EPPLER 748 AIRFOIL (e748-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 748 AIRFOIL (e748-il) Reynolds number: 50,000 Max Cl/Cd: 21.54 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e748-il-50000-n5.txt Download as CSV file: xf-e748-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.3761 0.11035 0.10288 -0.0602 1.0000 0.0635
-12.500 -0.4142 0.09907 0.09155 -0.0653 1.0000 0.0634
-12.250 -0.4513 0.08962 0.08198 -0.0695 1.0000 0.0632
-12.000 -0.4805 0.08262 0.07484 -0.0722 1.0000 0.0632
-11.750 -0.5049 0.07699 0.06904 -0.0739 1.0000 0.0635
-11.500 -0.5232 0.07259 0.06448 -0.0745 1.0000 0.0640
-11.250 -0.5217 0.07079 0.06277 -0.0733 1.0000 0.0652
-11.000 -0.5249 0.06869 0.06066 -0.0722 1.0000 0.0663
-10.750 -0.5300 0.06660 0.05858 -0.0709 1.0000 0.0677
-10.500 -0.5383 0.06448 0.05643 -0.0695 1.0000 0.0694
-10.250 -0.5476 0.06253 0.05441 -0.0677 1.0000 0.0711
-10.000 -0.5600 0.06065 0.05243 -0.0655 1.0000 0.0729
-9.750 -0.5667 0.05978 0.05172 -0.0626 1.0000 0.0747
-9.500 -0.5624 0.05846 0.05046 -0.0623 0.9966 0.0776
-9.250 -0.5366 0.05622 0.04807 -0.0658 0.9864 0.0841
-9.000 -0.5137 0.05432 0.04622 -0.0689 0.9751 0.0915
-8.750 -0.4957 0.05232 0.04429 -0.0714 0.9618 0.1000
-8.500 -0.4831 0.05017 0.04217 -0.0735 0.9467 0.1103
-8.250 -0.4704 0.04785 0.03993 -0.0759 0.9315 0.1229
-8.000 -0.4577 0.04529 0.03751 -0.0788 0.9162 0.1388
-7.750 -0.4446 0.04250 0.03489 -0.0821 0.9011 0.1601
-7.500 -0.4285 0.03997 0.03263 -0.0854 0.8865 0.1880
-7.250 -0.4040 0.03900 0.03206 -0.0870 0.8738 0.2272
-7.000 -0.3558 0.04178 0.03510 -0.0851 0.8660 0.2661
-6.750 -0.3236 0.04244 0.03559 -0.0856 0.8531 0.2950
-6.250 -0.2503 0.04303 0.03565 -0.0892 0.8324 0.3431
-6.000 -0.2179 0.04343 0.03582 -0.0898 0.8208 0.3604
-5.750 -0.1775 0.04355 0.03569 -0.0916 0.8123 0.3774
-5.500 -0.1531 0.04309 0.03500 -0.0924 0.7994 0.3930
-5.000 -0.0877 0.04343 0.03497 -0.0920 0.7789 0.4144
-4.750 -0.0615 0.04237 0.03365 -0.0941 0.7679 0.4289
-4.500 -0.0280 0.04270 0.03385 -0.0929 0.7584 0.4350
-4.250 -0.0059 0.04150 0.03240 -0.0949 0.7467 0.4476
-4.000 0.0283 0.04147 0.03221 -0.0945 0.7383 0.4530
-3.750 0.0485 0.04059 0.03114 -0.0955 0.7265 0.4628
-3.500 0.0826 0.04000 0.03034 -0.0967 0.7188 0.4690
-3.250 0.1006 0.03982 0.03008 -0.0954 0.7074 0.4743
-2.750 0.1541 0.03844 0.02834 -0.0979 0.6889 0.4873
-2.500 0.1872 0.03796 0.02767 -0.0990 0.6819 0.4919
-2.250 0.2071 0.03755 0.02715 -0.0993 0.6717 0.4975
-2.000 0.2431 0.03670 0.02605 -0.1025 0.6645 0.5033
-1.750 0.2622 0.03663 0.02595 -0.1014 0.6554 0.5062
-1.500 0.2910 0.03632 0.02551 -0.1020 0.6480 0.5100
-1.250 0.3192 0.03599 0.02504 -0.1031 0.6407 0.5144
-1.000 0.3479 0.03560 0.02450 -0.1051 0.6324 0.5189
-0.750 0.3836 0.03516 0.02388 -0.1071 0.6267 0.5224
-0.500 0.4001 0.03533 0.02407 -0.1058 0.6182 0.5250
-0.250 0.4287 0.03519 0.02384 -0.1064 0.6117 0.5283
0.000 0.4614 0.03497 0.02347 -0.1080 0.6061 0.5316
0.250 0.4821 0.03511 0.02359 -0.1082 0.5980 0.5347
0.500 0.5186 0.03486 0.02315 -0.1109 0.5922 0.5391
0.750 0.5437 0.03496 0.02322 -0.1107 0.5865 0.5417
1.000 0.5613 0.03531 0.02362 -0.1098 0.5792 0.5443
1.250 0.5918 0.03527 0.02350 -0.1106 0.5740 0.5472
1.500 0.6204 0.03538 0.02353 -0.1114 0.5687 0.5501
1.750 0.6376 0.03591 0.02410 -0.1109 0.5615 0.5533
2.000 0.6709 0.03598 0.02404 -0.1127 0.5564 0.5576
2.250 0.7051 0.03589 0.02388 -0.1137 0.5526 0.5607
2.500 0.7092 0.03697 0.02513 -0.1112 0.5447 0.5632
2.750 0.7346 0.03729 0.02544 -0.1113 0.5395 0.5665
3.000 0.7706 0.03727 0.02531 -0.1130 0.5357 0.5702
3.250 0.7801 0.03839 0.02652 -0.1116 0.5290 0.5733
3.500 0.7989 0.03915 0.02729 -0.1113 0.5231 0.5770
3.750 0.8284 0.03930 0.02744 -0.1116 0.5191 0.5806
4.000 0.8548 0.03971 0.02785 -0.1118 0.5150 0.5848
4.250 0.8453 0.04179 0.03010 -0.1082 0.5071 0.5877
4.500 0.8720 0.04228 0.03057 -0.1087 0.5027 0.5925
4.750 0.9093 0.04221 0.03047 -0.1101 0.4996 0.5970
5.000 0.8756 0.04548 0.03394 -0.1041 0.4906 0.5987
5.250 0.8887 0.04662 0.03513 -0.1030 0.4855 0.6024
5.500 0.9241 0.04664 0.03513 -0.1041 0.4825 0.6081
6.000 0.8897 0.05338 0.04208 -0.0984 0.4669 0.6147
6.250 0.9235 0.05315 0.04190 -0.0987 0.4644 0.6209
8.250 0.8472 0.08603 0.07551 -0.0961 0.4022 0.6551
8.500 0.8611 0.08783 0.07740 -0.0961 0.3974 0.6636
8.750 0.8852 0.08838 0.07806 -0.0959 0.3946 0.6744
9.250 0.8749 0.09653 0.08644 -0.0968 0.3803 0.6904
9.500 0.8987 0.09704 0.08708 -0.0964 0.3774 0.7072
10.000 0.8885 0.10512 0.09547 -0.0974 0.3636 0.7328
10.250 0.9096 0.10548 0.09603 -0.0965 0.3607 0.7654
10.750 0.8895 0.11228 0.10325 -0.0955 0.3473 0.9903
11.000 0.9169 0.11329 0.10422 -0.0963 0.3442 1.0000
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Polar data table (+)
Polar graphs
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