EPPLER 398 AIRFOIL (e398-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 398 AIRFOIL (e398-il) Reynolds number: 1,000,000 Max Cl/Cd: 147.04 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e398-il-1000000-n5.txt Download as CSV file: xf-e398-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 398 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
------ -------- --------- --------- -------- -------- --------
-14.500 -0.5668 0.08145 0.07893 -0.0831 0.9948 0.0033
-14.250 -0.5960 0.07196 0.06931 -0.0899 0.9919 0.0032
-14.000 -0.6284 0.06213 0.05935 -0.0976 0.9872 0.0032
-13.750 -0.6573 0.05324 0.05033 -0.1048 0.9792 0.0031
-13.500 -0.6882 0.04343 0.04033 -0.1139 0.9605 0.0031
-13.250 -0.6784 0.03319 0.02979 -0.1317 0.9446 0.0031
-13.000 -0.6397 0.02641 0.02270 -0.1490 0.9245 0.0031
-12.750 -0.6387 0.02293 0.01889 -0.1539 0.8842 0.0033
-12.500 -0.6313 0.02153 0.01728 -0.1538 0.8634 0.0032
-12.250 -0.6195 0.02040 0.01599 -0.1534 0.8480 0.0034
-11.750 -0.5864 0.01857 0.01388 -0.1528 0.8240 0.0035
-11.500 -0.5668 0.01782 0.01300 -0.1526 0.8139 0.0036
-11.000 -0.5239 0.01647 0.01142 -0.1522 0.7947 0.0038
-10.750 -0.5013 0.01585 0.01068 -0.1521 0.7865 0.0039
-10.500 -0.4774 0.01530 0.01003 -0.1521 0.7786 0.0040
-10.250 -0.4532 0.01481 0.00943 -0.1520 0.7707 0.0042
-10.000 -0.4283 0.01431 0.00885 -0.1520 0.7629 0.0043
-9.750 -0.4037 0.01378 0.00821 -0.1520 0.7554 0.0046
-9.500 -0.3778 0.01332 0.00768 -0.1521 0.7486 0.0049
-9.250 -0.3519 0.01293 0.00720 -0.1522 0.7418 0.0053
-9.000 -0.3254 0.01257 0.00677 -0.1523 0.7355 0.0057
-8.750 -0.2986 0.01224 0.00637 -0.1524 0.7285 0.0061
-8.500 -0.2720 0.01187 0.00592 -0.1525 0.7222 0.0070
-8.250 -0.2447 0.01155 0.00555 -0.1526 0.7163 0.0079
-8.000 -0.2176 0.01124 0.00519 -0.1528 0.7103 0.0094
-7.750 -0.1901 0.01095 0.00486 -0.1529 0.7049 0.0113
-7.500 -0.1624 0.01068 0.00455 -0.1531 0.6988 0.0137
-7.250 -0.1349 0.01043 0.00426 -0.1533 0.6930 0.0170
-7.000 -0.1069 0.01017 0.00399 -0.1535 0.6881 0.0208
-6.750 -0.0788 0.00994 0.00374 -0.1537 0.6828 0.0255
-6.500 -0.0509 0.00974 0.00351 -0.1539 0.6776 0.0301
-6.250 -0.0225 0.00954 0.00331 -0.1541 0.6728 0.0356
-6.000 0.0058 0.00933 0.00310 -0.1544 0.6676 0.0428
-5.750 0.0339 0.00914 0.00291 -0.1546 0.6627 0.0513
-5.500 0.0624 0.00896 0.00274 -0.1549 0.6587 0.0607
-5.250 0.0911 0.00879 0.00258 -0.1551 0.6541 0.0699
-5.000 0.1195 0.00864 0.00244 -0.1554 0.6493 0.0797
-4.750 0.1479 0.00852 0.00231 -0.1556 0.6449 0.0897
-4.500 0.1768 0.00840 0.00220 -0.1558 0.6410 0.0993
-4.000 0.2341 0.00819 0.00199 -0.1563 0.6325 0.1215
-3.750 0.2627 0.00810 0.00191 -0.1565 0.6284 0.1343
-3.500 0.2917 0.00799 0.00183 -0.1568 0.6247 0.1485
-3.250 0.3205 0.00790 0.00177 -0.1571 0.6208 0.1626
-3.000 0.3491 0.00785 0.00171 -0.1573 0.6168 0.1751
-2.750 0.3777 0.00779 0.00167 -0.1575 0.6130 0.1896
-2.500 0.4067 0.00772 0.00163 -0.1578 0.6095 0.2051
-2.250 0.4355 0.00767 0.00160 -0.1580 0.6056 0.2194
-2.000 0.4640 0.00763 0.00157 -0.1582 0.6017 0.2341
-1.500 0.5214 0.00757 0.00155 -0.1586 0.5947 0.2630
-1.250 0.5502 0.00754 0.00155 -0.1589 0.5910 0.2780
-1.000 0.5787 0.00753 0.00155 -0.1591 0.5871 0.2919
-0.750 0.6070 0.00753 0.00157 -0.1592 0.5835 0.3056
-0.500 0.6357 0.00752 0.00158 -0.1594 0.5802 0.3203
-0.250 0.6644 0.00751 0.00160 -0.1596 0.5766 0.3352
0.000 0.6929 0.00751 0.00163 -0.1598 0.5729 0.3490
0.250 0.7210 0.00753 0.00167 -0.1599 0.5691 0.3639
0.500 0.7494 0.00754 0.00171 -0.1601 0.5656 0.3792
1.000 0.8063 0.00756 0.00180 -0.1604 0.5581 0.4111
1.250 0.8343 0.00759 0.00185 -0.1605 0.5541 0.4280
1.500 0.8623 0.00762 0.00192 -0.1606 0.5503 0.4455
1.750 0.8907 0.00762 0.00198 -0.1608 0.5464 0.4639
2.000 0.9187 0.00765 0.00205 -0.1609 0.5420 0.4829
2.250 0.9462 0.00770 0.00214 -0.1609 0.5374 0.5030
2.500 0.9742 0.00773 0.00222 -0.1610 0.5331 0.5237
3.000 1.0292 0.00783 0.00241 -0.1611 0.5224 0.5657
3.250 1.0567 0.00787 0.00251 -0.1611 0.5172 0.5879
3.500 1.0840 0.00793 0.00262 -0.1611 0.5108 0.6108
3.750 1.1106 0.00802 0.00274 -0.1610 0.5039 0.6343
4.250 1.1637 0.00818 0.00301 -0.1607 0.4885 0.6847
4.500 1.1903 0.00826 0.00315 -0.1605 0.4808 0.7114
4.750 1.2158 0.00837 0.00331 -0.1602 0.4723 0.7410
5.250 1.2651 0.00863 0.00368 -0.1591 0.4487 0.8057
5.500 1.2881 0.00877 0.00388 -0.1583 0.4362 0.8456
5.750 1.3072 0.00889 0.00408 -0.1565 0.4230 0.9032
6.000 1.3265 0.00904 0.00426 -0.1549 0.4080 1.0000
6.250 1.3481 0.00939 0.00452 -0.1539 0.3886 1.0000
6.500 1.3685 0.00978 0.00483 -0.1527 0.3686 1.0000
6.750 1.3879 0.01021 0.00515 -0.1513 0.3469 1.0000
7.000 1.4049 0.01072 0.00555 -0.1495 0.3226 1.0000
7.250 1.4190 0.01125 0.00596 -0.1472 0.2970 1.0000
7.500 1.4305 0.01184 0.00643 -0.1443 0.2723 1.0000
7.750 1.4399 0.01254 0.00697 -0.1412 0.2453 1.0000
8.000 1.4500 0.01321 0.00753 -0.1383 0.2214 1.0000
8.250 1.4577 0.01399 0.00819 -0.1351 0.1964 1.0000
8.500 1.4641 0.01486 0.00893 -0.1318 0.1728 1.0000
8.750 1.4731 0.01565 0.00963 -0.1290 0.1547 1.0000
9.000 1.4823 0.01645 0.01038 -0.1264 0.1396 1.0000
9.250 1.4908 0.01734 0.01121 -0.1238 0.1252 1.0000
9.500 1.4989 0.01829 0.01212 -0.1213 0.1122 1.0000
9.750 1.5062 0.01934 0.01312 -0.1188 0.0996 1.0000
10.000 1.5120 0.02054 0.01426 -0.1163 0.0864 1.0000
10.250 1.5181 0.02179 0.01547 -0.1139 0.0750 1.0000
10.500 1.5242 0.02311 0.01675 -0.1117 0.0650 1.0000
10.750 1.5299 0.02452 0.01814 -0.1097 0.0561 1.0000
11.000 1.5343 0.02610 0.01968 -0.1076 0.0466 1.0000
11.250 1.5402 0.02763 0.02120 -0.1058 0.0403 1.0000
11.500 1.5459 0.02925 0.02281 -0.1041 0.0342 1.0000
11.750 1.5515 0.03092 0.02449 -0.1026 0.0290 1.0000
12.000 1.5555 0.03279 0.02635 -0.1010 0.0236 1.0000
12.250 1.5619 0.03452 0.02810 -0.0997 0.0205 1.0000
12.500 1.5674 0.03638 0.02998 -0.0985 0.0176 1.0000
12.750 1.5737 0.03822 0.03185 -0.0974 0.0154 1.0000
13.000 1.5800 0.04011 0.03377 -0.0964 0.0136 1.0000
13.250 1.5860 0.04208 0.03579 -0.0955 0.0122 1.0000
13.500 1.5921 0.04409 0.03784 -0.0946 0.0110 1.0000
13.750 1.5982 0.04615 0.03994 -0.0939 0.0099 1.0000
14.000 1.6035 0.04834 0.04218 -0.0932 0.0090 1.0000
14.250 1.6092 0.05054 0.04443 -0.0926 0.0081 1.0000
14.500 1.6140 0.05288 0.04682 -0.0921 0.0072 1.0000
14.750 1.6190 0.05525 0.04924 -0.0916 0.0066 1.0000
15.000 1.6233 0.05775 0.05180 -0.0912 0.0059 1.0000
15.250 1.6269 0.06037 0.05447 -0.0909 0.0053 1.0000
15.500 1.6310 0.06299 0.05715 -0.0907 0.0049 1.0000
15.750 1.6343 0.06575 0.05998 -0.0906 0.0044 1.0000
16.000 1.6375 0.06859 0.06288 -0.0905 0.0040 1.0000
16.250 1.6395 0.07162 0.06598 -0.0905 0.0037 1.0000
16.500 1.6422 0.07458 0.06902 -0.0906 0.0035 1.0000
16.750 1.6445 0.07767 0.07217 -0.0908 0.0032 1.0000
17.000 1.6454 0.08102 0.07559 -0.0911 0.0029 1.0000
17.250 1.6462 0.08440 0.07905 -0.0915 0.0027 1.0000
17.500 1.6466 0.08789 0.08261 -0.0920 0.0025 1.0000
17.750 1.6470 0.09143 0.08624 -0.0926 0.0024 1.0000
18.000 1.6476 0.09499 0.08988 -0.0933 0.0023 1.0000
18.250 1.6470 0.09877 0.09374 -0.0941 0.0021 1.0000
18.500 1.6458 0.10268 0.09774 -0.0951 0.0020 1.0000
18.750 1.6442 0.10666 0.10180 -0.0961 0.0019 1.0000
19.000 1.6419 0.11080 0.10603 -0.0973 0.0017 1.0000
19.250 1.6387 0.11516 0.11047 -0.0987 0.0016 1.0000
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