EPPLER 426 AIRFOIL (e426-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 426 AIRFOIL (e426-il) Reynolds number: 200,000 Max Cl/Cd: 54.09 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e426-il-200000-n5.txt Download as CSV file: xf-e426-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 426 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-14.500 -0.9503 0.08654 0.08170 -0.0098 1.0000 0.0222
-14.250 -0.9691 0.07941 0.07448 -0.0139 1.0000 0.0222
-14.000 -0.9917 0.07156 0.06651 -0.0187 1.0000 0.0222
-13.750 -1.0147 0.06361 0.05841 -0.0237 1.0000 0.0222
-13.500 -1.0366 0.05588 0.05052 -0.0291 1.0000 0.0222
-13.250 -1.0541 0.04926 0.04373 -0.0339 1.0000 0.0222
-13.000 -1.0683 0.04377 0.03808 -0.0378 1.0000 0.0224
-12.750 -1.0784 0.03966 0.03382 -0.0402 1.0000 0.0227
-12.500 -1.0860 0.03662 0.03064 -0.0409 1.0000 0.0230
-12.250 -1.0909 0.03443 0.02833 -0.0398 1.0000 0.0235
-12.000 -1.0896 0.03266 0.02642 -0.0383 1.0000 0.0243
-11.750 -1.0820 0.03107 0.02467 -0.0372 1.0000 0.0253
-11.500 -1.0730 0.02947 0.02295 -0.0361 1.0000 0.0264
-11.250 -1.0611 0.02802 0.02139 -0.0351 1.0000 0.0277
-11.000 -1.0463 0.02674 0.01998 -0.0341 1.0000 0.0293
-10.750 -1.0306 0.02547 0.01858 -0.0332 1.0000 0.0311
-10.500 -1.0138 0.02423 0.01725 -0.0323 1.0000 0.0334
-10.250 -0.9952 0.02316 0.01605 -0.0315 1.0000 0.0362
-10.000 -0.9762 0.02205 0.01490 -0.0307 1.0000 0.0403
-9.750 -0.9559 0.02110 0.01394 -0.0300 1.0000 0.0459
-9.500 -0.9340 0.02037 0.01323 -0.0294 1.0000 0.0539
-9.250 -0.9106 0.01983 0.01262 -0.0288 1.0000 0.0630
-9.000 -0.8868 0.01936 0.01209 -0.0282 1.0000 0.0705
-8.750 -0.8630 0.01890 0.01157 -0.0277 1.0000 0.0768
-8.500 -0.8387 0.01852 0.01108 -0.0271 1.0000 0.0830
-8.250 -0.8148 0.01808 0.01062 -0.0265 1.0000 0.0881
-8.000 -0.7903 0.01774 0.01021 -0.0260 1.0000 0.0932
-7.750 -0.7658 0.01735 0.00973 -0.0254 1.0000 0.0975
-7.500 -0.7415 0.01699 0.00937 -0.0248 1.0000 0.1016
-7.250 -0.7167 0.01667 0.00898 -0.0241 1.0000 0.1059
-7.000 -0.6921 0.01632 0.00857 -0.0235 1.0000 0.1099
-6.750 -0.6675 0.01604 0.00830 -0.0229 1.0000 0.1146
-6.500 -0.6426 0.01578 0.00797 -0.0222 1.0000 0.1194
-6.250 -0.6181 0.01541 0.00756 -0.0215 1.0000 0.1228
-6.000 -0.5940 0.01502 0.00718 -0.0208 1.0000 0.1259
-5.750 -0.5696 0.01468 0.00683 -0.0200 1.0000 0.1292
-5.500 -0.5451 0.01437 0.00648 -0.0193 1.0000 0.1334
-5.250 -0.5208 0.01404 0.00614 -0.0185 1.0000 0.1374
-5.000 -0.4968 0.01372 0.00585 -0.0177 1.0000 0.1417
-4.750 -0.4725 0.01345 0.00558 -0.0169 1.0000 0.1465
-4.500 -0.4483 0.01322 0.00531 -0.0161 1.0000 0.1512
-4.250 -0.4249 0.01292 0.00507 -0.0153 1.0000 0.1562
-4.000 -0.3919 0.01269 0.00485 -0.0164 0.9943 0.1626
-3.750 -0.3539 0.01245 0.00461 -0.0184 0.9838 0.1691
-3.250 -0.2820 0.01198 0.00418 -0.0215 0.9521 0.1840
-3.000 -0.2443 0.01172 0.00398 -0.0234 0.9323 0.1928
-2.750 -0.2021 0.01150 0.00375 -0.0261 0.9080 0.2022
-2.500 -0.1633 0.01130 0.00353 -0.0279 0.8727 0.2128
-2.250 -0.1328 0.01118 0.00334 -0.0279 0.8309 0.2237
-2.000 -0.1062 0.01110 0.00317 -0.0272 0.7909 0.2371
-1.750 -0.0806 0.01099 0.00303 -0.0264 0.7550 0.2577
-1.500 -0.0552 0.01083 0.00291 -0.0256 0.7250 0.2908
-1.250 -0.0299 0.01060 0.00283 -0.0250 0.6993 0.3466
-1.000 -0.0047 0.01040 0.00279 -0.0243 0.6746 0.4093
-0.750 0.0210 0.01029 0.00277 -0.0236 0.6500 0.4579
-0.500 0.0470 0.01024 0.00274 -0.0229 0.6266 0.4967
-0.250 0.0732 0.01019 0.00274 -0.0223 0.6032 0.5314
0.000 0.0992 0.01017 0.00275 -0.0216 0.5787 0.5653
0.250 0.1250 0.01017 0.00277 -0.0208 0.5528 0.5992
0.500 0.1507 0.01020 0.00279 -0.0200 0.5247 0.6313
0.750 0.1764 0.01025 0.00283 -0.0193 0.4952 0.6610
1.000 0.2022 0.01032 0.00287 -0.0185 0.4653 0.6888
1.250 0.2276 0.01040 0.00292 -0.0177 0.4335 0.7164
1.500 0.2525 0.01050 0.00300 -0.0167 0.3990 0.7484
1.750 0.2764 0.01061 0.00309 -0.0155 0.3625 0.7895
2.000 0.3000 0.01073 0.00320 -0.0142 0.3274 0.8365
2.250 0.3275 0.01089 0.00333 -0.0137 0.2991 0.8877
2.750 0.4091 0.01136 0.00362 -0.0186 0.2573 0.9922
3.000 0.4375 0.01162 0.00378 -0.0188 0.2449 1.0000
3.250 0.4626 0.01185 0.00394 -0.0182 0.2357 1.0000
3.500 0.4877 0.01212 0.00413 -0.0176 0.2277 1.0000
3.750 0.5136 0.01234 0.00433 -0.0171 0.2210 1.0000
4.000 0.5392 0.01260 0.00454 -0.0166 0.2143 1.0000
4.250 0.5649 0.01288 0.00478 -0.0161 0.2081 1.0000
4.500 0.5911 0.01311 0.00501 -0.0156 0.2018 1.0000
4.750 0.6168 0.01341 0.00526 -0.0151 0.1962 1.0000
5.000 0.6427 0.01370 0.00555 -0.0147 0.1911 1.0000
5.250 0.6689 0.01395 0.00582 -0.0143 0.1851 1.0000
5.500 0.6945 0.01427 0.00610 -0.0138 0.1795 1.0000
5.750 0.7204 0.01457 0.00643 -0.0133 0.1744 1.0000
6.000 0.7465 0.01485 0.00674 -0.0129 0.1686 1.0000
6.250 0.7718 0.01520 0.00706 -0.0124 0.1630 1.0000
6.500 0.7977 0.01551 0.00743 -0.0120 0.1575 1.0000
6.750 0.8234 0.01582 0.00777 -0.0115 0.1515 1.0000
7.000 0.8485 0.01620 0.00813 -0.0110 0.1460 1.0000
7.250 0.8743 0.01650 0.00852 -0.0106 0.1396 1.0000
7.500 0.8991 0.01686 0.00886 -0.0101 0.1335 1.0000
7.750 0.9245 0.01721 0.00929 -0.0096 0.1273 1.0000
8.000 0.9492 0.01759 0.00968 -0.0091 0.1215 1.0000
8.250 0.9737 0.01802 0.01016 -0.0086 0.1163 1.0000
8.500 0.9980 0.01845 0.01063 -0.0080 0.1111 1.0000
8.750 1.0214 0.01896 0.01114 -0.0074 0.1064 1.0000
9.000 1.0453 0.01945 0.01173 -0.0068 0.1016 1.0000
9.250 1.0681 0.02000 0.01230 -0.0061 0.0969 1.0000
9.500 1.0908 0.02057 0.01294 -0.0055 0.0920 1.0000
9.750 1.1134 0.02112 0.01356 -0.0048 0.0865 1.0000
10.000 1.1347 0.02178 0.01424 -0.0041 0.0819 1.0000
10.250 1.1568 0.02236 0.01493 -0.0034 0.0769 1.0000
10.500 1.1767 0.02309 0.01566 -0.0025 0.0728 1.0000
10.750 1.1979 0.02373 0.01645 -0.0017 0.0687 1.0000
11.000 1.2172 0.02446 0.01724 -0.0008 0.0647 1.0000
11.250 1.2359 0.02524 0.01811 0.0001 0.0612 1.0000
11.500 1.2541 0.02603 0.01898 0.0011 0.0573 1.0000
11.750 1.2701 0.02694 0.01994 0.0022 0.0540 1.0000
12.000 1.2860 0.02783 0.02097 0.0034 0.0508 1.0000
12.250 1.2988 0.02888 0.02208 0.0047 0.0479 1.0000
12.500 1.3101 0.02993 0.02324 0.0063 0.0450 1.0000
12.750 1.3172 0.03109 0.02450 0.0082 0.0424 1.0000
13.000 1.3209 0.03250 0.02599 0.0101 0.0401 1.0000
13.250 1.3247 0.03402 0.02766 0.0116 0.0376 1.0000
13.500 1.3248 0.03597 0.02972 0.0127 0.0358 1.0000
13.750 1.3222 0.03840 0.03227 0.0131 0.0336 1.0000
14.000 1.3190 0.04120 0.03523 0.0128 0.0318 1.0000
14.250 1.3109 0.04491 0.03906 0.0116 0.0301 1.0000
14.500 1.3004 0.04931 0.04361 0.0096 0.0290 1.0000
14.750 1.2877 0.05445 0.04894 0.0069 0.0278 1.0000
15.000 1.2692 0.06086 0.05553 0.0031 0.0271 1.0000
15.250 1.2457 0.06851 0.06338 -0.0015 0.0271 1.0000
15.500 1.2167 0.07748 0.07255 -0.0070 0.0275 1.0000
15.750 1.1837 0.08748 0.08273 -0.0129 0.0282 1.0000
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Polar data table (+)
Polar graphs
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