EPPLER 748 AIRFOIL (e748-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 748 AIRFOIL (e748-il) Reynolds number: 200,000 Max Cl/Cd: 63.77 at α=10.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e748-il-200000.txt Download as CSV file: xf-e748-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -0.5701 0.09255 0.08815 -0.0735 1.0000 0.0368
-14.500 -0.5951 0.08573 0.08120 -0.0768 1.0000 0.0367
-14.250 -0.6134 0.08027 0.07565 -0.0790 1.0000 0.0364
-14.000 -0.6367 0.07479 0.07003 -0.0814 1.0000 0.0363
-13.750 -0.6571 0.06996 0.06507 -0.0831 1.0000 0.0361
-13.500 -0.6736 0.06593 0.06092 -0.0841 1.0000 0.0360
-13.250 -0.6952 0.06185 0.05667 -0.0852 1.0000 0.0362
-13.000 -0.7108 0.05851 0.05321 -0.0855 1.0000 0.0362
-12.750 -0.7260 0.05546 0.05002 -0.0853 1.0000 0.0362
-12.500 -0.7412 0.05279 0.04722 -0.0846 1.0000 0.0363
-12.250 -0.7570 0.05048 0.04480 -0.0834 1.0000 0.0364
-12.000 -0.7696 0.04859 0.04283 -0.0814 1.0000 0.0364
-11.750 -0.7883 0.04696 0.04111 -0.0787 1.0000 0.0365
-11.500 -0.8074 0.04560 0.03968 -0.0760 0.9993 0.0366
-11.000 -0.7451 0.04122 0.03507 -0.0821 0.9892 0.0377
-10.750 -0.7096 0.03978 0.03362 -0.0846 0.9843 0.0384
-10.500 -0.6772 0.03829 0.03207 -0.0872 0.9782 0.0394
-10.250 -0.6438 0.03692 0.03063 -0.0897 0.9722 0.0404
-10.000 -0.6131 0.03556 0.02918 -0.0916 0.9646 0.0416
-9.750 -0.5782 0.03437 0.02795 -0.0935 0.9588 0.0428
-9.500 -0.5517 0.03321 0.02690 -0.0943 0.9491 0.0444
-9.250 -0.5154 0.03164 0.02533 -0.0981 0.9436 0.0470
-9.000 -0.4917 0.03002 0.02368 -0.0997 0.9315 0.0495
-8.750 -0.4663 0.02811 0.02184 -0.1025 0.9199 0.0527
-8.500 -0.4290 0.02567 0.01940 -0.1081 0.9143 0.0580
-8.250 -0.4009 0.02324 0.01697 -0.1125 0.9018 0.0658
-8.000 -0.3655 0.02059 0.01440 -0.1183 0.8916 0.0861
-7.750 -0.3198 0.01806 0.01208 -0.1256 0.8840 0.1285
-7.500 -0.2748 0.01606 0.01033 -0.1318 0.8726 0.1869
-7.250 -0.2222 0.01465 0.00940 -0.1386 0.8629 0.2838
-7.000 -0.1760 0.01492 0.00968 -0.1417 0.8483 0.3335
-6.750 -0.1337 0.01550 0.01005 -0.1438 0.8313 0.3595
-6.500 -0.0961 0.01641 0.01081 -0.1447 0.8132 0.3759
-6.250 -0.0634 0.01741 0.01176 -0.1442 0.7951 0.3848
-6.000 -0.0328 0.01780 0.01194 -0.1444 0.7777 0.3939
-5.750 -0.0046 0.01855 0.01266 -0.1432 0.7615 0.3989
-5.500 0.0247 0.01873 0.01256 -0.1437 0.7460 0.4089
-5.250 0.0513 0.01934 0.01315 -0.1423 0.7318 0.4130
-5.000 0.0785 0.02006 0.01381 -0.1409 0.7187 0.4176
-4.750 0.1063 0.01995 0.01345 -0.1416 0.7051 0.4274
-4.500 0.1315 0.02030 0.01379 -0.1402 0.6933 0.4310
-4.250 0.1574 0.02087 0.01431 -0.1387 0.6823 0.4346
-4.000 0.1828 0.02106 0.01443 -0.1380 0.6706 0.4404
-3.750 0.2126 0.02067 0.01377 -0.1393 0.6609 0.4481
-3.500 0.2367 0.02087 0.01399 -0.1379 0.6507 0.4508
-3.250 0.2634 0.02103 0.01406 -0.1373 0.6421 0.4540
-3.000 0.2900 0.02088 0.01382 -0.1374 0.6325 0.4584
-2.750 0.3236 0.02039 0.01297 -0.1399 0.6244 0.4651
-2.500 0.3484 0.02015 0.01275 -0.1393 0.6156 0.4673
-2.250 0.3757 0.02018 0.01269 -0.1390 0.6087 0.4695
-2.000 0.4020 0.02011 0.01261 -0.1387 0.6009 0.4720
-1.750 0.4300 0.01997 0.01236 -0.1390 0.5936 0.4748
-1.500 0.4600 0.01983 0.01207 -0.1398 0.5870 0.4783
-1.250 0.4894 0.01955 0.01168 -0.1407 0.5797 0.4812
-1.000 0.5206 0.01936 0.01129 -0.1419 0.5736 0.4841
-0.750 0.5482 0.01925 0.01116 -0.1420 0.5677 0.4860
-0.500 0.5752 0.01915 0.01105 -0.1420 0.5612 0.4878
-0.250 0.6039 0.01910 0.01091 -0.1422 0.5555 0.4895
0.000 0.6326 0.01910 0.01085 -0.1426 0.5500 0.4915
0.250 0.6600 0.01907 0.01081 -0.1427 0.5441 0.4941
0.500 0.6895 0.01904 0.01069 -0.1432 0.5390 0.4967
0.750 0.7211 0.01909 0.01058 -0.1443 0.5343 0.4989
1.000 0.7482 0.01905 0.01053 -0.1444 0.5285 0.5009
1.250 0.7770 0.01902 0.01044 -0.1448 0.5232 0.5027
1.500 0.8060 0.01901 0.01038 -0.1452 0.5187 0.5045
1.750 0.8341 0.01913 0.01050 -0.1454 0.5144 0.5067
2.000 0.8602 0.01920 0.01062 -0.1452 0.5093 0.5091
2.250 0.8882 0.01926 0.01066 -0.1453 0.5045 0.5114
2.500 0.9180 0.01936 0.01067 -0.1458 0.5003 0.5137
2.750 0.9460 0.01953 0.01082 -0.1461 0.4958 0.5161
3.000 0.9726 0.01964 0.01096 -0.1460 0.4912 0.5185
3.250 1.0011 0.01977 0.01104 -0.1464 0.4868 0.5207
3.500 1.0301 0.01984 0.01109 -0.1467 0.4829 0.5229
3.750 1.0577 0.02007 0.01133 -0.1468 0.4789 0.5255
4.000 1.0818 0.02022 0.01159 -0.1463 0.4742 0.5285
4.250 1.1086 0.02039 0.01179 -0.1462 0.4700 0.5316
4.500 1.1375 0.02056 0.01190 -0.1466 0.4662 0.5348
4.750 1.1686 0.02088 0.01211 -0.1474 0.4625 0.5380
5.000 1.1906 0.02104 0.01243 -0.1465 0.4581 0.5406
5.250 1.2154 0.02122 0.01271 -0.1461 0.4539 0.5435
5.500 1.2424 0.02140 0.01291 -0.1461 0.4500 0.5469
5.750 1.2723 0.02164 0.01310 -0.1466 0.4464 0.5510
6.000 1.2969 0.02199 0.01351 -0.1462 0.4426 0.5554
6.250 1.3193 0.02225 0.01390 -0.1455 0.4383 0.5595
6.500 1.3442 0.02246 0.01420 -0.1451 0.4343 0.5639
6.750 1.3722 0.02266 0.01440 -0.1453 0.4307 0.5690
7.000 1.4030 0.02306 0.01473 -0.1460 0.4272 0.5747
7.250 1.4205 0.02338 0.01527 -0.1444 0.4231 0.5794
7.500 1.4421 0.02366 0.01568 -0.1435 0.4189 0.5852
7.750 1.4679 0.02389 0.01594 -0.1433 0.4150 0.5925
8.000 1.4975 0.02412 0.01618 -0.1438 0.4116 0.5999
8.250 1.5193 0.02457 0.01676 -0.1430 0.4079 0.6087
8.500 1.5362 0.02493 0.01732 -0.1414 0.4034 0.6179
8.750 1.5588 0.02520 0.01768 -0.1406 0.3993 0.6302
9.000 1.5862 0.02538 0.01792 -0.1407 0.3957 0.6444
9.250 1.6132 0.02577 0.01837 -0.1409 0.3920 0.6625
9.500 1.6243 0.02619 0.01909 -0.1383 0.3875 0.6839
9.750 1.6423 0.02646 0.01955 -0.1368 0.3832 0.7168
10.000 1.6642 0.02649 0.01975 -0.1357 0.3794 0.7803
10.250 1.6828 0.02639 0.01977 -0.1337 0.3761 1.0000
10.500 1.6877 0.02704 0.02062 -0.1303 0.3717 1.0000
10.750 1.7008 0.02751 0.02117 -0.1282 0.3671 1.0000
11.000 1.7229 0.02776 0.02138 -0.1275 0.3629 1.0000
11.250 1.7523 0.02813 0.02166 -0.1280 0.3587 1.0000
11.500 1.7461 0.02886 0.02261 -0.1229 0.3543 1.0000
11.750 1.7537 0.02938 0.02321 -0.1200 0.3496 1.0000
12.000 1.7751 0.02961 0.02339 -0.1192 0.3452 1.0000
12.250 1.7872 0.03024 0.02407 -0.1172 0.3407 1.0000
12.500 1.7819 0.03123 0.02523 -0.1129 0.3359 1.0000
12.750 1.7917 0.03180 0.02584 -0.1107 0.3310 1.0000
13.000 1.8185 0.03201 0.02594 -0.1108 0.3261 1.0000
13.250 1.8023 0.03363 0.02781 -0.1058 0.3214 1.0000
13.500 1.8034 0.03474 0.02901 -0.1031 0.3162 1.0000
13.750 1.8233 0.03509 0.02928 -0.1024 0.3111 1.0000
14.000 1.8117 0.03708 0.03146 -0.0990 0.3061 1.0000
14.250 1.8066 0.03884 0.03336 -0.0965 0.3005 1.0000
14.500 1.8230 0.03942 0.03385 -0.0957 0.2951 1.0000
14.750 1.8065 0.04226 0.03691 -0.0930 0.2896 1.0000
15.000 1.8000 0.04460 0.03934 -0.0913 0.2837 1.0000
15.250 1.8125 0.04558 0.04025 -0.0905 0.2778 1.0000
15.500 1.7893 0.04969 0.04461 -0.0889 0.2718 1.0000
15.750 1.7888 0.05195 0.04688 -0.0881 0.2656 1.0000
16.000 1.7806 0.05519 0.05021 -0.0874 0.2593 1.0000
16.250 1.7664 0.05924 0.05438 -0.0870 0.2526 1.0000
16.500 1.7692 0.06151 0.05663 -0.0867 0.2460 1.0000
16.750 1.7469 0.06695 0.06226 -0.0870 0.2391 1.0000
17.000 1.7532 0.06892 0.06413 -0.0868 0.2321 1.0000
17.250 1.7266 0.07540 0.07084 -0.0878 0.2249 1.0000
17.500 1.7323 0.07753 0.07285 -0.0879 0.2175 1.0000
17.750 1.7048 0.08457 0.08012 -0.0895 0.2102 1.0000
18.000 1.7090 0.08699 0.08242 -0.0897 0.2027 1.0000
18.250 1.6831 0.09418 0.08983 -0.0917 0.1953 1.0000
18.500 1.6846 0.09710 0.09264 -0.0923 0.1878 1.0000
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Polar data table (+)
Polar graphs
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