 0.2532 0.01832 0.00742 -0.0374 0.7992 1.0000
0.750 0.2765 0.01859 0.00763 -0.0366 0.7904 1.0000
1.000 0.2999 0.01891 0.00793 -0.0360 0.7807 1.0000
1.250 0.3233 0.01921 0.00819 -0.0352 0.7724 1.0000
1.500 0.3467 0.01953 0.00852 -0.0345 0.7632 1.0000
1.750 0.3701 0.01989 0.00889 -0.0339 0.7539 1.0000
2.000 0.3936 0.02017 0.00920 -0.0329 0.7460 1.0000
2.250 0.4172 0.02057 0.00966 -0.0324 0.7356 1.0000
2.500 0.4406 0.02093 0.01008 -0.0316 0.7261 1.0000
2.750 0.4639 0.02120 0.01044 -0.0304 0.7172 1.0000
3.000 0.4869 0.02158 0.01093 -0.0297 0.7057 1.0000
3.250 0.5098 0.02193 0.01139 -0.0287 0.6942 1.0000
3.500 0.5327 0.02221 0.01178 -0.0275 0.6827 1.0000
3.750 0.5557 0.02243 0.01216 -0.0261 0.6706 1.0000
4.000 0.5785 0.02260 0.01248 -0.0246 0.6574 1.0000
4.250 0.6010 0.02277 0.01280 -0.0231 0.6422 1.0000
4.500 0.6233 0.02290 0.01312 -0.0216 0.6250 1.0000
4.750 0.6457 0.02291 0.01332 -0.0198 0.6064 1.0000
5.000 0.6685 0.02274 0.01336 -0.0177 0.5870 1.0000
5.250 0.6904 0.02269 0.01354 -0.0159 0.5618 1.0000
5.500 0.7123 0.02251 0.01358 -0.0139 0.5328 1.0000
5.750 0.7338 0.02238 0.01366 -0.0119 0.4957 1.0000
6.000 0.7542 0.02228 0.01372 -0.0096 0.4429 1.0000
6.250 0.7705 0.02258 0.01368 -0.0069 0.3454 1.0000
6.500 0.7769 0.02467 0.01462 -0.0049 0.2064 1.0000
6.750 0.7824 0.02741 0.01644 -0.0038 0.1091 1.0000
7.000 0.7917 0.02974 0.01846 -0.0024 0.0719 1.0000
7.250 0.8022 0.03187 0.02047 -0.0009 0.0583 1.0000
7.500 0.8160 0.03366 0.02246 0.0008 0.0513 1.0000
7.750 0.8296 0.03556 0.02439 0.0023 0.0469 1.0000
8.000 0.8492 0.03724 0.02639 0.0038 0.0423 1.0000
8.250 0.8674 0.03903 0.02833 0.0050 0.0386 1.0000
8.500 0.8863 0.04128 0.03063 0.0061 0.0363 1.0000
8.750 0.9077 0.04389 0.03356 0.0072 0.0352 1.0000
9.000 0.9253 0.04683 0.03691 0.0083 0.0344 1.0000
9.250 0.9378 0.05006 0.04057 0.0093 0.0339 1.0000
9.500 0.9448 0.05361 0.04455 0.0104 0.0335 1.0000
9.750 0.9465 0.05726 0.04857 0.0113 0.0333 1.0000
10.000 0.9425 0.06105 0.05276 0.0121 0.0333 1.0000
10.250 0.9322 0.06472 0.05669 0.0129 0.0333 1.0000
10.500 0.9186 0.06874 0.06093 0.0127 0.0334 1.0000
10.750 0.9031 0.07329 0.06568 0.0115 0.0336 1.0000
11.000 0.8857 0.07853 0.07108 0.0091 0.0337 1.0000
11.250 0.8682 0.08437 0.07699 0.0059 0.0340 1.0000
11.500 0.8504 0.09099 0.08371 0.0017 0.0343 1.0000
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Polar data table (+)
Polar graphs
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