E182 (8.47%) (e182-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: E182 (8.47%) (e182-il) Reynolds number: 100,000 Max Cl/Cd: 47.03 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e182-il-100000-n5.txt Download as CSV file: xf-e182-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5797 0.08795 0.08353 0.0049 1.0000 0.0255
-8.250 -0.5818 0.08293 0.07858 0.0012 1.0000 0.0249
-8.000 -0.5864 0.07751 0.07322 -0.0035 1.0000 0.0243
-7.750 -0.5883 0.07109 0.06678 -0.0089 1.0000 0.0234
-7.250 -0.5918 0.05377 0.04882 -0.0184 1.0000 0.0210
-7.000 -0.5840 0.04882 0.04352 -0.0195 1.0000 0.0211
-6.750 -0.5734 0.04447 0.03890 -0.0201 1.0000 0.0215
-6.500 -0.5571 0.04167 0.03596 -0.0205 1.0000 0.0223
-6.250 -0.5399 0.03841 0.03234 -0.0207 1.0000 0.0229
-6.000 -0.5219 0.03451 0.02793 -0.0205 1.0000 0.0228
-5.750 -0.5016 0.03099 0.02385 -0.0202 1.0000 0.0226
-5.500 -0.4772 0.02813 0.02051 -0.0202 0.9810 0.0226
-5.250 -0.4442 0.02560 0.01751 -0.0216 0.9505 0.0229
-5.000 -0.4137 0.02364 0.01518 -0.0221 0.9296 0.0234
-4.750 -0.3866 0.02209 0.01335 -0.0218 0.9112 0.0242
-4.500 -0.3615 0.02081 0.01182 -0.0210 0.8950 0.0251
-4.250 -0.3374 0.01987 0.01067 -0.0200 0.8804 0.0273
-4.000 -0.3145 0.01889 0.00960 -0.0190 0.8672 0.0302
-3.750 -0.2911 0.01811 0.00869 -0.0180 0.8553 0.0332
-3.500 -0.2675 0.01739 0.00775 -0.0168 0.8444 0.0372
-3.250 -0.2438 0.01656 0.00683 -0.0157 0.8339 0.0477
-3.000 -0.2203 0.01564 0.00616 -0.0149 0.8237 0.0985
-2.750 -0.1987 0.01459 0.00582 -0.0142 0.8147 0.2366
-2.500 -0.1774 0.01359 0.00556 -0.0132 0.8058 0.4125
-2.250 -0.1553 0.01276 0.00535 -0.0118 0.7972 0.5871
-2.000 -0.1263 0.01212 0.00528 -0.0106 0.7900 0.7804
-1.750 -0.0603 0.01201 0.00514 -0.0169 0.7832 0.9244
-1.500 -0.0110 0.01206 0.00491 -0.0209 0.7762 0.9759
-1.250 0.0352 0.01202 0.00464 -0.0248 0.7684 1.0000
-1.000 0.0586 0.01206 0.00448 -0.0240 0.7610 1.0000
-0.750 0.0835 0.01210 0.00437 -0.0236 0.7525 1.0000
-0.500 0.1072 0.01216 0.00427 -0.0228 0.7459 1.0000
-0.250 0.1326 0.01224 0.00424 -0.0224 0.7376 1.0000
0.000 0.1567 0.01232 0.00418 -0.0217 0.7313 1.0000
0.250 0.1824 0.01242 0.00421 -0.0214 0.7232 1.0000
0.500 0.2069 0.01251 0.00420 -0.0207 0.7171 1.0000
0.750 0.2328 0.01263 0.00428 -0.0204 0.7091 1.0000
1.000 0.2575 0.01274 0.00432 -0.0197 0.7029 1.0000
1.250 0.2834 0.01288 0.00445 -0.0195 0.6951 1.0000
1.500 0.3084 0.01300 0.00452 -0.0188 0.6888 1.0000
1.750 0.3343 0.01315 0.00468 -0.0185 0.6808 1.0000
2.000 0.3593 0.01328 0.00480 -0.0179 0.6741 1.0000
2.250 0.3851 0.01344 0.00499 -0.0175 0.6653 1.0000
2.500 0.4101 0.01355 0.00510 -0.0168 0.6577 1.0000
2.750 0.4356 0.01369 0.00529 -0.0163 0.6477 1.0000
3.000 0.4609 0.01381 0.00549 -0.0158 0.6377 1.0000
3.250 0.4859 0.01391 0.00561 -0.0150 0.6275 1.0000
3.500 0.5109 0.01399 0.00575 -0.0143 0.6160 1.0000
3.750 0.5362 0.01408 0.00594 -0.0136 0.6027 1.0000
4.000 0.5613 0.01415 0.00610 -0.0129 0.5884 1.0000
4.250 0.5864 0.01421 0.00625 -0.0121 0.5728 1.0000
4.500 0.6116 0.01429 0.00645 -0.0114 0.5537 1.0000
4.750 0.6366 0.01436 0.00665 -0.0106 0.5322 1.0000
5.000 0.6615 0.01446 0.00686 -0.0099 0.5063 1.0000
5.250 0.6852 0.01457 0.00694 -0.0088 0.4594 1.0000
5.500 0.7057 0.01511 0.00701 -0.0075 0.3519 1.0000
5.750 0.7234 0.01648 0.00768 -0.0067 0.2312 1.0000
6.000 0.7402 0.01815 0.00871 -0.0062 0.1244 1.0000
6.250 0.7577 0.01972 0.00983 -0.0054 0.0552 1.0000
6.500 0.7762 0.02112 0.01108 -0.0044 0.0332 1.0000
6.750 0.7958 0.02229 0.01234 -0.0034 0.0280 1.0000
7.000 0.8143 0.02356 0.01373 -0.0024 0.0257 1.0000
7.250 0.8325 0.02480 0.01519 -0.0013 0.0240 1.0000
7.500 0.8499 0.02615 0.01669 -0.0001 0.0228 1.0000
7.750 0.8669 0.02759 0.01823 0.0011 0.0218 1.0000
8.000 0.8837 0.02911 0.01983 0.0023 0.0208 1.0000
8.250 0.9000 0.03093 0.02170 0.0034 0.0197 1.0000
8.500 0.9186 0.03254 0.02355 0.0045 0.0187 1.0000
8.750 0.9364 0.03448 0.02572 0.0055 0.0179 1.0000
9.000 0.9533 0.03675 0.02826 0.0066 0.0176 1.0000
9.250 0.9680 0.03927 0.03113 0.0078 0.0174 1.0000
9.500 0.9793 0.04212 0.03434 0.0090 0.0172 1.0000
9.750 0.9867 0.04512 0.03769 0.0103 0.0171 1.0000
10.000 0.9889 0.04838 0.04132 0.0116 0.0171 1.0000
10.250 0.9858 0.05170 0.04499 0.0130 0.0171 1.0000
10.500 0.9761 0.05495 0.04851 0.0144 0.0172 1.0000
10.750 0.9634 0.05862 0.05243 0.0149 0.0173 1.0000
11.000 0.9485 0.06276 0.05681 0.0143 0.0173 1.0000
11.250 0.9325 0.06746 0.06172 0.0127 0.0174 1.0000
11.500 0.9146 0.07290 0.06735 0.0101 0.0175 1.0000
11.750 0.8945 0.07932 0.07394 0.0062 0.0176 1.0000
12.000 0.8739 0.08672 0.08148 0.0013 0.0178 1.0000
12.250 0.8525 0.09545 0.09031 -0.0047 0.0181 1.0000
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Polar data table (+)
Polar graphs
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