EPPLER 560 AIRFOIL (e560-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 560 AIRFOIL (e560-il) Reynolds number: 500,000 Max Cl/Cd: 103.28 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e560-il-500000-n5.txt Download as CSV file: xf-e560-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.250 -0.6144 0.14640 0.14335 -0.0373 1.0000 0.0128
-18.000 -0.6317 0.13872 0.13555 -0.0409 1.0000 0.0129
-17.750 -0.6430 0.13258 0.12933 -0.0438 1.0000 0.0129
-17.500 -0.6501 0.12741 0.12409 -0.0461 1.0000 0.0130
-17.250 -0.6578 0.12224 0.11885 -0.0485 1.0000 0.0131
-17.000 -0.6632 0.11765 0.11419 -0.0505 1.0000 0.0132
-16.750 -0.6678 0.11330 0.10978 -0.0523 1.0000 0.0131
-16.500 -0.6724 0.10902 0.10545 -0.0542 1.0000 0.0133
-16.250 -0.6766 0.10488 0.10125 -0.0559 1.0000 0.0133
-16.000 -0.6804 0.10093 0.09725 -0.0575 1.0000 0.0134
-15.750 -0.6849 0.09688 0.09315 -0.0591 1.0000 0.0136
-15.500 -0.6881 0.09318 0.08940 -0.0605 1.0000 0.0136
-15.250 -0.6912 0.08960 0.08578 -0.0618 1.0000 0.0137
-15.000 -0.6958 0.08581 0.08194 -0.0632 1.0000 0.0137
-14.750 -0.6998 0.08225 0.07833 -0.0644 1.0000 0.0138
-14.500 -0.7050 0.07858 0.07461 -0.0657 1.0000 0.0139
-14.250 -0.7103 0.07503 0.07101 -0.0668 1.0000 0.0140
-14.000 -0.7168 0.07143 0.06736 -0.0679 1.0000 0.0141
-13.750 -0.7234 0.06798 0.06387 -0.0689 1.0000 0.0141
-13.500 -0.7320 0.06450 0.06035 -0.0697 1.0000 0.0141
-13.250 -0.7340 0.06053 0.05632 -0.0727 0.9991 0.0142
-13.000 -0.7300 0.05620 0.05191 -0.0776 0.9969 0.0143
-12.750 -0.7264 0.05174 0.04737 -0.0831 0.9943 0.0143
-12.500 -0.7286 0.04686 0.04241 -0.0885 0.9906 0.0145
-12.250 -0.7298 0.04180 0.03727 -0.0946 0.9858 0.0147
-12.000 -0.7334 0.03717 0.03255 -0.0996 0.9789 0.0147
-11.500 -0.7133 0.02654 0.02161 -0.1163 0.9625 0.0151
-11.250 -0.6920 0.02379 0.01871 -0.1210 0.9552 0.0154
-11.000 -0.6658 0.02216 0.01697 -0.1238 0.9497 0.0157
-10.750 -0.6410 0.02088 0.01560 -0.1254 0.9433 0.0161
-10.500 -0.6144 0.01977 0.01441 -0.1268 0.9370 0.0166
-10.250 -0.5829 0.01877 0.01331 -0.1288 0.9330 0.0171
-10.000 -0.5567 0.01795 0.01240 -0.1295 0.9247 0.0175
-9.750 -0.5225 0.01692 0.01128 -0.1320 0.9201 0.0181
-9.500 -0.4896 0.01608 0.01038 -0.1338 0.9132 0.0189
-9.250 -0.4514 0.01533 0.00954 -0.1366 0.9070 0.0198
-9.000 -0.4094 0.01464 0.00877 -0.1400 0.9006 0.0211
-8.750 -0.3652 0.01391 0.00798 -0.1440 0.8921 0.0236
-8.500 -0.3159 0.01322 0.00724 -0.1491 0.8829 0.0295
-8.250 -0.2711 0.01250 0.00651 -0.1533 0.8697 0.0439
-8.000 -0.2334 0.01199 0.00597 -0.1558 0.8534 0.0572
-7.750 -0.2007 0.01161 0.00553 -0.1571 0.8352 0.0689
-7.500 -0.1711 0.01131 0.00518 -0.1577 0.8171 0.0797
-7.250 -0.1430 0.01107 0.00487 -0.1579 0.7998 0.0904
-7.000 -0.1158 0.01086 0.00460 -0.1579 0.7830 0.1019
-6.750 -0.0889 0.01066 0.00435 -0.1578 0.7674 0.1140
-6.500 -0.0621 0.01049 0.00413 -0.1577 0.7523 0.1251
-6.250 -0.0354 0.01033 0.00393 -0.1575 0.7380 0.1375
-6.000 -0.0085 0.01020 0.00375 -0.1573 0.7238 0.1489
-5.750 0.0185 0.01012 0.00361 -0.1571 0.7108 0.1579
-5.500 0.0456 0.01002 0.00347 -0.1569 0.6985 0.1682
-5.250 0.0725 0.00995 0.00334 -0.1567 0.6861 0.1794
-5.000 0.0998 0.00990 0.00323 -0.1565 0.6735 0.1888
-4.750 0.1271 0.00983 0.00314 -0.1564 0.6623 0.1990
-4.500 0.1543 0.00981 0.00305 -0.1561 0.6513 0.2064
-4.250 0.1817 0.00978 0.00297 -0.1560 0.6399 0.2141
-4.000 0.2091 0.00977 0.00289 -0.1557 0.6290 0.2205
-3.750 0.2363 0.00976 0.00283 -0.1555 0.6189 0.2279
-3.500 0.2641 0.00975 0.00277 -0.1554 0.6087 0.2342
-3.250 0.2914 0.00975 0.00273 -0.1552 0.5987 0.2409
-3.000 0.3188 0.00976 0.00269 -0.1550 0.5885 0.2479
-2.750 0.3465 0.00977 0.00265 -0.1548 0.5795 0.2539
-2.500 0.3738 0.00979 0.00263 -0.1546 0.5702 0.2610
-2.250 0.4015 0.00982 0.00261 -0.1545 0.5613 0.2672
-1.750 0.4564 0.00987 0.00260 -0.1541 0.5436 0.2807
-1.250 0.5113 0.00995 0.00262 -0.1538 0.5274 0.2936
-1.000 0.5383 0.01002 0.00264 -0.1535 0.5191 0.3000
-0.750 0.5660 0.01005 0.00266 -0.1534 0.5114 0.3061
-0.500 0.5932 0.01011 0.00270 -0.1531 0.5040 0.3132
-0.250 0.6206 0.01017 0.00273 -0.1529 0.4971 0.3196
0.000 0.6478 0.01023 0.00278 -0.1527 0.4895 0.3262
0.250 0.6747 0.01031 0.00283 -0.1524 0.4825 0.3330
0.500 0.7022 0.01037 0.00289 -0.1523 0.4759 0.3401
0.750 0.7288 0.01046 0.00296 -0.1520 0.4695 0.3471
1.000 0.7561 0.01053 0.00303 -0.1518 0.4633 0.3535
1.250 0.7830 0.01061 0.00311 -0.1515 0.4565 0.3614
1.500 0.8095 0.01072 0.00320 -0.1511 0.4506 0.3685
1.750 0.8367 0.01078 0.00329 -0.1510 0.4450 0.3754
2.000 0.8632 0.01089 0.00339 -0.1506 0.4390 0.3835
2.250 0.8896 0.01099 0.00350 -0.1503 0.4334 0.3913
2.500 0.9164 0.01108 0.00360 -0.1500 0.4276 0.3995
2.750 0.9425 0.01119 0.00372 -0.1496 0.4223 0.4072
3.000 0.9686 0.01131 0.00385 -0.1492 0.4174 0.4168
3.250 0.9952 0.01140 0.00398 -0.1489 0.4120 0.4258
3.500 1.0209 0.01153 0.00412 -0.1485 0.4066 0.4355
3.750 1.0464 0.01167 0.00427 -0.1480 0.4019 0.4457
4.000 1.0727 0.01176 0.00442 -0.1477 0.3972 0.4576
4.250 1.0983 0.01189 0.00459 -0.1472 0.3920 0.4702
4.500 1.1229 0.01205 0.00476 -0.1466 0.3871 0.4831
4.750 1.1487 0.01216 0.00494 -0.1462 0.3827 0.4987
5.000 1.1740 0.01228 0.00513 -0.1457 0.3777 0.5162
5.250 1.1983 0.01244 0.00533 -0.1450 0.3728 0.5353
5.500 1.2224 0.01259 0.00554 -0.1443 0.3685 0.5581
5.750 1.2470 0.01269 0.00575 -0.1437 0.3637 0.5845
6.000 1.2703 0.01283 0.00598 -0.1428 0.3586 0.6147
6.250 1.2924 0.01300 0.00623 -0.1418 0.3539 0.6525
6.500 1.3164 0.01309 0.00648 -0.1410 0.3491 0.6999
6.750 1.3382 0.01319 0.00675 -0.1399 0.3439 0.7604
7.000 1.3535 0.01325 0.00703 -0.1373 0.3389 0.8580
7.250 1.3715 0.01328 0.00718 -0.1352 0.3344 1.0000
7.500 1.3939 0.01352 0.00744 -0.1343 0.3287 1.0000
7.750 1.4143 0.01384 0.00773 -0.1330 0.3230 1.0000
8.000 1.4364 0.01408 0.00800 -0.1320 0.3174 1.0000
8.250 1.4569 0.01439 0.00832 -0.1308 0.3108 1.0000
8.500 1.4764 0.01474 0.00865 -0.1294 0.3048 1.0000
8.750 1.4973 0.01503 0.00897 -0.1282 0.2984 1.0000
9.000 1.5153 0.01544 0.00936 -0.1266 0.2917 1.0000
9.250 1.5350 0.01578 0.00974 -0.1254 0.2852 1.0000
9.500 1.5523 0.01622 0.01017 -0.1237 0.2776 1.0000
9.750 1.5700 0.01665 0.01061 -0.1222 0.2699 1.0000
10.000 1.5844 0.01722 0.01116 -0.1202 0.2605 1.0000
10.250 1.6003 0.01775 0.01169 -0.1184 0.2503 1.0000
10.500 1.6137 0.01840 0.01232 -0.1164 0.2404 1.0000
10.750 1.6241 0.01920 0.01308 -0.1140 0.2269 1.0000
11.000 1.6337 0.02009 0.01393 -0.1116 0.2143 1.0000
11.250 1.6411 0.02112 0.01491 -0.1091 0.2002 1.0000
11.500 1.6468 0.02230 0.01604 -0.1065 0.1858 1.0000
11.750 1.6525 0.02353 0.01724 -0.1040 0.1733 1.0000
12.000 1.6560 0.02497 0.01864 -0.1015 0.1602 1.0000
12.250 1.6588 0.02652 0.02018 -0.0991 0.1483 1.0000
12.500 1.6608 0.02823 0.02187 -0.0969 0.1375 1.0000
12.750 1.6617 0.03011 0.02373 -0.0948 0.1276 1.0000
13.000 1.6610 0.03222 0.02584 -0.0928 0.1179 1.0000
13.250 1.6614 0.03438 0.02801 -0.0912 0.1091 1.0000
13.500 1.6607 0.03673 0.03039 -0.0897 0.1018 1.0000
13.750 1.6578 0.03942 0.03308 -0.0884 0.0938 1.0000
14.000 1.6559 0.04215 0.03584 -0.0873 0.0868 1.0000
14.250 1.6511 0.04530 0.03901 -0.0864 0.0805 1.0000
14.500 1.6474 0.04846 0.04222 -0.0858 0.0738 1.0000
14.750 1.6419 0.05196 0.04575 -0.0853 0.0684 1.0000
15.000 1.6370 0.05553 0.04937 -0.0851 0.0630 1.0000
15.250 1.6312 0.05933 0.05322 -0.0851 0.0589 1.0000
15.500 1.6261 0.06315 0.05711 -0.0852 0.0547 1.0000
15.750 1.6190 0.06736 0.06137 -0.0856 0.0510 1.0000
16.000 1.6141 0.07139 0.06548 -0.0861 0.0476 1.0000
16.250 1.6068 0.07584 0.06999 -0.0867 0.0445 1.0000
16.500 1.6012 0.08016 0.07438 -0.0875 0.0419 1.0000
16.750 1.5947 0.08468 0.07897 -0.0885 0.0388 1.0000
17.000 1.5872 0.08945 0.08381 -0.0896 0.0366 1.0000
17.250 1.5820 0.09392 0.08836 -0.0908 0.0343 1.0000
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