EPPLER 428 AIRFOIL (e428-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: EPPLER 428 AIRFOIL (e428-il) Reynolds number: 100,000 Max Cl/Cd: 37.86 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e428-il-100000-n5.txt Download as CSV file: xf-e428-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -0.7615 0.13035 0.12480 0.0162 1.0000 0.0298
-14.250 -0.8133 0.11304 0.10733 0.0072 1.0000 0.0298
-14.000 -0.8346 0.10415 0.09831 0.0025 1.0000 0.0298
-13.750 -0.8515 0.09678 0.09082 -0.0013 1.0000 0.0301
-13.500 -0.8661 0.09017 0.08410 -0.0048 1.0000 0.0304
-13.250 -0.8796 0.08397 0.07779 -0.0081 1.0000 0.0307
-13.000 -0.8929 0.07792 0.07162 -0.0113 1.0000 0.0310
-12.750 -0.9060 0.07202 0.06564 -0.0146 1.0000 0.0313
-12.500 -0.9217 0.06568 0.05923 -0.0183 1.0000 0.0316
-12.250 -0.9378 0.05925 0.05268 -0.0225 1.0000 0.0317
-12.000 -0.9556 0.05257 0.04586 -0.0272 1.0000 0.0318
-11.750 -0.9716 0.04680 0.03993 -0.0314 1.0000 0.0320
-11.500 -0.9848 0.04250 0.03548 -0.0338 1.0000 0.0323
-11.250 -0.9946 0.03952 0.03237 -0.0337 1.0000 0.0331
-11.000 -0.9960 0.03713 0.02984 -0.0329 1.0000 0.0346
-10.750 -0.9920 0.03498 0.02755 -0.0322 1.0000 0.0370
-10.500 -0.9839 0.03306 0.02550 -0.0314 1.0000 0.0411
-10.250 -0.9731 0.03126 0.02359 -0.0307 1.0000 0.0468
-10.000 -0.9599 0.02961 0.02181 -0.0299 1.0000 0.0548
-9.750 -0.9442 0.02819 0.02030 -0.0292 1.0000 0.0631
-9.500 -0.9262 0.02704 0.01907 -0.0286 1.0000 0.0713
-9.250 -0.9063 0.02610 0.01804 -0.0280 1.0000 0.0790
-9.000 -0.8852 0.02535 0.01719 -0.0275 1.0000 0.0889
-8.750 -0.8633 0.02469 0.01643 -0.0270 1.0000 0.0992
-8.500 -0.8407 0.02405 0.01560 -0.0264 1.0000 0.1088
-8.250 -0.8187 0.02350 0.01506 -0.0259 1.0000 0.1173
-8.000 -0.7959 0.02293 0.01442 -0.0253 1.0000 0.1262
-7.750 -0.7725 0.02237 0.01370 -0.0247 1.0000 0.1356
-7.500 -0.7493 0.02188 0.01322 -0.0241 1.0000 0.1429
-7.250 -0.7255 0.02125 0.01245 -0.0235 1.0000 0.1504
-7.000 -0.7017 0.02076 0.01195 -0.0228 1.0000 0.1576
-6.750 -0.6775 0.02024 0.01132 -0.0222 1.0000 0.1656
-6.500 -0.6533 0.01981 0.01084 -0.0215 1.0000 0.1733
-6.250 -0.6290 0.01934 0.01030 -0.0209 1.0000 0.1810
-6.000 -0.6046 0.01895 0.00987 -0.0202 1.0000 0.1890
-5.750 -0.5803 0.01855 0.00941 -0.0196 1.0000 0.1971
-5.500 -0.5559 0.01820 0.00901 -0.0189 1.0000 0.2058
-5.250 -0.5317 0.01786 0.00867 -0.0182 1.0000 0.2150
-5.000 -0.5073 0.01758 0.00828 -0.0175 1.0000 0.2257
-4.750 -0.4836 0.01723 0.00802 -0.0167 1.0000 0.2342
-4.500 -0.4595 0.01691 0.00763 -0.0159 1.0000 0.2436
-4.250 -0.4359 0.01656 0.00733 -0.0151 1.0000 0.2512
-4.000 -0.4120 0.01625 0.00697 -0.0143 1.0000 0.2597
-3.750 -0.3889 0.01590 0.00672 -0.0134 1.0000 0.2670
-3.250 -0.3434 0.01535 0.00624 -0.0116 1.0000 0.2846
-3.000 -0.3214 0.01513 0.00604 -0.0107 1.0000 0.2941
-2.750 -0.2854 0.01487 0.00587 -0.0125 0.9889 0.3055
-2.500 -0.2451 0.01462 0.00571 -0.0150 0.9737 0.3193
-2.250 -0.2052 0.01437 0.00556 -0.0174 0.9575 0.3354
-2.000 -0.1659 0.01412 0.00541 -0.0196 0.9394 0.3541
-1.750 -0.1276 0.01386 0.00527 -0.0214 0.9157 0.3760
-1.500 -0.0886 0.01359 0.00511 -0.0231 0.8872 0.4017
-1.250 -0.0540 0.01336 0.00496 -0.0237 0.8518 0.4330
-1.000 -0.0246 0.01320 0.00485 -0.0232 0.8162 0.4685
-0.750 0.0024 0.01307 0.00480 -0.0223 0.7850 0.5076
-0.500 0.0283 0.01297 0.00477 -0.0213 0.7566 0.5492
-0.250 0.0536 0.01289 0.00478 -0.0201 0.7291 0.5910
0.000 0.0790 0.01285 0.00478 -0.0189 0.7017 0.6323
0.250 0.1041 0.01282 0.00479 -0.0177 0.6742 0.6722
0.500 0.1290 0.01281 0.00481 -0.0163 0.6469 0.7107
0.750 0.1537 0.01280 0.00483 -0.0150 0.6178 0.7488
1.000 0.1785 0.01281 0.00485 -0.0136 0.5880 0.7882
1.250 0.2045 0.01284 0.00487 -0.0124 0.5558 0.8285
1.500 0.2337 0.01291 0.00488 -0.0119 0.5197 0.8715
1.750 0.2694 0.01305 0.00489 -0.0129 0.4778 0.9155
2.000 0.3103 0.01326 0.00491 -0.0153 0.4295 0.9587
2.250 0.3494 0.01356 0.00497 -0.0176 0.3830 1.0000
2.500 0.3721 0.01390 0.00508 -0.0167 0.3491 1.0000
2.750 0.3955 0.01427 0.00524 -0.0159 0.3217 1.0000
3.000 0.4195 0.01464 0.00543 -0.0152 0.3008 1.0000
3.250 0.4438 0.01502 0.00568 -0.0145 0.2851 1.0000
3.500 0.4684 0.01541 0.00596 -0.0139 0.2723 1.0000
4.000 0.5182 0.01621 0.00660 -0.0127 0.2509 1.0000
4.250 0.5430 0.01667 0.00695 -0.0121 0.2429 1.0000
4.500 0.5685 0.01707 0.00735 -0.0116 0.2348 1.0000
4.750 0.5934 0.01757 0.00775 -0.0110 0.2280 1.0000
5.000 0.6192 0.01798 0.00821 -0.0105 0.2207 1.0000
5.250 0.6445 0.01845 0.00865 -0.0100 0.2143 1.0000
5.500 0.6698 0.01897 0.00916 -0.0095 0.2086 1.0000
5.750 0.6954 0.01944 0.00968 -0.0090 0.2020 1.0000
6.000 0.7204 0.01995 0.01015 -0.0085 0.1961 1.0000
6.250 0.7456 0.02044 0.01073 -0.0081 0.1893 1.0000
6.500 0.7704 0.02088 0.01119 -0.0075 0.1821 1.0000
6.750 0.7950 0.02138 0.01173 -0.0070 0.1757 1.0000
7.000 0.8197 0.02186 0.01231 -0.0065 0.1689 1.0000
7.250 0.8438 0.02241 0.01281 -0.0060 0.1637 1.0000
7.500 0.8683 0.02299 0.01358 -0.0054 0.1576 1.0000
7.750 0.8923 0.02357 0.01423 -0.0048 0.1522 1.0000
8.000 0.9158 0.02421 0.01487 -0.0042 0.1475 1.0000
8.250 0.9393 0.02489 0.01577 -0.0036 0.1414 1.0000
8.500 0.9622 0.02549 0.01641 -0.0030 0.1363 1.0000
8.750 0.9847 0.02626 0.01731 -0.0023 0.1312 1.0000
9.000 1.0068 0.02704 0.01825 -0.0016 0.1258 1.0000
9.250 1.0285 0.02772 0.01894 -0.0009 0.1216 1.0000
9.500 1.0492 0.02868 0.02013 -0.0001 0.1163 1.0000
9.750 1.0694 0.02933 0.02088 0.0008 0.1109 1.0000
10.000 1.0887 0.03007 0.02172 0.0016 0.1057 1.0000
10.250 1.1072 0.03083 0.02265 0.0025 0.0998 1.0000
10.500 1.1249 0.03155 0.02341 0.0034 0.0954 1.0000
10.750 1.1413 0.03260 0.02470 0.0044 0.0899 1.0000
11.000 1.1565 0.03335 0.02547 0.0055 0.0856 1.0000
11.250 1.1698 0.03460 0.02698 0.0066 0.0806 1.0000
11.500 1.1813 0.03568 0.02814 0.0079 0.0765 1.0000
11.750 1.1896 0.03709 0.02970 0.0092 0.0728 1.0000
12.000 1.1937 0.03861 0.03139 0.0109 0.0691 1.0000
12.250 1.1939 0.04021 0.03304 0.0126 0.0664 1.0000
12.500 1.1909 0.04249 0.03551 0.0137 0.0637 1.0000
12.750 1.1852 0.04525 0.03846 0.0139 0.0610 1.0000
13.000 1.1775 0.04850 0.04184 0.0132 0.0591 1.0000
13.250 1.1675 0.05236 0.04576 0.0116 0.0574 1.0000
13.500 1.1522 0.05762 0.05124 0.0089 0.0560 1.0000
13.750 1.1324 0.06407 0.05791 0.0050 0.0548 1.0000
14.000 1.1080 0.07180 0.06582 0.0001 0.0541 1.0000
14.250 1.0778 0.08111 0.07532 -0.0058 0.0538 1.0000
14.500 1.0390 0.09264 0.08706 -0.0129 0.0540 1.0000
|
Polar data table (+)
Polar graphs
<< Back to EPPLER 428 AIRFOIL (e428-il)