EPPLER 560 AIRFOIL (e560-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 560 AIRFOIL (e560-il) Reynolds number: 1,000,000 Max Cl/Cd: 123.55 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e560-il-1000000-n5.txt Download as CSV file: xf-e560-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 560 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -0.7479 0.08908 0.08595 -0.0610 1.0000 0.0108
-15.500 -0.7562 0.08475 0.08158 -0.0628 1.0000 0.0108
-15.250 -0.7663 0.08027 0.07704 -0.0647 1.0000 0.0108
-15.000 -0.7704 0.07560 0.07231 -0.0679 0.9996 0.0108
-14.750 -0.7687 0.07015 0.06678 -0.0737 0.9982 0.0109
-14.500 -0.7686 0.06481 0.06135 -0.0793 0.9966 0.0110
-14.250 -0.7700 0.05962 0.05608 -0.0847 0.9952 0.0110
-14.000 -0.7731 0.05448 0.05085 -0.0901 0.9940 0.0111
-13.750 -0.7804 0.04958 0.04586 -0.0944 0.9919 0.0111
-13.500 -0.7893 0.04438 0.04057 -0.0993 0.9888 0.0111
-13.250 -0.7937 0.03902 0.03510 -0.1055 0.9857 0.0111
-13.000 -0.7897 0.03389 0.02985 -0.1130 0.9832 0.0112
-12.750 -0.8008 0.02886 0.02471 -0.1170 0.9745 0.0112
-12.500 -0.7740 0.02436 0.02005 -0.1267 0.9720 0.0113
-12.250 -0.7629 0.02186 0.01742 -0.1293 0.9635 0.0114
-11.750 -0.7211 0.01882 0.01419 -0.1324 0.9512 0.0118
-11.500 -0.6935 0.01773 0.01304 -0.1341 0.9468 0.0120
-11.250 -0.6706 0.01689 0.01213 -0.1343 0.9388 0.0123
-10.750 -0.6048 0.01532 0.01045 -0.1382 0.9282 0.0128
-10.500 -0.5648 0.01460 0.00967 -0.1413 0.9223 0.0132
-10.250 -0.5194 0.01394 0.00894 -0.1456 0.9164 0.0135
-10.000 -0.4683 0.01336 0.00828 -0.1509 0.9079 0.0140
-9.750 -0.4146 0.01282 0.00764 -0.1568 0.8957 0.0144
-9.500 -0.3739 0.01233 0.00702 -0.1600 0.8748 0.0152
-9.250 -0.3439 0.01203 0.00658 -0.1608 0.8512 0.0157
-9.000 -0.3180 0.01177 0.00620 -0.1607 0.8293 0.0164
-8.750 -0.2931 0.01156 0.00587 -0.1602 0.8083 0.0171
-8.500 -0.2685 0.01135 0.00555 -0.1597 0.7890 0.0181
-8.250 -0.2436 0.01110 0.00521 -0.1593 0.7718 0.0199
-7.750 -0.1931 0.01046 0.00449 -0.1587 0.7396 0.0342
-7.500 -0.1673 0.01015 0.00416 -0.1586 0.7250 0.0453
-7.250 -0.1409 0.00989 0.00389 -0.1584 0.7116 0.0551
-7.000 -0.1144 0.00965 0.00363 -0.1583 0.6983 0.0666
-6.750 -0.0877 0.00945 0.00341 -0.1582 0.6857 0.0776
-6.500 -0.0605 0.00922 0.00319 -0.1582 0.6736 0.0910
-6.250 -0.0331 0.00908 0.00302 -0.1581 0.6618 0.1010
-6.000 -0.0058 0.00894 0.00286 -0.1580 0.6501 0.1113
-5.750 0.0219 0.00880 0.00271 -0.1580 0.6388 0.1228
-5.500 0.0497 0.00869 0.00259 -0.1579 0.6283 0.1335
-5.250 0.0773 0.00862 0.00248 -0.1579 0.6174 0.1438
-5.000 0.1053 0.00853 0.00238 -0.1579 0.6067 0.1544
-4.750 0.1333 0.00845 0.00229 -0.1578 0.5974 0.1648
-4.500 0.1612 0.00842 0.00222 -0.1578 0.5873 0.1737
-4.250 0.1894 0.00835 0.00216 -0.1578 0.5774 0.1857
-4.000 0.2172 0.00832 0.00210 -0.1577 0.5679 0.1950
-3.750 0.2456 0.00830 0.00205 -0.1577 0.5593 0.2025
-3.500 0.2735 0.00830 0.00201 -0.1576 0.5505 0.2091
-3.250 0.3018 0.00829 0.00198 -0.1576 0.5414 0.2164
-3.000 0.3297 0.00831 0.00195 -0.1575 0.5327 0.2219
-2.750 0.3580 0.00830 0.00193 -0.1575 0.5245 0.2286
-2.500 0.3859 0.00833 0.00192 -0.1573 0.5169 0.2346
-2.250 0.4142 0.00833 0.00191 -0.1573 0.5088 0.2410
-2.000 0.4419 0.00837 0.00191 -0.1572 0.5005 0.2478
-1.750 0.4702 0.00839 0.00191 -0.1572 0.4934 0.2534
-1.500 0.4980 0.00842 0.00193 -0.1571 0.4862 0.2604
-1.250 0.5262 0.00845 0.00194 -0.1570 0.4798 0.2664
-1.000 0.5540 0.00849 0.00196 -0.1569 0.4720 0.2721
-0.750 0.5819 0.00853 0.00198 -0.1568 0.4656 0.2790
-0.500 0.6099 0.00858 0.00201 -0.1567 0.4593 0.2848
-0.250 0.6374 0.00863 0.00205 -0.1565 0.4529 0.2910
0.000 0.6654 0.00868 0.00209 -0.1565 0.4472 0.2974
0.250 0.6930 0.00873 0.00213 -0.1563 0.4406 0.3036
0.500 0.7204 0.00880 0.00219 -0.1561 0.4345 0.3105
0.750 0.7483 0.00885 0.00224 -0.1560 0.4296 0.3162
1.000 0.7758 0.00891 0.00230 -0.1559 0.4237 0.3230
1.250 0.8029 0.00900 0.00237 -0.1556 0.4179 0.3301
1.500 0.8305 0.00906 0.00243 -0.1555 0.4127 0.3356
1.750 0.8578 0.00913 0.00251 -0.1553 0.4075 0.3430
2.000 0.8846 0.00923 0.00260 -0.1550 0.4024 0.3501
2.250 0.9121 0.00929 0.00268 -0.1549 0.3980 0.3566
2.500 0.9391 0.00937 0.00277 -0.1546 0.3925 0.3637
2.750 0.9656 0.00948 0.00287 -0.1543 0.3874 0.3709
3.000 0.9927 0.00956 0.00297 -0.1541 0.3835 0.3788
3.250 1.0195 0.00964 0.00307 -0.1538 0.3788 0.3855
3.500 1.0458 0.00975 0.00318 -0.1535 0.3736 0.3935
3.750 1.0720 0.00987 0.00330 -0.1531 0.3692 0.4022
4.000 1.0988 0.00994 0.00342 -0.1528 0.3652 0.4105
4.250 1.1249 0.01006 0.00354 -0.1524 0.3602 0.4191
4.500 1.1504 0.01019 0.00369 -0.1520 0.3553 0.4290
5.000 1.2024 0.01040 0.00396 -0.1512 0.3466 0.4508
5.250 1.2275 0.01053 0.00412 -0.1506 0.3415 0.4622
5.500 1.2525 0.01067 0.00429 -0.1501 0.3367 0.4765
5.750 1.2778 0.01078 0.00444 -0.1496 0.3322 0.4922
6.250 1.3251 0.01108 0.00481 -0.1480 0.3215 0.5287
6.500 1.3493 0.01119 0.00499 -0.1473 0.3164 0.5522
6.750 1.3723 0.01135 0.00520 -0.1464 0.3103 0.5764
7.000 1.3952 0.01152 0.00543 -0.1455 0.3046 0.6083
7.250 1.4184 0.01166 0.00566 -0.1446 0.2983 0.6450
7.500 1.4399 0.01187 0.00594 -0.1435 0.2913 0.6873
7.750 1.4628 0.01199 0.00620 -0.1426 0.2857 0.7436
8.000 1.4832 0.01212 0.00651 -0.1412 0.2786 0.8253
8.250 1.4974 0.01212 0.00672 -0.1384 0.2730 1.0000
8.500 1.5183 0.01241 0.00699 -0.1372 0.2649 1.0000
8.750 1.5377 0.01275 0.00730 -0.1358 0.2564 1.0000
9.000 1.5551 0.01319 0.00768 -0.1340 0.2441 1.0000
9.250 1.5717 0.01368 0.00810 -0.1322 0.2303 1.0000
9.500 1.5878 0.01418 0.00854 -0.1303 0.2169 1.0000
9.750 1.6014 0.01479 0.00907 -0.1280 0.2019 1.0000
10.000 1.6137 0.01547 0.00967 -0.1256 0.1864 1.0000
10.250 1.6240 0.01624 0.01036 -0.1229 0.1702 1.0000
10.500 1.6347 0.01700 0.01106 -0.1204 0.1569 1.0000
10.750 1.6446 0.01781 0.01182 -0.1178 0.1448 1.0000
11.000 1.6533 0.01870 0.01266 -0.1152 0.1326 1.0000
11.250 1.6615 0.01964 0.01356 -0.1126 0.1216 1.0000
11.500 1.6697 0.02062 0.01451 -0.1101 0.1127 1.0000
11.750 1.6743 0.02184 0.01569 -0.1074 0.1017 1.0000
12.000 1.6775 0.02320 0.01701 -0.1046 0.0911 1.0000
12.250 1.6817 0.02457 0.01837 -0.1022 0.0827 1.0000
12.500 1.6858 0.02603 0.01982 -0.0999 0.0750 1.0000
12.750 1.6890 0.02764 0.02142 -0.0978 0.0688 1.0000
13.000 1.6905 0.02947 0.02324 -0.0957 0.0618 1.0000
13.250 1.6921 0.03138 0.02517 -0.0938 0.0557 1.0000
13.500 1.6914 0.03360 0.02740 -0.0921 0.0500 1.0000
13.750 1.6918 0.03586 0.02968 -0.0906 0.0451 1.0000
14.000 1.6924 0.03820 0.03205 -0.0894 0.0415 1.0000
14.250 1.6917 0.04078 0.03467 -0.0883 0.0379 1.0000
14.500 1.6914 0.04344 0.03737 -0.0875 0.0350 1.0000
14.750 1.6910 0.04622 0.04020 -0.0868 0.0324 1.0000
15.000 1.6883 0.04933 0.04336 -0.0863 0.0298 1.0000
15.250 1.6858 0.05256 0.04665 -0.0860 0.0273 1.0000
15.500 1.6815 0.05613 0.05027 -0.0858 0.0249 1.0000
15.750 1.6781 0.05967 0.05387 -0.0858 0.0228 1.0000
16.000 1.6727 0.06358 0.05784 -0.0860 0.0208 1.0000
16.250 1.6673 0.06760 0.06193 -0.0864 0.0185 1.0000
16.500 1.6606 0.07193 0.06632 -0.0870 0.0166 1.0000
16.750 1.6519 0.07662 0.07108 -0.0878 0.0143 1.0000
17.000 1.6449 0.08120 0.07572 -0.0887 0.0124 1.0000
17.250 1.6361 0.08613 0.08072 -0.0898 0.0106 1.0000
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Polar data table (+)
Polar graphs
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