FX LIII-142 K 25 AIRFOIL (fxl142k-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX LIII-142 K 25 AIRFOIL (fxl142k-il) Reynolds number: 100,000 Max Cl/Cd: 42.13 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fxl142k-il-100000.txt Download as CSV file: xf-fxl142k-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: FX LIII-142 K 25 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.8092 0.10269 0.09752 -0.0118 1.0000 0.1005
-13.250 -0.8315 0.09341 0.08822 -0.0160 1.0000 0.0995
-13.000 -0.8703 0.08324 0.07801 -0.0217 1.0000 0.0979
-12.750 -0.9162 0.07405 0.06868 -0.0268 1.0000 0.0963
-12.500 -0.9576 0.06694 0.06138 -0.0298 1.0000 0.0951
-12.250 -0.9913 0.06169 0.05591 -0.0307 1.0000 0.0945
-12.000 -1.0177 0.05769 0.05168 -0.0295 1.0000 0.0944
-11.750 -1.0370 0.05442 0.04815 -0.0270 1.0000 0.0948
-11.500 -1.0472 0.05120 0.04463 -0.0250 1.0000 0.0956
-11.250 -1.0519 0.04830 0.04139 -0.0229 1.0000 0.0971
-11.000 -1.0536 0.04580 0.03847 -0.0207 1.0000 0.0990
-10.750 -1.0516 0.04360 0.03583 -0.0185 1.0000 0.1008
-10.500 -1.0328 0.04043 0.03264 -0.0184 1.0000 0.1036
-10.250 -1.0157 0.03842 0.03047 -0.0175 1.0000 0.1061
-10.000 -0.9985 0.03658 0.02844 -0.0166 1.0000 0.1091
-9.750 -0.9823 0.03494 0.02652 -0.0154 1.0000 0.1128
-9.500 -0.9649 0.03321 0.02448 -0.0142 1.0000 0.1162
-9.250 -0.9397 0.03135 0.02274 -0.0142 1.0000 0.1203
-9.000 -0.9173 0.02993 0.02123 -0.0135 1.0000 0.1248
-8.750 -0.8971 0.02874 0.01977 -0.0125 1.0000 0.1301
-8.500 -0.8724 0.02713 0.01837 -0.0123 1.0000 0.1372
-8.250 -0.8515 0.02601 0.01705 -0.0113 1.0000 0.1452
-8.000 -0.8288 0.02446 0.01577 -0.0106 1.0000 0.1558
-7.750 -0.8095 0.02309 0.01455 -0.0095 1.0000 0.1699
-7.500 -0.7925 0.02180 0.01341 -0.0080 1.0000 0.1901
-7.250 -0.7779 0.02056 0.01245 -0.0063 1.0000 0.2157
-7.000 -0.7636 0.01939 0.01155 -0.0046 1.0000 0.2498
-6.750 -0.7504 0.01829 0.01085 -0.0026 1.0000 0.2926
-6.500 -0.7364 0.01748 0.01043 -0.0005 1.0000 0.3482
-6.250 -0.7205 0.01713 0.01035 0.0016 1.0000 0.4002
-6.000 -0.7033 0.01714 0.01049 0.0036 1.0000 0.4394
-5.750 -0.6879 0.01737 0.01078 0.0058 1.0000 0.4658
-5.500 -0.6860 0.01753 0.01088 0.0093 1.0000 0.4855
-5.250 -0.6518 0.01808 0.01146 0.0076 0.9881 0.5099
-5.000 -0.6003 0.01888 0.01225 0.0035 0.9734 0.5363
-4.750 -0.5512 0.01940 0.01264 -0.0002 0.9595 0.5610
-4.500 -0.5040 0.01975 0.01297 -0.0034 0.9457 0.5772
-4.250 -0.4595 0.01982 0.01292 -0.0063 0.9326 0.5911
-4.000 -0.4194 0.02002 0.01310 -0.0079 0.9181 0.6026
-3.750 -0.3853 0.02021 0.01324 -0.0085 0.9032 0.6158
-3.500 -0.3542 0.02045 0.01343 -0.0083 0.8896 0.6297
-3.250 -0.3248 0.02067 0.01361 -0.0077 0.8769 0.6427
-3.000 -0.2976 0.02075 0.01363 -0.0071 0.8647 0.6543
-2.750 -0.2722 0.02065 0.01342 -0.0066 0.8536 0.6654
-2.500 -0.2459 0.02070 0.01344 -0.0058 0.8422 0.6730
-2.250 -0.2221 0.02055 0.01322 -0.0052 0.8320 0.6825
-1.750 -0.1725 0.02047 0.01305 -0.0037 0.8136 0.7007
-1.500 -0.1495 0.02031 0.01280 -0.0033 0.8049 0.7108
-1.250 -0.1235 0.02025 0.01274 -0.0026 0.7967 0.7172
-1.000 -0.1003 0.02010 0.01253 -0.0023 0.7879 0.7265
-0.750 -0.0745 0.02004 0.01248 -0.0017 0.7804 0.7333
-0.500 -0.0504 0.01990 0.01230 -0.0013 0.7723 0.7421
-0.250 -0.0249 0.01990 0.01232 -0.0006 0.7647 0.7491
0.000 0.0000 0.01982 0.01221 0.0000 0.7574 0.7574
0.250 0.0249 0.01990 0.01232 0.0006 0.7491 0.7647
0.500 0.0504 0.01990 0.01230 0.0013 0.7420 0.7723
0.750 0.0745 0.02004 0.01248 0.0017 0.7332 0.7805
1.000 0.1003 0.02010 0.01253 0.0023 0.7265 0.7879
1.250 0.1235 0.02025 0.01274 0.0026 0.7172 0.7967
1.500 0.1496 0.02031 0.01280 0.0033 0.7108 0.8048
1.750 0.1725 0.02047 0.01304 0.0037 0.7006 0.8137
2.000 0.1966 0.02052 0.01311 0.0044 0.6919 0.8236
2.250 0.2221 0.02055 0.01322 0.0052 0.6825 0.8321
2.500 0.2459 0.02070 0.01344 0.0058 0.6730 0.8422
2.750 0.2722 0.02066 0.01342 0.0066 0.6654 0.8536
3.000 0.2976 0.02075 0.01363 0.0071 0.6543 0.8648
3.250 0.3248 0.02067 0.01361 0.0077 0.6427 0.8769
3.500 0.3542 0.02044 0.01341 0.0083 0.6295 0.8896
3.750 0.3853 0.02022 0.01324 0.0085 0.6158 0.9032
4.000 0.4194 0.02002 0.01309 0.0080 0.6026 0.9181
4.250 0.4595 0.01982 0.01292 0.0063 0.5911 0.9326
4.500 0.5040 0.01975 0.01297 0.0034 0.5772 0.9458
4.750 0.5512 0.01941 0.01265 0.0002 0.5611 0.9596
5.000 0.6002 0.01891 0.01229 -0.0036 0.5367 0.9735
5.250 0.6517 0.01808 0.01146 -0.0076 0.5099 0.9881
5.500 0.6859 0.01753 0.01088 -0.0093 0.4855 1.0000
5.750 0.6879 0.01737 0.01078 -0.0058 0.4657 1.0000
6.000 0.7032 0.01714 0.01049 -0.0036 0.4394 1.0000
6.250 0.7205 0.01713 0.01035 -0.0016 0.4001 1.0000
6.500 0.7364 0.01748 0.01043 0.0005 0.3481 1.0000
6.750 0.7504 0.01829 0.01085 0.0026 0.2926 1.0000
7.000 0.7636 0.01939 0.01155 0.0046 0.2499 1.0000
7.250 0.7779 0.02055 0.01245 0.0063 0.2158 1.0000
7.500 0.7926 0.02180 0.01341 0.0080 0.1900 1.0000
7.750 0.8095 0.02309 0.01455 0.0095 0.1696 1.0000
8.000 0.8289 0.02446 0.01577 0.0106 0.1558 1.0000
8.250 0.8515 0.02601 0.01705 0.0112 0.1452 1.0000
8.500 0.8724 0.02713 0.01836 0.0123 0.1371 1.0000
8.750 0.8970 0.02873 0.01976 0.0125 0.1300 1.0000
9.000 0.9173 0.02993 0.02123 0.0135 0.1247 1.0000
9.250 0.9398 0.03135 0.02274 0.0142 0.1203 1.0000
9.500 0.9651 0.03327 0.02452 0.0142 0.1160 1.0000
9.750 0.9821 0.03494 0.02651 0.0154 0.1127 1.0000
10.000 0.9985 0.03657 0.02842 0.0166 0.1090 1.0000
10.250 1.0158 0.03842 0.03046 0.0175 0.1060 1.0000
10.500 1.0330 0.04042 0.03263 0.0183 0.1035 1.0000
10.750 1.0517 0.04366 0.03589 0.0185 0.1008 1.0000
11.000 1.0538 0.04586 0.03854 0.0207 0.0991 1.0000
11.250 1.0520 0.04835 0.04144 0.0229 0.0971 1.0000
11.500 1.0472 0.05122 0.04465 0.0250 0.0956 1.0000
11.750 1.0370 0.05447 0.04821 0.0270 0.0948 1.0000
12.000 1.0180 0.05767 0.05166 0.0295 0.0942 1.0000
12.250 0.9916 0.06171 0.05593 0.0306 0.0944 1.0000
12.500 0.9578 0.06699 0.06143 0.0297 0.0951 1.0000
12.750 0.9163 0.07413 0.06877 0.0267 0.0963 1.0000
13.000 0.8699 0.08344 0.07822 0.0215 0.0980 1.0000
13.250 0.8301 0.09385 0.08865 0.0156 0.0995 1.0000
13.500 0.8088 0.10302 0.09785 0.0115 0.1005 1.0000
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