EPPLER 748 AIRFOIL (e748-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 748 AIRFOIL (e748-il) Reynolds number: 500,000 Max Cl/Cd: 94.17 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e748-il-500000.txt Download as CSV file: xf-e748-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.000 -0.6030 0.12961 0.12658 -0.0514 1.0000 0.0199
-17.750 -0.6404 0.11824 0.11502 -0.0575 1.0000 0.0198
-17.500 -0.6694 0.10918 0.10579 -0.0622 1.0000 0.0197
-17.250 -0.6899 0.10213 0.09859 -0.0658 1.0000 0.0196
-17.000 -0.7092 0.09551 0.09183 -0.0692 1.0000 0.0196
-16.750 -0.7250 0.08974 0.08592 -0.0720 1.0000 0.0195
-16.500 -0.7366 0.08490 0.08096 -0.0741 1.0000 0.0195
-16.250 -0.7457 0.08060 0.07655 -0.0757 1.0000 0.0194
-16.000 -0.7549 0.07638 0.07220 -0.0775 1.0000 0.0195
-15.750 -0.7596 0.07296 0.06869 -0.0785 1.0000 0.0195
-15.500 -0.7663 0.06937 0.06498 -0.0797 1.0000 0.0196
-15.250 -0.7697 0.06638 0.06189 -0.0804 1.0000 0.0197
-15.000 -0.7719 0.06363 0.05907 -0.0808 1.0000 0.0197
-14.750 -0.7732 0.06110 0.05646 -0.0811 1.0000 0.0198
-14.500 -0.7758 0.05850 0.05377 -0.0815 1.0000 0.0199
-14.250 -0.7751 0.05643 0.05162 -0.0812 1.0000 0.0199
-14.000 -0.7723 0.05475 0.04990 -0.0802 1.0000 0.0200
-13.750 -0.7679 0.05339 0.04852 -0.0788 1.0000 0.0202
-13.500 -0.7650 0.05192 0.04703 -0.0777 1.0000 0.0203
-13.250 -0.7626 0.05053 0.04565 -0.0765 1.0000 0.0205
-13.000 -0.7621 0.04909 0.04420 -0.0752 1.0000 0.0206
-12.750 -0.7634 0.04765 0.04276 -0.0737 1.0000 0.0208
-12.500 -0.7487 0.04594 0.04103 -0.0754 0.9985 0.0211
-12.250 -0.7241 0.04411 0.03917 -0.0789 0.9956 0.0214
-12.000 -0.6980 0.04239 0.03741 -0.0826 0.9931 0.0217
-11.750 -0.6767 0.04055 0.03553 -0.0854 0.9890 0.0221
-11.500 -0.6519 0.03875 0.03369 -0.0889 0.9853 0.0225
-11.250 -0.6240 0.03699 0.03187 -0.0929 0.9827 0.0230
-11.000 -0.6043 0.03525 0.03008 -0.0952 0.9768 0.0233
-10.750 -0.5825 0.03323 0.02805 -0.0987 0.9719 0.0238
-10.500 -0.5712 0.03109 0.02592 -0.1005 0.9630 0.0244
-10.250 -0.5492 0.02895 0.02375 -0.1042 0.9572 0.0249
-10.000 -0.5394 0.02678 0.02156 -0.1053 0.9444 0.0255
-9.750 -0.5255 0.02457 0.01929 -0.1072 0.9308 0.0259
-9.500 -0.5055 0.02241 0.01707 -0.1101 0.9173 0.0266
-9.000 -0.4229 0.01775 0.01222 -0.1243 0.8978 0.0294
-8.750 -0.3685 0.01645 0.01081 -0.1317 0.8854 0.0321
-8.500 -0.3131 0.01510 0.00938 -0.1394 0.8684 0.0379
-8.250 -0.2720 0.01393 0.00818 -0.1440 0.8437 0.0541
-8.000 -0.2422 0.01307 0.00731 -0.1459 0.8172 0.0777
-7.750 -0.2150 0.01250 0.00669 -0.1467 0.7932 0.0994
-7.500 -0.1889 0.01198 0.00615 -0.1472 0.7720 0.1224
-7.250 -0.1627 0.01144 0.00561 -0.1477 0.7532 0.1516
-7.000 -0.1360 0.01080 0.00504 -0.1484 0.7356 0.1926
-6.750 -0.1088 0.01010 0.00447 -0.1493 0.7189 0.2498
-6.500 -0.0809 0.00977 0.00429 -0.1498 0.7031 0.3091
-6.250 -0.0528 0.00984 0.00433 -0.1497 0.6885 0.3350
-6.000 -0.0246 0.01000 0.00440 -0.1496 0.6754 0.3501
-5.750 0.0034 0.01018 0.00443 -0.1495 0.6625 0.3602
-5.500 0.0316 0.01037 0.00455 -0.1493 0.6499 0.3681
-5.250 0.0600 0.01055 0.00458 -0.1492 0.6383 0.3752
-5.000 0.0876 0.01077 0.00475 -0.1489 0.6272 0.3809
-4.750 0.1160 0.01097 0.00489 -0.1488 0.6170 0.3867
-4.500 0.1444 0.01121 0.00494 -0.1488 0.6072 0.3912
-4.250 0.1723 0.01122 0.00497 -0.1486 0.5976 0.3956
-4.000 0.1998 0.01141 0.00509 -0.1483 0.5885 0.3993
-3.750 0.2283 0.01153 0.00517 -0.1483 0.5799 0.4032
-3.500 0.2564 0.01174 0.00524 -0.1482 0.5719 0.4074
-3.250 0.2851 0.01176 0.00520 -0.1483 0.5644 0.4110
-3.000 0.3127 0.01178 0.00520 -0.1481 0.5566 0.4138
-2.750 0.3407 0.01185 0.00523 -0.1480 0.5496 0.4162
-2.500 0.3690 0.01189 0.00523 -0.1480 0.5426 0.4185
-2.250 0.3971 0.01196 0.00520 -0.1480 0.5362 0.4206
-2.000 0.4258 0.01196 0.00516 -0.1481 0.5303 0.4226
-1.750 0.4544 0.01198 0.00511 -0.1482 0.5240 0.4244
-1.500 0.4825 0.01206 0.00508 -0.1482 0.5180 0.4260
-1.250 0.5112 0.01208 0.00505 -0.1484 0.5125 0.4272
-1.000 0.5398 0.01202 0.00495 -0.1485 0.5071 0.4286
-0.750 0.5678 0.01197 0.00485 -0.1486 0.5019 0.4304
-0.500 0.5958 0.01202 0.00487 -0.1486 0.4970 0.4321
-0.250 0.6241 0.01201 0.00487 -0.1487 0.4922 0.4336
0.000 0.6521 0.01204 0.00487 -0.1486 0.4871 0.4350
0.250 0.6799 0.01213 0.00490 -0.1486 0.4823 0.4365
0.500 0.7081 0.01218 0.00493 -0.1487 0.4780 0.4380
0.750 0.7364 0.01220 0.00495 -0.1487 0.4738 0.4395
1.000 0.7643 0.01226 0.00498 -0.1487 0.4695 0.4411
1.250 0.7919 0.01237 0.00503 -0.1487 0.4651 0.4428
1.500 0.8199 0.01248 0.00510 -0.1487 0.4609 0.4445
1.750 0.8477 0.01253 0.00516 -0.1487 0.4568 0.4458
2.000 0.8755 0.01256 0.00517 -0.1487 0.4529 0.4472
2.250 0.9029 0.01260 0.00520 -0.1487 0.4490 0.4491
2.500 0.9305 0.01276 0.00531 -0.1487 0.4448 0.4508
2.750 0.9577 0.01278 0.00540 -0.1485 0.4415 0.4525
3.000 0.9848 0.01284 0.00548 -0.1484 0.4375 0.4542
3.250 1.0117 0.01294 0.00558 -0.1482 0.4337 0.4561
3.500 1.0386 0.01309 0.00570 -0.1481 0.4300 0.4580
3.750 1.0658 0.01326 0.00585 -0.1480 0.4263 0.4600
4.000 1.0923 0.01333 0.00597 -0.1478 0.4228 0.4622
4.250 1.1187 0.01344 0.00609 -0.1475 0.4191 0.4641
4.500 1.1450 0.01355 0.00619 -0.1473 0.4156 0.4661
4.750 1.1713 0.01370 0.00634 -0.1471 0.4118 0.4686
5.000 1.1975 0.01384 0.00652 -0.1469 0.4083 0.4708
5.250 1.2232 0.01393 0.00667 -0.1465 0.4050 0.4732
5.500 1.2487 0.01405 0.00683 -0.1461 0.4015 0.4757
5.750 1.2737 0.01421 0.00699 -0.1457 0.3980 0.4783
6.000 1.2990 0.01445 0.00720 -0.1453 0.3942 0.4809
6.250 1.3241 0.01463 0.00741 -0.1449 0.3910 0.4833
6.500 1.3486 0.01472 0.00759 -0.1443 0.3878 0.4866
6.750 1.3723 0.01484 0.00777 -0.1437 0.3842 0.4901
7.000 1.3952 0.01501 0.00797 -0.1428 0.3807 0.4938
7.250 1.4187 0.01528 0.00822 -0.1422 0.3771 0.4975
7.500 1.4410 0.01547 0.00846 -0.1412 0.3739 0.5011
7.750 1.4625 0.01560 0.00868 -0.1402 0.3705 0.5052
8.000 1.4841 0.01576 0.00893 -0.1391 0.3669 0.5097
8.250 1.5053 0.01600 0.00918 -0.1381 0.3634 0.5146
8.500 1.5277 0.01636 0.00951 -0.1373 0.3593 0.5198
8.750 1.5479 0.01652 0.00981 -0.1361 0.3562 0.5257
9.000 1.5682 0.01673 0.01011 -0.1349 0.3525 0.5328
9.250 1.5882 0.01698 0.01042 -0.1337 0.3488 0.5405
9.500 1.6076 0.01730 0.01077 -0.1325 0.3450 0.5500
9.750 1.6273 0.01764 0.01119 -0.1314 0.3412 0.5618
10.000 1.6463 0.01789 0.01157 -0.1301 0.3374 0.5772
10.250 1.6649 0.01817 0.01198 -0.1288 0.3334 0.5980
10.500 1.6819 0.01855 0.01245 -0.1273 0.3292 0.6278
10.750 1.6995 0.01895 0.01300 -0.1260 0.3250 0.6723
11.000 1.7166 0.01921 0.01353 -0.1246 0.3208 0.7434
11.250 1.7231 0.01925 0.01396 -0.1209 0.3168 1.0000
11.500 1.7366 0.01987 0.01455 -0.1191 0.3122 1.0000
11.750 1.7515 0.02045 0.01518 -0.1176 0.3077 1.0000
12.000 1.7662 0.02102 0.01582 -0.1160 0.3029 1.0000
12.250 1.7780 0.02176 0.01657 -0.1142 0.2980 1.0000
12.500 1.7884 0.02263 0.01745 -0.1123 0.2930 1.0000
12.750 1.8012 0.02337 0.01828 -0.1108 0.2873 1.0000
13.000 1.8089 0.02444 0.01935 -0.1089 0.2813 1.0000
13.250 1.8174 0.02553 0.02049 -0.1072 0.2750 1.0000
13.500 1.8248 0.02674 0.02174 -0.1055 0.2681 1.0000
13.750 1.8283 0.02829 0.02329 -0.1036 0.2616 1.0000
14.000 1.8360 0.02966 0.02473 -0.1022 0.2548 1.0000
14.250 1.8356 0.03166 0.02673 -0.1004 0.2482 1.0000
14.500 1.8419 0.03330 0.02844 -0.0993 0.2416 1.0000
14.750 1.8395 0.03571 0.03086 -0.0978 0.2343 1.0000
15.000 1.8407 0.03794 0.03315 -0.0968 0.2272 1.0000
15.250 1.8353 0.04088 0.03611 -0.0957 0.2197 1.0000
15.500 1.8332 0.04364 0.03892 -0.0949 0.2127 1.0000
15.750 1.8255 0.04709 0.04240 -0.0941 0.2054 1.0000
16.000 1.8196 0.05047 0.04584 -0.0936 0.1986 1.0000
16.250 1.8092 0.05448 0.04989 -0.0933 0.1912 1.0000
16.500 1.8004 0.05846 0.05392 -0.0932 0.1843 1.0000
16.750 1.7882 0.06297 0.05846 -0.0934 0.1771 1.0000
17.000 1.7770 0.06749 0.06303 -0.0937 0.1702 1.0000
17.250 1.7630 0.07253 0.06811 -0.0942 0.1631 1.0000
17.500 1.7511 0.07738 0.07301 -0.0949 0.1565 1.0000
17.750 1.7364 0.08275 0.07842 -0.0959 0.1495 1.0000
18.000 1.7244 0.08783 0.08354 -0.0969 0.1431 1.0000
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