EPPLER 399 AIRFOIL (e399-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 399 AIRFOIL (e399-il) Reynolds number: 1,000,000 Max Cl/Cd: 161.48 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e399-il-1000000.txt Download as CSV file: xf-e399-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 399 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
------ -------- --------- --------- -------- -------- --------
-14.750 -0.6082 0.08602 0.08354 -0.0713 1.0000 0.0055
-14.500 -0.6273 0.08004 0.07748 -0.0738 1.0000 0.0056
-14.250 -0.6453 0.07464 0.07203 -0.0757 1.0000 0.0056
-14.000 -0.6530 0.06781 0.06509 -0.0820 0.9990 0.0055
-13.750 -0.6601 0.06086 0.05802 -0.0893 0.9971 0.0055
-13.500 -0.6630 0.05437 0.05142 -0.0968 0.9948 0.0054
-13.250 -0.6664 0.04788 0.04480 -0.1044 0.9916 0.0055
-13.000 -0.6677 0.04158 0.03836 -0.1122 0.9865 0.0055
-12.750 -0.6587 0.03582 0.03246 -0.1211 0.9826 0.0054
-12.500 -0.6563 0.03061 0.02709 -0.1279 0.9711 0.0055
-12.250 -0.6458 0.02626 0.02259 -0.1347 0.9568 0.0056
-12.000 -0.6125 0.02227 0.01836 -0.1459 0.9451 0.0056
-11.750 -0.5772 0.02024 0.01615 -0.1519 0.9332 0.0057
-11.500 -0.5479 0.01884 0.01456 -0.1550 0.9169 0.0059
-11.250 -0.5260 0.01784 0.01338 -0.1559 0.8992 0.0060
-11.000 -0.5059 0.01707 0.01246 -0.1558 0.8836 0.0060
-10.750 -0.4893 0.01593 0.01114 -0.1555 0.8695 0.0063
-10.500 -0.4693 0.01505 0.01013 -0.1553 0.8575 0.0067
-10.250 -0.4466 0.01448 0.00944 -0.1551 0.8466 0.0072
-10.000 -0.4230 0.01396 0.00881 -0.1549 0.8360 0.0076
-9.750 -0.3987 0.01349 0.00823 -0.1548 0.8267 0.0081
-9.500 -0.3749 0.01285 0.00751 -0.1547 0.8173 0.0094
-9.250 -0.3497 0.01236 0.00693 -0.1547 0.8091 0.0109
-9.000 -0.3241 0.01193 0.00643 -0.1547 0.8006 0.0130
-8.750 -0.2982 0.01146 0.00592 -0.1548 0.7927 0.0169
-8.500 -0.2718 0.01110 0.00553 -0.1549 0.7846 0.0213
-8.250 -0.2450 0.01080 0.00519 -0.1550 0.7773 0.0257
-8.000 -0.2178 0.01051 0.00488 -0.1551 0.7699 0.0302
-7.750 -0.1907 0.01026 0.00458 -0.1552 0.7631 0.0348
-7.500 -0.1629 0.01000 0.00431 -0.1554 0.7563 0.0399
-7.250 -0.1355 0.00978 0.00405 -0.1555 0.7494 0.0456
-7.000 -0.1075 0.00954 0.00381 -0.1558 0.7430 0.0523
-6.750 -0.0796 0.00932 0.00359 -0.1560 0.7363 0.0607
-6.500 -0.0518 0.00911 0.00337 -0.1561 0.7303 0.0711
-6.250 -0.0234 0.00888 0.00318 -0.1565 0.7245 0.0832
-6.000 0.0048 0.00870 0.00300 -0.1567 0.7184 0.0952
-5.750 0.0330 0.00854 0.00283 -0.1569 0.7127 0.1070
-5.500 0.0617 0.00836 0.00268 -0.1572 0.7070 0.1200
-5.250 0.0901 0.00822 0.00254 -0.1574 0.7015 0.1335
-5.000 0.1186 0.00810 0.00242 -0.1577 0.6964 0.1474
-4.750 0.1475 0.00796 0.00230 -0.1580 0.6911 0.1620
-4.500 0.1761 0.00786 0.00220 -0.1582 0.6859 0.1768
-4.250 0.2045 0.00778 0.00212 -0.1584 0.6809 0.1926
-4.000 0.2337 0.00766 0.00204 -0.1588 0.6765 0.2096
-3.750 0.2625 0.00757 0.00197 -0.1590 0.6716 0.2261
-3.500 0.2909 0.00752 0.00191 -0.1592 0.6667 0.2420
-3.250 0.3199 0.00746 0.00187 -0.1595 0.6625 0.2581
-3.000 0.3489 0.00739 0.00183 -0.1598 0.6582 0.2739
-2.750 0.3777 0.00736 0.00180 -0.1600 0.6537 0.2885
-2.250 0.4352 0.00732 0.00177 -0.1605 0.6454 0.3162
-2.000 0.4642 0.00728 0.00175 -0.1607 0.6414 0.3295
-1.750 0.4928 0.00727 0.00174 -0.1609 0.6371 0.3418
-1.500 0.5212 0.00731 0.00175 -0.1610 0.6328 0.3546
-1.250 0.5502 0.00728 0.00176 -0.1613 0.6294 0.3674
-1.000 0.5792 0.00725 0.00177 -0.1616 0.6256 0.3808
-0.750 0.6078 0.00726 0.00178 -0.1618 0.6216 0.3940
-0.500 0.6361 0.00729 0.00180 -0.1619 0.6176 0.4071
-0.250 0.6648 0.00730 0.00184 -0.1621 0.6140 0.4212
0.000 0.6937 0.00728 0.00187 -0.1624 0.6104 0.4361
0.250 0.7222 0.00729 0.00190 -0.1626 0.6066 0.4514
0.500 0.7505 0.00732 0.00195 -0.1627 0.6026 0.4666
0.750 0.7787 0.00736 0.00201 -0.1629 0.5987 0.4826
1.000 0.8075 0.00735 0.00205 -0.1631 0.5954 0.4994
1.250 0.8360 0.00736 0.00211 -0.1633 0.5915 0.5166
1.500 0.8641 0.00740 0.00217 -0.1634 0.5876 0.5344
1.750 0.8918 0.00747 0.00226 -0.1634 0.5832 0.5528
2.000 0.9204 0.00746 0.00232 -0.1636 0.5799 0.5719
2.250 0.9487 0.00748 0.00240 -0.1638 0.5759 0.5918
2.500 0.9764 0.00752 0.00248 -0.1638 0.5716 0.6119
2.750 1.0037 0.00761 0.00259 -0.1638 0.5670 0.6323
3.000 1.0320 0.00761 0.00268 -0.1639 0.5632 0.6539
3.250 1.0597 0.00763 0.00277 -0.1640 0.5586 0.6759
3.500 1.0867 0.00770 0.00287 -0.1639 0.5536 0.6980
3.750 1.1138 0.00775 0.00299 -0.1638 0.5486 0.7212
4.000 1.1412 0.00778 0.00309 -0.1638 0.5432 0.7457
4.250 1.1674 0.00785 0.00322 -0.1635 0.5376 0.7705
4.500 1.1938 0.00790 0.00335 -0.1633 0.5322 0.7987
4.750 1.2198 0.00793 0.00347 -0.1629 0.5262 0.8284
5.000 1.2435 0.00801 0.00361 -0.1621 0.5197 0.8629
5.250 1.2651 0.00798 0.00372 -0.1608 0.5136 0.9120
5.500 1.2867 0.00799 0.00378 -0.1594 0.5063 1.0000
5.750 1.3128 0.00813 0.00392 -0.1592 0.4987 1.0000
6.000 1.3380 0.00829 0.00407 -0.1589 0.4896 1.0000
6.250 1.3634 0.00845 0.00422 -0.1585 0.4801 1.0000
6.500 1.3871 0.00867 0.00441 -0.1579 0.4694 1.0000
6.750 1.4105 0.00889 0.00460 -0.1572 0.4569 1.0000
7.000 1.4334 0.00913 0.00482 -0.1564 0.4433 1.0000
7.250 1.4549 0.00942 0.00506 -0.1553 0.4281 1.0000
7.500 1.4743 0.00978 0.00535 -0.1539 0.4101 1.0000
7.750 1.4907 0.01019 0.00568 -0.1519 0.3892 1.0000
8.000 1.5033 0.01071 0.00608 -0.1492 0.3639 1.0000
8.250 1.5136 0.01132 0.00656 -0.1462 0.3361 1.0000
8.500 1.5225 0.01200 0.00711 -0.1430 0.3091 1.0000
8.750 1.5310 0.01273 0.00770 -0.1398 0.2837 1.0000
9.000 1.5387 0.01350 0.00836 -0.1366 0.2587 1.0000
9.250 1.5441 0.01440 0.00913 -0.1332 0.2342 1.0000
9.500 1.5489 0.01536 0.00998 -0.1298 0.2103 1.0000
9.750 1.5530 0.01641 0.01092 -0.1264 0.1890 1.0000
10.000 1.5566 0.01755 0.01196 -0.1232 0.1679 1.0000
10.250 1.5592 0.01882 0.01314 -0.1201 0.1493 1.0000
10.500 1.5614 0.02019 0.01443 -0.1171 0.1308 1.0000
10.750 1.5647 0.02160 0.01577 -0.1144 0.1153 1.0000
11.000 1.5678 0.02310 0.01721 -0.1119 0.1013 1.0000
11.250 1.5697 0.02477 0.01882 -0.1095 0.0875 1.0000
11.500 1.5732 0.02643 0.02044 -0.1074 0.0767 1.0000
11.750 1.5764 0.02817 0.02215 -0.1054 0.0668 1.0000
12.000 1.5800 0.02996 0.02391 -0.1036 0.0585 1.0000
12.250 1.5832 0.03185 0.02579 -0.1019 0.0510 1.0000
12.500 1.5857 0.03387 0.02779 -0.1003 0.0438 1.0000
12.750 1.5888 0.03592 0.02984 -0.0989 0.0380 1.0000
13.000 1.5919 0.03804 0.03196 -0.0976 0.0329 1.0000
13.250 1.5966 0.04007 0.03401 -0.0965 0.0291 1.0000
13.500 1.6010 0.04219 0.03615 -0.0955 0.0257 1.0000
13.750 1.6047 0.04445 0.03844 -0.0945 0.0228 1.0000
14.000 1.6084 0.04676 0.04078 -0.0937 0.0203 1.0000
14.250 1.6131 0.04903 0.04308 -0.0930 0.0183 1.0000
14.500 1.6163 0.05150 0.04559 -0.0924 0.0165 1.0000
14.750 1.6207 0.05391 0.04806 -0.0919 0.0150 1.0000
15.000 1.6233 0.05658 0.05077 -0.0914 0.0136 1.0000
15.250 1.6278 0.05907 0.05331 -0.0910 0.0125 1.0000
15.500 1.6300 0.06189 0.05618 -0.0907 0.0114 1.0000
15.750 1.6332 0.06463 0.05899 -0.0905 0.0105 1.0000
16.000 1.6358 0.06753 0.06194 -0.0904 0.0095 1.0000
16.250 1.6365 0.07072 0.06518 -0.0904 0.0087 1.0000
16.500 1.6398 0.07360 0.06813 -0.0905 0.0079 1.0000
16.750 1.6400 0.07696 0.07155 -0.0907 0.0072 1.0000
17.000 1.6401 0.08039 0.07506 -0.0910 0.0067 1.0000
17.250 1.6417 0.08365 0.07840 -0.0913 0.0061 1.0000
17.500 1.6407 0.08735 0.08216 -0.0918 0.0056 1.0000
17.750 1.6378 0.09138 0.08627 -0.0925 0.0052 1.0000
18.000 1.6384 0.09493 0.08991 -0.0931 0.0048 1.0000
18.250 1.6372 0.09883 0.09389 -0.0940 0.0045 1.0000
18.500 1.6353 0.10287 0.09801 -0.0950 0.0042 1.0000
18.750 1.6306 0.10738 0.10260 -0.0962 0.0040 1.0000
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Polar data table (+)
Polar graphs
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