E168 (12.45%) (e168-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: E168 (12.45%) (e168-il) Reynolds number: 50,000 Max Cl/Cd: 27.97 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e168-il-50000-n5.txt Download as CSV file: xf-e168-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E168 (12.45%)
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
------ -------- --------- --------- -------- -------- --------
-13.000 -0.7866 0.10069 0.09348 -0.0030 1.0000 0.0642
-12.750 -0.8380 0.08584 0.07845 -0.0127 1.0000 0.0621
-12.500 -0.8648 0.07726 0.06965 -0.0179 1.0000 0.0619
-12.250 -0.8803 0.07121 0.06343 -0.0212 1.0000 0.0628
-12.000 -0.8920 0.06607 0.05810 -0.0235 1.0000 0.0639
-11.750 -0.9015 0.06143 0.05325 -0.0253 1.0000 0.0654
-11.500 -0.9091 0.05723 0.04881 -0.0264 1.0000 0.0674
-11.250 -0.9154 0.05342 0.04467 -0.0270 1.0000 0.0697
-11.000 -0.9132 0.05092 0.04220 -0.0267 1.0000 0.0732
-10.750 -0.9143 0.04836 0.03955 -0.0262 1.0000 0.0775
-10.500 -0.9148 0.04566 0.03655 -0.0252 1.0000 0.0822
-10.250 -0.9117 0.04365 0.03463 -0.0237 1.0000 0.0870
-10.000 -0.9090 0.04152 0.03233 -0.0222 1.0000 0.0941
-9.750 -0.9040 0.03962 0.03047 -0.0207 1.0000 0.1018
-9.500 -0.8976 0.03772 0.02851 -0.0193 1.0000 0.1119
-9.250 -0.8898 0.03598 0.02673 -0.0178 1.0000 0.1242
-9.000 -0.8807 0.03442 0.02517 -0.0164 1.0000 0.1385
-8.750 -0.8698 0.03303 0.02381 -0.0149 1.0000 0.1550
-8.500 -0.8575 0.03179 0.02249 -0.0135 1.0000 0.1743
-8.250 -0.8433 0.03070 0.02138 -0.0121 1.0000 0.1940
-8.000 -0.8277 0.02983 0.02050 -0.0107 1.0000 0.2141
-7.750 -0.8110 0.02896 0.01946 -0.0095 1.0000 0.2350
-7.500 -0.7926 0.02834 0.01886 -0.0081 1.0000 0.2538
-7.250 -0.7736 0.02774 0.01816 -0.0069 1.0000 0.2729
-7.000 -0.7541 0.02711 0.01741 -0.0057 1.0000 0.2918
-6.750 -0.7338 0.02655 0.01676 -0.0046 1.0000 0.3093
-6.500 -0.7125 0.02605 0.01622 -0.0034 1.0000 0.3257
-6.250 -0.6910 0.02556 0.01567 -0.0023 1.0000 0.3418
-6.000 -0.6692 0.02506 0.01507 -0.0013 1.0000 0.3573
-5.750 -0.6472 0.02457 0.01452 -0.0002 1.0000 0.3726
-5.500 -0.6250 0.02410 0.01398 0.0008 1.0000 0.3876
-5.250 -0.6027 0.02362 0.01344 0.0018 1.0000 0.4022
-5.000 -0.5803 0.02316 0.01291 0.0028 1.0000 0.4168
-4.750 -0.5580 0.02272 0.01243 0.0038 1.0000 0.4312
-4.500 -0.5358 0.02230 0.01197 0.0048 1.0000 0.4457
-4.250 -0.5137 0.02190 0.01155 0.0059 1.0000 0.4602
-4.000 -0.4917 0.02151 0.01114 0.0069 1.0000 0.4749
-3.750 -0.4700 0.02116 0.01078 0.0080 1.0000 0.4896
-3.500 -0.4486 0.02083 0.01046 0.0091 1.0000 0.5046
-3.250 -0.4275 0.02052 0.01019 0.0102 1.0000 0.5196
-3.000 -0.4071 0.02025 0.00993 0.0113 1.0000 0.5349
-2.750 -0.3878 0.02002 0.00975 0.0126 1.0000 0.5503
-2.500 -0.3703 0.01984 0.00962 0.0141 1.0000 0.5658
-2.250 -0.3393 0.01972 0.00955 0.0129 0.9883 0.5836
-2.000 -0.2948 0.01962 0.00946 0.0094 0.9641 0.6046
-1.750 -0.2496 0.01951 0.00938 0.0061 0.9415 0.6257
-1.500 -0.2066 0.01938 0.00930 0.0034 0.9181 0.6464
-1.250 -0.1637 0.01926 0.00919 0.0009 0.8956 0.6687
-1.000 -0.1259 0.01916 0.00915 -0.0004 0.8707 0.6888
-0.750 -0.0901 0.01908 0.00906 -0.0012 0.8467 0.7102
-0.500 -0.0580 0.01902 0.00902 -0.0013 0.8223 0.7316
-0.250 -0.0285 0.01899 0.00900 -0.0007 0.7983 0.7530
0.000 0.0000 0.01898 0.00897 0.0000 0.7758 0.7758
0.250 0.0285 0.01899 0.00900 0.0007 0.7530 0.7983
0.500 0.0580 0.01902 0.00902 0.0013 0.7316 0.8224
0.750 0.0901 0.01908 0.00906 0.0012 0.7102 0.8466
1.000 0.1258 0.01916 0.00915 0.0004 0.6888 0.8707
1.500 0.2066 0.01938 0.00930 -0.0034 0.6464 0.9182
1.750 0.2496 0.01951 0.00938 -0.0061 0.6257 0.9416
2.000 0.2948 0.01962 0.00946 -0.0094 0.6046 0.9641
2.250 0.3393 0.01972 0.00955 -0.0129 0.5836 0.9884
2.500 0.3703 0.01984 0.00962 -0.0141 0.5658 1.0000
2.750 0.3878 0.02002 0.00975 -0.0126 0.5503 1.0000
3.000 0.4071 0.02025 0.00993 -0.0114 0.5349 1.0000
3.250 0.4276 0.02052 0.01018 -0.0102 0.5196 1.0000
3.500 0.4486 0.02083 0.01046 -0.0091 0.5046 1.0000
3.750 0.4701 0.02116 0.01078 -0.0080 0.4897 1.0000
4.000 0.4918 0.02151 0.01114 -0.0069 0.4749 1.0000
4.250 0.5137 0.02189 0.01155 -0.0059 0.4602 1.0000
4.500 0.5358 0.02230 0.01197 -0.0049 0.4457 1.0000
4.750 0.5581 0.02272 0.01243 -0.0038 0.4312 1.0000
5.000 0.5804 0.02316 0.01291 -0.0028 0.4168 1.0000
5.250 0.6027 0.02362 0.01344 -0.0018 0.4022 1.0000
5.500 0.6250 0.02409 0.01397 -0.0008 0.3875 1.0000
5.750 0.6472 0.02457 0.01452 0.0002 0.3726 1.0000
6.000 0.6692 0.02506 0.01507 0.0013 0.3573 1.0000
6.250 0.6910 0.02556 0.01566 0.0023 0.3417 1.0000
6.500 0.7125 0.02605 0.01622 0.0034 0.3257 1.0000
6.750 0.7337 0.02655 0.01676 0.0046 0.3093 1.0000
7.000 0.7541 0.02711 0.01741 0.0057 0.2917 1.0000
7.250 0.7736 0.02773 0.01816 0.0069 0.2729 1.0000
7.500 0.7926 0.02834 0.01886 0.0081 0.2538 1.0000
8.000 0.8276 0.02983 0.02050 0.0107 0.2141 1.0000
8.250 0.8432 0.03069 0.02137 0.0121 0.1940 1.0000
8.500 0.8574 0.03178 0.02249 0.0135 0.1744 1.0000
8.750 0.8698 0.03302 0.02380 0.0149 0.1550 1.0000
9.000 0.8806 0.03441 0.02517 0.0164 0.1386 1.0000
9.250 0.8898 0.03597 0.02672 0.0178 0.1242 1.0000
9.500 0.8977 0.03772 0.02850 0.0193 0.1119 1.0000
9.750 0.9040 0.03961 0.03047 0.0208 0.1018 1.0000
10.000 0.9089 0.04152 0.03232 0.0222 0.0940 1.0000
10.250 0.9118 0.04363 0.03461 0.0237 0.0870 1.0000
10.500 0.9146 0.04566 0.03656 0.0252 0.0821 1.0000
10.750 0.9139 0.04836 0.03955 0.0262 0.0773 1.0000
11.000 0.9136 0.05090 0.04221 0.0267 0.0733 1.0000
11.250 0.9159 0.05339 0.04463 0.0270 0.0697 1.0000
11.500 0.9089 0.05726 0.04883 0.0264 0.0672 1.0000
11.750 0.9017 0.06143 0.05326 0.0253 0.0653 1.0000
12.000 0.8924 0.06603 0.05807 0.0235 0.0639 1.0000
12.250 0.8808 0.07117 0.06339 0.0212 0.0627 1.0000
12.500 0.8656 0.07717 0.06956 0.0180 0.0619 1.0000
12.750 0.8382 0.08587 0.07849 0.0126 0.0622 1.0000
13.000 0.7871 0.10069 0.09347 0.0030 0.0642 1.0000
|
Polar data table (+)
Polar graphs
<< Back to E168 (12.45%) (e168-il)