E168 (12.45%) (e168-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: E168 (12.45%) (e168-il) Reynolds number: 500,000 Max Cl/Cd: 67.92 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e168-il-500000-n5.txt Download as CSV file: xf-e168-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.000 -1.0753 0.09987 0.09606 0.0018 1.0000 0.0067
-16.750 -1.0877 0.09367 0.08975 -0.0015 1.0000 0.0068
-16.500 -1.1024 0.08723 0.08320 -0.0048 1.0000 0.0069
-16.250 -1.1148 0.08135 0.07721 -0.0078 1.0000 0.0069
-16.000 -1.1274 0.07559 0.07134 -0.0107 1.0000 0.0070
-15.750 -1.1421 0.06979 0.06542 -0.0136 1.0000 0.0070
-15.500 -1.1555 0.06433 0.05984 -0.0163 1.0000 0.0071
-15.250 -1.1665 0.05933 0.05471 -0.0186 1.0000 0.0072
-15.000 -1.1744 0.05486 0.05014 -0.0207 1.0000 0.0072
-14.750 -1.1836 0.05031 0.04546 -0.0227 1.0000 0.0073
-14.500 -1.1949 0.04557 0.04061 -0.0249 1.0000 0.0074
-14.250 -1.2012 0.04165 0.03657 -0.0265 1.0000 0.0076
-14.000 -1.2068 0.03799 0.03279 -0.0279 1.0000 0.0077
-13.750 -1.2086 0.03500 0.02970 -0.0288 1.0000 0.0079
-13.500 -1.2084 0.03246 0.02707 -0.0292 1.0000 0.0082
-13.250 -1.2087 0.03015 0.02464 -0.0290 1.0000 0.0084
-13.000 -1.2052 0.02844 0.02284 -0.0283 1.0000 0.0088
-12.750 -1.2025 0.02691 0.02121 -0.0269 1.0000 0.0091
-12.500 -1.1972 0.02575 0.01996 -0.0252 1.0000 0.0095
-12.250 -1.1911 0.02474 0.01886 -0.0229 1.0000 0.0099
-12.000 -1.1847 0.02381 0.01785 -0.0204 1.0000 0.0103
-11.750 -1.1758 0.02277 0.01675 -0.0184 1.0000 0.0109
-11.500 -1.1620 0.02193 0.01585 -0.0168 1.0000 0.0115
-11.250 -1.1461 0.02118 0.01503 -0.0155 1.0000 0.0123
-11.000 -1.1290 0.02047 0.01423 -0.0142 1.0000 0.0130
-10.750 -1.1107 0.01982 0.01350 -0.0131 1.0000 0.0136
-10.500 -1.0934 0.01902 0.01266 -0.0118 1.0000 0.0146
-10.250 -1.0741 0.01838 0.01197 -0.0108 1.0000 0.0157
-10.000 -1.0537 0.01780 0.01134 -0.0098 1.0000 0.0169
-9.750 -1.0329 0.01724 0.01072 -0.0088 1.0000 0.0182
-9.500 -1.0125 0.01663 0.01009 -0.0079 1.0000 0.0202
-9.250 -0.9909 0.01611 0.00952 -0.0070 1.0000 0.0221
-9.000 -0.9693 0.01558 0.00897 -0.0061 1.0000 0.0247
-8.750 -0.9475 0.01506 0.00844 -0.0052 1.0000 0.0284
-8.500 -0.9258 0.01453 0.00793 -0.0043 1.0000 0.0337
-8.250 -0.9036 0.01405 0.00745 -0.0034 1.0000 0.0401
-8.000 -0.8812 0.01359 0.00700 -0.0025 1.0000 0.0472
-7.750 -0.8589 0.01312 0.00656 -0.0017 1.0000 0.0556
-7.500 -0.8366 0.01267 0.00614 -0.0007 1.0000 0.0660
-7.250 -0.8142 0.01222 0.00575 0.0002 1.0000 0.0779
-7.000 -0.7916 0.01181 0.00538 0.0011 1.0000 0.0910
-6.750 -0.7689 0.01141 0.00503 0.0020 1.0000 0.1055
-6.500 -0.7460 0.01104 0.00472 0.0028 1.0000 0.1211
-6.250 -0.7233 0.01065 0.00442 0.0037 1.0000 0.1393
-6.000 -0.6910 0.01025 0.00413 0.0025 0.9946 0.1644
-5.750 -0.6568 0.00988 0.00386 0.0010 0.9846 0.1892
-5.500 -0.6222 0.00961 0.00363 -0.0005 0.9681 0.2062
-5.250 -0.5805 0.00936 0.00340 -0.0035 0.9387 0.2213
-5.000 -0.5393 0.00915 0.00315 -0.0062 0.8966 0.2374
-4.750 -0.5118 0.00907 0.00297 -0.0059 0.8528 0.2510
-4.500 -0.4865 0.00901 0.00281 -0.0052 0.8171 0.2643
-4.250 -0.4609 0.00894 0.00266 -0.0046 0.7869 0.2770
-3.750 -0.4088 0.00881 0.00238 -0.0036 0.7353 0.3012
-3.500 -0.3823 0.00875 0.00226 -0.0032 0.7126 0.3131
-3.250 -0.3555 0.00869 0.00215 -0.0029 0.6910 0.3250
-3.000 -0.3286 0.00865 0.00204 -0.0025 0.6707 0.3367
-2.750 -0.3017 0.00860 0.00195 -0.0022 0.6514 0.3486
-2.500 -0.2745 0.00855 0.00186 -0.0020 0.6332 0.3598
-2.250 -0.2473 0.00851 0.00179 -0.0018 0.6156 0.3715
-2.000 -0.2199 0.00848 0.00172 -0.0015 0.5989 0.3831
-1.750 -0.1926 0.00845 0.00166 -0.0013 0.5827 0.3952
-1.500 -0.1652 0.00842 0.00161 -0.0011 0.5670 0.4072
-1.250 -0.1377 0.00839 0.00156 -0.0009 0.5519 0.4187
-1.000 -0.1102 0.00838 0.00153 -0.0007 0.5371 0.4311
-0.750 -0.0826 0.00837 0.00150 -0.0005 0.5227 0.4434
-0.500 -0.0551 0.00836 0.00148 -0.0004 0.5088 0.4560
-0.250 -0.0276 0.00835 0.00147 -0.0002 0.4951 0.4689
0.000 0.0000 0.00834 0.00146 0.0000 0.4819 0.4817
0.250 0.0275 0.00835 0.00147 0.0002 0.4690 0.4950
0.500 0.0550 0.00836 0.00148 0.0004 0.4560 0.5088
0.750 0.0826 0.00837 0.00150 0.0006 0.4434 0.5227
1.000 0.1102 0.00838 0.00153 0.0007 0.4312 0.5370
1.250 0.1377 0.00839 0.00156 0.0009 0.4188 0.5519
1.500 0.1651 0.00842 0.00161 0.0011 0.4071 0.5670
1.750 0.1925 0.00845 0.00166 0.0013 0.3952 0.5825
2.000 0.2199 0.00848 0.00172 0.0015 0.3832 0.5988
2.250 0.2472 0.00851 0.00179 0.0018 0.3716 0.6156
2.500 0.2745 0.00855 0.00186 0.0020 0.3597 0.6332
2.750 0.3016 0.00859 0.00195 0.0023 0.3486 0.6516
3.000 0.3285 0.00865 0.00204 0.0026 0.3368 0.6707
3.250 0.3554 0.00870 0.00215 0.0029 0.3250 0.6909
3.500 0.3822 0.00875 0.00226 0.0032 0.3129 0.7125
3.750 0.4087 0.00880 0.00238 0.0036 0.3012 0.7353
4.000 0.4350 0.00887 0.00251 0.0041 0.2892 0.7599
4.250 0.4609 0.00894 0.00266 0.0046 0.2770 0.7870
4.500 0.4864 0.00901 0.00281 0.0052 0.2644 0.8173
4.750 0.5118 0.00907 0.00297 0.0059 0.2511 0.8528
5.000 0.5393 0.00915 0.00315 0.0062 0.2374 0.8970
5.250 0.5803 0.00936 0.00340 0.0035 0.2211 0.9385
5.500 0.6222 0.00961 0.00363 0.0005 0.2063 0.9680
5.750 0.6568 0.00988 0.00386 -0.0010 0.1894 0.9846
6.000 0.6909 0.01025 0.00413 -0.0025 0.1645 0.9945
6.250 0.7234 0.01065 0.00442 -0.0038 0.1397 1.0000
6.500 0.7461 0.01103 0.00472 -0.0029 0.1213 1.0000
6.750 0.7690 0.01141 0.00504 -0.0020 0.1053 1.0000
7.000 0.7917 0.01181 0.00538 -0.0011 0.0911 1.0000
7.250 0.8142 0.01222 0.00575 -0.0002 0.0779 1.0000
7.500 0.8366 0.01267 0.00614 0.0007 0.0660 1.0000
7.750 0.8589 0.01312 0.00656 0.0016 0.0556 1.0000
8.000 0.8812 0.01359 0.00700 0.0025 0.0471 1.0000
8.250 0.9035 0.01405 0.00746 0.0034 0.0400 1.0000
8.500 0.9257 0.01453 0.00793 0.0043 0.0337 1.0000
8.750 0.9475 0.01506 0.00844 0.0052 0.0285 1.0000
9.000 0.9692 0.01558 0.00897 0.0061 0.0246 1.0000
9.250 0.9908 0.01611 0.00952 0.0070 0.0221 1.0000
9.500 1.0124 0.01662 0.01009 0.0079 0.0201 1.0000
9.750 1.0328 0.01724 0.01072 0.0089 0.0183 1.0000
10.000 1.0535 0.01780 0.01134 0.0098 0.0169 1.0000
10.250 1.0739 0.01837 0.01197 0.0108 0.0157 1.0000
10.500 1.0932 0.01903 0.01266 0.0119 0.0146 1.0000
10.750 1.1103 0.01983 0.01351 0.0131 0.0135 1.0000
11.000 1.1288 0.02047 0.01422 0.0143 0.0130 1.0000
11.250 1.1460 0.02117 0.01502 0.0155 0.0123 1.0000
11.500 1.1617 0.02193 0.01585 0.0169 0.0115 1.0000
11.750 1.1754 0.02278 0.01676 0.0184 0.0109 1.0000
12.000 1.1842 0.02383 0.01786 0.0205 0.0102 1.0000
12.250 1.1913 0.02472 0.01884 0.0229 0.0099 1.0000
12.500 1.1966 0.02577 0.01998 0.0252 0.0096 1.0000
12.750 1.2024 0.02692 0.02122 0.0270 0.0090 1.0000
13.000 1.2050 0.02846 0.02286 0.0283 0.0088 1.0000
13.250 1.2078 0.03023 0.02473 0.0290 0.0085 1.0000
13.500 1.2092 0.03238 0.02698 0.0292 0.0082 1.0000
13.750 1.2089 0.03497 0.02967 0.0288 0.0079 1.0000
14.000 1.2066 0.03803 0.03283 0.0279 0.0077 1.0000
14.250 1.2024 0.04151 0.03643 0.0266 0.0076 1.0000
14.500 1.1942 0.04568 0.04072 0.0248 0.0074 1.0000
14.750 1.1845 0.05022 0.04537 0.0227 0.0073 1.0000
15.000 1.1767 0.05458 0.04985 0.0208 0.0072 1.0000
15.250 1.1675 0.05924 0.05463 0.0186 0.0071 1.0000
15.500 1.1552 0.06443 0.05995 0.0161 0.0070 1.0000
15.750 1.1419 0.06989 0.06552 0.0135 0.0070 1.0000
16.000 1.1295 0.07534 0.07108 0.0108 0.0069 1.0000
16.250 1.1159 0.08125 0.07711 0.0078 0.0069 1.0000
16.500 1.1045 0.08697 0.08294 0.0048 0.0068 1.0000
16.750 1.0900 0.09336 0.08944 0.0015 0.0069 1.0000
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Polar data table (+)
Polar graphs
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