EPPLER 428 AIRFOIL (e428-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 428 AIRFOIL (e428-il) Reynolds number: 200,000 Max Cl/Cd: 53.4 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e428-il-200000-n5.txt Download as CSV file: xf-e428-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 428 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
------ -------- --------- --------- -------- -------- --------
-14.250 -0.9444 0.08564 0.08037 -0.0066 1.0000 0.0161
-14.000 -0.9562 0.08004 0.07470 -0.0097 1.0000 0.0159
-13.750 -0.9721 0.07371 0.06828 -0.0132 1.0000 0.0160
-13.500 -0.9892 0.06722 0.06167 -0.0170 1.0000 0.0160
-13.250 -1.0066 0.06061 0.05495 -0.0210 1.0000 0.0160
-13.000 -1.0236 0.05392 0.04811 -0.0253 1.0000 0.0160
-12.750 -1.0379 0.04778 0.04181 -0.0297 1.0000 0.0159
-12.500 -1.0503 0.04236 0.03622 -0.0336 1.0000 0.0161
-12.250 -1.0598 0.03825 0.03195 -0.0361 1.0000 0.0160
-12.000 -1.0672 0.03532 0.02886 -0.0365 1.0000 0.0162
-11.750 -1.0714 0.03325 0.02666 -0.0351 1.0000 0.0164
-11.500 -1.0685 0.03135 0.02464 -0.0340 1.0000 0.0166
-11.250 -1.0608 0.02967 0.02283 -0.0329 1.0000 0.0170
-11.000 -1.0492 0.02819 0.02122 -0.0320 1.0000 0.0176
-10.750 -1.0348 0.02689 0.01978 -0.0311 1.0000 0.0183
-10.500 -1.0185 0.02571 0.01846 -0.0302 1.0000 0.0192
-10.250 -1.0018 0.02446 0.01712 -0.0294 1.0000 0.0202
-10.000 -0.9835 0.02334 0.01590 -0.0286 1.0000 0.0216
-9.750 -0.9641 0.02230 0.01477 -0.0278 1.0000 0.0235
-9.500 -0.9445 0.02123 0.01366 -0.0271 1.0000 0.0273
-9.250 -0.9242 0.02020 0.01268 -0.0264 1.0000 0.0369
-9.000 -0.9019 0.01945 0.01190 -0.0257 1.0000 0.0490
-8.750 -0.8791 0.01878 0.01118 -0.0251 1.0000 0.0572
-8.000 -0.8091 0.01697 0.00941 -0.0234 1.0000 0.0845
-7.750 -0.7849 0.01650 0.00894 -0.0229 1.0000 0.0934
-7.500 -0.7604 0.01607 0.00847 -0.0223 1.0000 0.1006
-7.250 -0.7356 0.01570 0.00803 -0.0217 1.0000 0.1090
-7.000 -0.7113 0.01527 0.00764 -0.0211 1.0000 0.1184
-6.750 -0.6868 0.01490 0.00728 -0.0205 1.0000 0.1282
-6.500 -0.6620 0.01457 0.00695 -0.0199 1.0000 0.1383
-6.250 -0.6371 0.01428 0.00665 -0.0193 1.0000 0.1481
-6.000 -0.6124 0.01398 0.00638 -0.0187 1.0000 0.1563
-5.750 -0.5875 0.01373 0.00608 -0.0180 1.0000 0.1643
-5.500 -0.5630 0.01346 0.00583 -0.0173 1.0000 0.1718
-5.250 -0.5382 0.01324 0.00557 -0.0166 1.0000 0.1793
-5.000 -0.5138 0.01299 0.00535 -0.0158 1.0000 0.1865
-4.750 -0.4891 0.01280 0.00511 -0.0151 1.0000 0.1938
-4.500 -0.4650 0.01257 0.00494 -0.0143 1.0000 0.2017
-4.250 -0.4408 0.01241 0.00476 -0.0135 1.0000 0.2101
-4.000 -0.4105 0.01221 0.00462 -0.0140 0.9954 0.2194
-3.750 -0.3724 0.01203 0.00445 -0.0161 0.9843 0.2296
-3.500 -0.3349 0.01185 0.00428 -0.0180 0.9716 0.2391
-3.250 -0.2980 0.01165 0.00410 -0.0197 0.9562 0.2468
-3.000 -0.2606 0.01146 0.00393 -0.0214 0.9371 0.2553
-2.750 -0.2217 0.01128 0.00374 -0.0234 0.9106 0.2643
-2.500 -0.1842 0.01114 0.00356 -0.0249 0.8754 0.2747
-2.000 -0.1258 0.01098 0.00324 -0.0244 0.8020 0.2942
-1.750 -0.0999 0.01093 0.00312 -0.0236 0.7672 0.3056
-1.500 -0.0741 0.01089 0.00301 -0.0228 0.7353 0.3197
-1.250 -0.0481 0.01082 0.00293 -0.0221 0.7075 0.3375
-0.750 0.0041 0.01067 0.00279 -0.0208 0.6572 0.3834
-0.500 0.0301 0.01061 0.00275 -0.0202 0.6323 0.4132
-0.250 0.0560 0.01053 0.00273 -0.0195 0.6066 0.4494
0.000 0.0817 0.01047 0.00273 -0.0188 0.5804 0.4883
0.250 0.1076 0.01044 0.00274 -0.0181 0.5532 0.5261
0.500 0.1332 0.01043 0.00276 -0.0174 0.5238 0.5637
0.750 0.1586 0.01046 0.00279 -0.0166 0.4926 0.6015
1.000 0.1839 0.01050 0.00285 -0.0158 0.4605 0.6374
1.250 0.2092 0.01058 0.00291 -0.0150 0.4264 0.6710
1.500 0.2342 0.01069 0.00298 -0.0141 0.3880 0.7042
1.750 0.2588 0.01084 0.00308 -0.0132 0.3473 0.7383
2.000 0.2833 0.01099 0.00319 -0.0122 0.3129 0.7731
2.250 0.3082 0.01113 0.00332 -0.0113 0.2886 0.8104
2.500 0.3348 0.01127 0.00348 -0.0106 0.2700 0.8522
2.750 0.3657 0.01143 0.00364 -0.0109 0.2545 0.8979
3.000 0.4057 0.01164 0.00382 -0.0132 0.2406 0.9458
3.250 0.4469 0.01190 0.00401 -0.0159 0.2292 0.9990
3.500 0.4729 0.01213 0.00420 -0.0155 0.2216 1.0000
3.750 0.4984 0.01239 0.00440 -0.0149 0.2143 1.0000
4.000 0.5241 0.01266 0.00463 -0.0144 0.2077 1.0000
4.250 0.5501 0.01290 0.00486 -0.0139 0.2011 1.0000
4.500 0.5756 0.01322 0.00511 -0.0134 0.1958 1.0000
4.750 0.6017 0.01348 0.00538 -0.0130 0.1906 1.0000
5.000 0.6278 0.01374 0.00564 -0.0125 0.1843 1.0000
5.250 0.6533 0.01408 0.00591 -0.0120 0.1782 1.0000
5.500 0.6796 0.01430 0.00618 -0.0116 0.1717 1.0000
5.750 0.7053 0.01460 0.00644 -0.0112 0.1654 1.0000
6.000 0.7311 0.01492 0.00678 -0.0107 0.1607 1.0000
6.250 0.7571 0.01521 0.00712 -0.0102 0.1559 1.0000
6.500 0.7826 0.01554 0.00744 -0.0098 0.1511 1.0000
6.750 0.8080 0.01591 0.00782 -0.0093 0.1466 1.0000
7.000 0.8338 0.01621 0.00820 -0.0088 0.1416 1.0000
7.250 0.8590 0.01656 0.00856 -0.0083 0.1367 1.0000
7.500 0.8840 0.01696 0.00899 -0.0078 0.1323 1.0000
7.750 0.9094 0.01729 0.00940 -0.0074 0.1266 1.0000
8.000 0.9338 0.01769 0.00978 -0.0068 0.1211 1.0000
8.250 0.9590 0.01804 0.01024 -0.0063 0.1148 1.0000
8.500 0.9831 0.01845 0.01065 -0.0058 0.1088 1.0000
8.750 1.0076 0.01887 0.01115 -0.0052 0.1027 1.0000
9.000 1.0311 0.01934 0.01163 -0.0046 0.0966 1.0000
9.250 1.0549 0.01982 0.01219 -0.0040 0.0907 1.0000
9.500 1.0774 0.02037 0.01275 -0.0034 0.0854 1.0000
9.750 1.1004 0.02092 0.01338 -0.0027 0.0802 1.0000
10.000 1.1220 0.02155 0.01404 -0.0020 0.0756 1.0000
10.250 1.1438 0.02218 0.01476 -0.0012 0.0715 1.0000
10.500 1.1642 0.02289 0.01550 -0.0004 0.0668 1.0000
10.750 1.1845 0.02361 0.01631 0.0004 0.0624 1.0000
11.000 1.2033 0.02444 0.01719 0.0013 0.0583 1.0000
11.250 1.2217 0.02527 0.01812 0.0023 0.0544 1.0000
11.500 1.2381 0.02623 0.01915 0.0034 0.0506 1.0000
11.750 1.2538 0.02721 0.02024 0.0046 0.0468 1.0000
12.000 1.2665 0.02837 0.02147 0.0060 0.0429 1.0000
12.250 1.2792 0.02946 0.02270 0.0074 0.0388 1.0000
12.500 1.2866 0.03074 0.02407 0.0092 0.0355 1.0000
12.750 1.2909 0.03210 0.02553 0.0113 0.0326 1.0000
13.000 1.2922 0.03375 0.02727 0.0131 0.0305 1.0000
13.250 1.2914 0.03573 0.02936 0.0143 0.0286 1.0000
13.500 1.2879 0.03820 0.03194 0.0148 0.0276 1.0000
13.750 1.2815 0.04134 0.03521 0.0143 0.0267 1.0000
14.000 1.2733 0.04510 0.03913 0.0130 0.0261 1.0000
14.250 1.2619 0.04972 0.04392 0.0108 0.0256 1.0000
14.500 1.2471 0.05528 0.04966 0.0076 0.0255 1.0000
14.750 1.2273 0.06209 0.05664 0.0035 0.0254 1.0000
15.000 1.2008 0.07042 0.06517 -0.0016 0.0253 1.0000
15.250 1.1704 0.07978 0.07471 -0.0073 0.0254 1.0000
15.500 1.1403 0.08927 0.08437 -0.0128 0.0257 1.0000
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