EPPLER 748 AIRFOIL (e748-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 748 AIRFOIL (e748-il) Reynolds number: 200,000 Max Cl/Cd: 66.92 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e748-il-200000-n5.txt Download as CSV file: xf-e748-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 748 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.750 -0.5920 0.11278 0.10798 -0.0604 1.0000 0.0204
-16.500 -0.6161 0.10466 0.09967 -0.0644 1.0000 0.0204
-16.250 -0.6318 0.09849 0.09333 -0.0673 1.0000 0.0204
-16.000 -0.6378 0.09427 0.08905 -0.0691 1.0000 0.0206
-15.750 -0.6453 0.08988 0.08455 -0.0709 1.0000 0.0206
-15.500 -0.6504 0.08604 0.08065 -0.0723 1.0000 0.0209
-15.250 -0.6552 0.08238 0.07690 -0.0735 1.0000 0.0210
-15.000 -0.6588 0.07900 0.07345 -0.0745 1.0000 0.0211
-14.750 -0.6614 0.07589 0.07026 -0.0752 1.0000 0.0213
-14.500 -0.6633 0.07297 0.06727 -0.0758 1.0000 0.0215
-14.250 -0.6643 0.07029 0.06452 -0.0762 1.0000 0.0217
-14.000 -0.6643 0.06783 0.06201 -0.0763 1.0000 0.0218
-13.750 -0.6648 0.06542 0.05954 -0.0763 1.0000 0.0221
-13.500 -0.6638 0.06330 0.05737 -0.0761 1.0000 0.0222
-13.250 -0.6631 0.06126 0.05528 -0.0757 1.0000 0.0224
-13.000 -0.6626 0.05930 0.05327 -0.0752 1.0000 0.0227
-12.750 -0.6625 0.05743 0.05135 -0.0745 1.0000 0.0229
-12.500 -0.6625 0.05569 0.04957 -0.0736 1.0000 0.0232
-12.250 -0.6615 0.05397 0.04780 -0.0729 0.9997 0.0234
-12.000 -0.6410 0.05180 0.04562 -0.0763 0.9963 0.0237
-11.750 -0.6211 0.04955 0.04336 -0.0799 0.9925 0.0243
-11.500 -0.6026 0.04738 0.04116 -0.0829 0.9875 0.0248
-11.250 -0.5819 0.04522 0.03896 -0.0865 0.9830 0.0254
-11.000 -0.5659 0.04319 0.03689 -0.0888 0.9761 0.0260
-10.250 -0.5290 0.03713 0.03073 -0.0940 0.9452 0.0285
-9.750 -0.5192 0.03327 0.02681 -0.0945 0.9114 0.0302
-9.500 -0.5040 0.03119 0.02465 -0.0965 0.8976 0.0314
-9.250 -0.4819 0.02871 0.02211 -0.1006 0.8832 0.0331
-9.000 -0.4510 0.02634 0.01963 -0.1060 0.8693 0.0358
-8.750 -0.4100 0.02386 0.01705 -0.1137 0.8554 0.0401
-8.500 -0.3623 0.02172 0.01479 -0.1220 0.8399 0.0484
-8.250 -0.3202 0.02013 0.01314 -0.1279 0.8220 0.0607
-8.000 -0.2834 0.01893 0.01187 -0.1321 0.8031 0.0759
-7.750 -0.2511 0.01798 0.01086 -0.1348 0.7842 0.0932
-7.500 -0.2215 0.01715 0.00997 -0.1367 0.7658 0.1120
-7.250 -0.1932 0.01642 0.00920 -0.1382 0.7486 0.1354
-7.000 -0.1654 0.01557 0.00839 -0.1397 0.7329 0.1699
-6.750 -0.1374 0.01455 0.00757 -0.1416 0.7183 0.2333
-6.500 -0.1092 0.01434 0.00767 -0.1423 0.7037 0.3044
-6.250 -0.0807 0.01453 0.00779 -0.1423 0.6900 0.3322
-6.000 -0.0521 0.01467 0.00776 -0.1423 0.6774 0.3464
-5.750 -0.0234 0.01472 0.00757 -0.1425 0.6652 0.3576
-5.500 0.0044 0.01495 0.00774 -0.1421 0.6540 0.3650
-5.250 0.0333 0.01502 0.00754 -0.1424 0.6431 0.3741
-5.000 0.0604 0.01527 0.00777 -0.1419 0.6322 0.3793
-4.750 0.0883 0.01545 0.00782 -0.1417 0.6224 0.3856
-4.500 0.1170 0.01550 0.00767 -0.1420 0.6128 0.3922
-4.250 0.1440 0.01573 0.00788 -0.1414 0.6042 0.3964
-4.000 0.1715 0.01590 0.00797 -0.1412 0.5951 0.4014
-3.750 0.1998 0.01594 0.00784 -0.1413 0.5869 0.4064
-3.500 0.2284 0.01590 0.00765 -0.1415 0.5785 0.4101
-3.250 0.2556 0.01594 0.00762 -0.1413 0.5715 0.4123
-3.000 0.2834 0.01595 0.00759 -0.1412 0.5641 0.4144
-2.750 0.3111 0.01596 0.00751 -0.1411 0.5568 0.4166
-2.500 0.3391 0.01596 0.00741 -0.1412 0.5502 0.4189
-2.250 0.3674 0.01593 0.00730 -0.1413 0.5432 0.4213
-2.000 0.3957 0.01592 0.00716 -0.1415 0.5372 0.4236
-1.750 0.4243 0.01590 0.00703 -0.1417 0.5315 0.4255
-1.500 0.4530 0.01589 0.00690 -0.1420 0.5252 0.4275
-1.250 0.4805 0.01589 0.00684 -0.1419 0.5194 0.4291
-1.000 0.5082 0.01591 0.00682 -0.1419 0.5141 0.4306
-0.750 0.5361 0.01592 0.00681 -0.1419 0.5086 0.4321
-0.500 0.5638 0.01595 0.00680 -0.1419 0.5035 0.4335
-0.250 0.5915 0.01602 0.00678 -0.1419 0.4989 0.4351
0.000 0.6195 0.01605 0.00680 -0.1419 0.4938 0.4368
0.250 0.6472 0.01609 0.00681 -0.1419 0.4886 0.4389
0.500 0.6748 0.01617 0.00682 -0.1419 0.4839 0.4411
0.750 0.7028 0.01627 0.00683 -0.1420 0.4801 0.4431
1.000 0.7308 0.01632 0.00688 -0.1421 0.4755 0.4448
1.250 0.7585 0.01640 0.00691 -0.1421 0.4709 0.4464
1.500 0.7854 0.01647 0.00696 -0.1420 0.4665 0.4479
1.750 0.8126 0.01659 0.00704 -0.1419 0.4627 0.4494
2.000 0.8397 0.01666 0.00717 -0.1418 0.4584 0.4510
2.250 0.8667 0.01676 0.00729 -0.1417 0.4544 0.4528
2.500 0.8936 0.01689 0.00741 -0.1416 0.4504 0.4550
2.750 0.9204 0.01704 0.00752 -0.1415 0.4467 0.4573
3.000 0.9472 0.01719 0.00766 -0.1413 0.4429 0.4597
3.250 0.9738 0.01731 0.00782 -0.1412 0.4387 0.4619
3.500 1.0003 0.01746 0.00797 -0.1410 0.4349 0.4639
3.750 1.0266 0.01761 0.00812 -0.1408 0.4314 0.4659
4.000 1.0530 0.01778 0.00828 -0.1406 0.4281 0.4678
4.250 1.0786 0.01793 0.00850 -0.1403 0.4242 0.4699
4.500 1.1040 0.01809 0.00874 -0.1400 0.4202 0.4722
4.750 1.1294 0.01827 0.00895 -0.1396 0.4166 0.4747
5.000 1.1549 0.01847 0.00915 -0.1393 0.4132 0.4776
5.250 1.1807 0.01871 0.00936 -0.1390 0.4100 0.4808
5.750 1.2291 0.01909 0.00993 -0.1380 0.4024 0.4866
6.000 1.2532 0.01930 0.01021 -0.1374 0.3988 0.4895
6.250 1.2772 0.01953 0.01045 -0.1369 0.3954 0.4927
6.500 1.3014 0.01980 0.01072 -0.1364 0.3922 0.4962
6.750 1.3240 0.02004 0.01108 -0.1356 0.3885 0.4999
7.000 1.3463 0.02029 0.01142 -0.1348 0.3848 0.5034
7.250 1.3683 0.02053 0.01174 -0.1339 0.3811 0.5071
7.500 1.3903 0.02080 0.01204 -0.1331 0.3779 0.5114
7.750 1.4120 0.02110 0.01239 -0.1322 0.3748 0.5165
8.000 1.4308 0.02139 0.01281 -0.1308 0.3709 0.5216
8.250 1.4497 0.02169 0.01324 -0.1294 0.3671 0.5271
8.500 1.4692 0.02201 0.01363 -0.1282 0.3636 0.5338
8.750 1.4894 0.02236 0.01400 -0.1271 0.3603 0.5407
9.000 1.5078 0.02274 0.01451 -0.1258 0.3568 0.5482
9.250 1.5247 0.02315 0.01506 -0.1243 0.3527 0.5570
9.500 1.5418 0.02355 0.01558 -0.1228 0.3488 0.5666
9.750 1.5592 0.02397 0.01606 -0.1214 0.3452 0.5785
10.000 1.5766 0.02444 0.01661 -0.1201 0.3416 0.5930
10.250 1.5907 0.02496 0.01734 -0.1183 0.3374 0.6103
10.750 1.6188 0.02604 0.01868 -0.1149 0.3293 0.6616
11.000 1.6327 0.02660 0.01937 -0.1132 0.3256 0.7027
11.250 1.6417 0.02724 0.02030 -0.1109 0.3212 0.7645
11.500 1.6416 0.02762 0.02099 -0.1067 0.3171 1.0000
11.750 1.6527 0.02848 0.02185 -0.1051 0.3128 1.0000
12.000 1.6632 0.02942 0.02283 -0.1035 0.3087 1.0000
12.250 1.6705 0.03056 0.02411 -0.1017 0.3036 1.0000
12.500 1.6777 0.03175 0.02536 -0.1000 0.2986 1.0000
12.750 1.6857 0.03295 0.02654 -0.0985 0.2942 1.0000
13.000 1.6897 0.03451 0.02826 -0.0969 0.2888 1.0000
13.250 1.6934 0.03614 0.02996 -0.0954 0.2833 1.0000
13.500 1.6977 0.03779 0.03161 -0.0941 0.2785 1.0000
13.750 1.6985 0.03988 0.03385 -0.0928 0.2727 1.0000
14.000 1.6989 0.04205 0.03610 -0.0917 0.2669 1.0000
14.250 1.6992 0.04433 0.03842 -0.0908 0.2615 1.0000
14.500 1.6967 0.04705 0.04126 -0.0900 0.2553 1.0000
14.750 1.6940 0.04983 0.04407 -0.0893 0.2493 1.0000
15.000 1.6904 0.05289 0.04724 -0.0889 0.2433 1.0000
15.250 1.6843 0.05633 0.05075 -0.0886 0.2366 1.0000
15.500 1.6786 0.05981 0.05429 -0.0885 0.2305 1.0000
15.750 1.6707 0.06375 0.05833 -0.0887 0.2236 1.0000
16.000 1.6632 0.06766 0.06225 -0.0889 0.2172 1.0000
16.250 1.6538 0.07207 0.06679 -0.0894 0.2102 1.0000
16.500 1.6447 0.07641 0.07114 -0.0900 0.2035 1.0000
16.750 1.6352 0.08105 0.07590 -0.0908 0.1967 1.0000
17.000 1.6256 0.08570 0.08057 -0.0918 0.1898 1.0000
17.250 1.6161 0.09050 0.08546 -0.0929 0.1832 1.0000
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Polar data table (+)
Polar graphs
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