EPPLER EC 86(-3)-914 AIRFOIL (ec863914-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER EC 86(-3)-914 AIRFOIL (ec863914-il) Reynolds number: 1,000,000 Max Cl/Cd: 150.87 at α=1° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ec863914-il-1000000.txt Download as CSV file: xf-ec863914-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER EC 86(-3)-914 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.1842 0.12009 0.11814 -0.1177 0.9742 0.0067
-14.000 -0.1850 0.11359 0.11164 -0.1203 0.9738 0.0067
-6.500 -0.1333 0.01521 0.01027 -0.1521 0.9097 0.0091
-6.250 -0.0959 0.01429 0.00924 -0.1547 0.9092 0.0084
-6.000 -0.0595 0.01369 0.00856 -0.1570 0.9088 0.0084
-5.750 -0.0227 0.01318 0.00799 -0.1593 0.9085 0.0086
-5.500 0.0138 0.01277 0.00753 -0.1613 0.9082 0.0084
-5.250 0.0507 0.01237 0.00709 -0.1635 0.9079 0.0088
-5.000 0.0876 0.01202 0.00671 -0.1656 0.9077 0.0092
-4.750 0.1242 0.01176 0.00641 -0.1676 0.9074 0.0090
-4.500 0.1611 0.01150 0.00612 -0.1696 0.9071 0.0089
-4.250 0.1978 0.01126 0.00585 -0.1716 0.9068 0.0089
-4.000 0.2343 0.01101 0.00559 -0.1735 0.9064 0.0090
-3.750 0.2714 0.01075 0.00531 -0.1755 0.9061 0.0094
-3.500 0.3110 0.01040 0.00499 -0.1780 0.9057 0.0151
-3.250 0.3636 0.00912 0.00442 -0.1846 0.9056 0.2105
-3.000 0.4057 0.00863 0.00406 -0.1878 0.9048 0.2454
-2.750 0.4507 0.00807 0.00362 -0.1915 0.9036 0.2808
-2.500 0.4768 0.00778 0.00348 -0.1914 0.8988 0.3198
-2.250 0.5135 0.00733 0.00323 -0.1936 0.8961 0.3846
-2.000 0.5537 0.00685 0.00289 -0.1964 0.8935 0.4412
-1.750 0.5964 0.00629 0.00252 -0.1998 0.8906 0.5138
-1.500 0.6265 0.00609 0.00254 -0.2005 0.8863 0.5919
-1.250 0.6554 0.00603 0.00253 -0.2006 0.8823 0.6180
-1.000 0.6867 0.00595 0.00245 -0.2013 0.8789 0.6314
-0.750 0.7185 0.00590 0.00239 -0.2020 0.8757 0.6407
-0.500 0.7425 0.00593 0.00243 -0.2012 0.8697 0.6482
-0.250 0.7729 0.00587 0.00236 -0.2016 0.8642 0.6541
0.000 0.7981 0.00590 0.00240 -0.2010 0.8570 0.6597
0.250 0.8281 0.00588 0.00234 -0.2013 0.8495 0.6652
0.500 0.8532 0.00589 0.00237 -0.2007 0.8382 0.6691
0.750 0.8801 0.00591 0.00236 -0.2003 0.8224 0.6726
1.000 0.9052 0.00600 0.00234 -0.1996 0.7930 0.6761
1.250 0.9231 0.00634 0.00241 -0.1974 0.7450 0.6793
1.500 0.9354 0.00679 0.00263 -0.1940 0.6999 0.6822
1.750 0.9444 0.00723 0.00289 -0.1900 0.6581 0.6849
2.000 0.9520 0.00770 0.00317 -0.1858 0.6154 0.6879
2.250 0.9632 0.00823 0.00350 -0.1824 0.5732 0.6918
2.500 0.9774 0.00875 0.00382 -0.1797 0.5327 0.6957
2.750 0.9934 0.00922 0.00414 -0.1774 0.4944 0.6991
3.000 1.0105 0.00970 0.00447 -0.1754 0.4594 0.7024
3.250 1.0295 0.01015 0.00477 -0.1737 0.4259 0.7054
3.500 1.0494 0.01060 0.00507 -0.1723 0.3941 0.7082
3.750 1.0699 0.01103 0.00536 -0.1711 0.3644 0.7112
4.000 1.0900 0.01143 0.00568 -0.1697 0.3386 0.7143
4.250 1.1107 0.01184 0.00600 -0.1684 0.3172 0.7172
4.500 1.1326 0.01219 0.00628 -0.1675 0.2987 0.7192
4.750 1.1551 0.01253 0.00656 -0.1666 0.2818 0.7205
5.000 1.1778 0.01287 0.00684 -0.1659 0.2665 0.7215
5.250 1.2005 0.01321 0.00712 -0.1651 0.2528 0.7226
5.500 1.2229 0.01357 0.00742 -0.1643 0.2389 0.7235
5.750 1.2451 0.01396 0.00773 -0.1634 0.2242 0.7244
6.000 1.2670 0.01433 0.00806 -0.1626 0.2103 0.7257
6.250 1.2886 0.01470 0.00840 -0.1617 0.2003 0.7268
6.500 1.3112 0.01501 0.00872 -0.1609 0.1927 0.7279
6.750 1.3330 0.01538 0.00907 -0.1600 0.1834 0.7289
7.000 1.3540 0.01582 0.00945 -0.1590 0.1698 0.7299
7.250 1.3744 0.01631 0.00985 -0.1579 0.1536 0.7310
7.500 1.3927 0.01697 0.01036 -0.1565 0.1289 0.7321
7.750 1.3923 0.01919 0.01196 -0.1523 0.0405 0.7332
8.000 1.4007 0.02083 0.01337 -0.1493 0.0059 0.7343
8.250 1.4199 0.02145 0.01405 -0.1481 0.0050 0.7356
8.500 1.4382 0.02214 0.01479 -0.1467 0.0043 0.7368
8.750 1.4541 0.02305 0.01578 -0.1449 0.0037 0.7379
9.000 1.4697 0.02398 0.01680 -0.1431 0.0034 0.7388
9.250 1.4867 0.02475 0.01764 -0.1417 0.0033 0.7401
9.500 1.5026 0.02560 0.01857 -0.1401 0.0031 0.7412
9.750 1.5175 0.02651 0.01956 -0.1383 0.0029 0.7424
10.000 1.5321 0.02745 0.02057 -0.1366 0.0028 0.7435
10.250 1.5456 0.02847 0.02167 -0.1348 0.0026 0.7447
10.500 1.5577 0.02960 0.02286 -0.1329 0.0025 0.7460
10.750 1.5685 0.03086 0.02421 -0.1308 0.0024 0.7472
11.000 1.5777 0.03225 0.02569 -0.1286 0.0024 0.7485
11.250 1.5838 0.03392 0.02746 -0.1261 0.0023 0.7498
11.500 1.5879 0.03578 0.02943 -0.1235 0.0022 0.7511
11.750 1.5889 0.03795 0.03171 -0.1207 0.0022 0.7523
12.000 1.5866 0.04050 0.03439 -0.1178 0.0021 0.7534
12.250 1.5830 0.04327 0.03730 -0.1151 0.0021 0.7547
12.500 1.5713 0.04703 0.04123 -0.1120 0.0020 0.7558
12.750 1.5664 0.05027 0.04461 -0.1099 0.0020 0.7569
13.000 1.5678 0.05295 0.04740 -0.1085 0.0020 0.7581
13.250 1.5701 0.05564 0.05019 -0.1073 0.0020 0.7594
13.500 1.5715 0.05854 0.05321 -0.1064 0.0020 0.7607
13.750 1.5729 0.06156 0.05633 -0.1057 0.0019 0.7621
14.000 1.5740 0.06474 0.05962 -0.1052 0.0019 0.7635
14.250 1.5651 0.06941 0.06444 -0.1048 0.0019 0.7646
14.500 1.5613 0.07359 0.06873 -0.1049 0.0019 0.7658
14.750 1.5591 0.07768 0.07294 -0.1053 0.0018 0.7670
15.000 1.5527 0.08259 0.07799 -0.1061 0.0018 0.7681
15.250 1.5460 0.08772 0.08326 -0.1072 0.0018 0.7693
15.500 1.5375 0.09329 0.08897 -0.1087 0.0018 0.7704
15.750 1.5299 0.09890 0.09472 -0.1105 0.0017 0.7715
16.000 1.5252 0.10418 0.10013 -0.1125 0.0016 0.7727
16.250 1.5172 0.11011 0.10618 -0.1149 0.0016 0.7739
16.500 1.5065 0.11657 0.11278 -0.1176 0.0016 0.7749
16.750 1.5002 0.12242 0.11875 -0.1204 0.0015 0.7761
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Polar data table (+)
Polar graphs
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