FX 79-L-100 (fx79l100-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 79-L-100 (fx79l100-il) Reynolds number: 500,000 Max Cl/Cd: 58.11 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx79l100-il-500000-n5.txt Download as CSV file: xf-fx79l100-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 79-L-100
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
------ -------- --------- --------- -------- -------- --------
-15.750 -1.0196 0.10691 0.10422 0.0156 1.0000 0.0078
-15.250 -1.0924 0.08207 0.07904 0.0012 1.0000 0.0076
-15.000 -1.1178 0.07272 0.06953 -0.0047 1.0000 0.0076
-14.750 -1.1361 0.06527 0.06188 -0.0095 1.0000 0.0077
-14.500 -1.1555 0.05826 0.05468 -0.0138 1.0000 0.0077
-14.250 -1.1666 0.05293 0.04918 -0.0169 1.0000 0.0077
-14.000 -1.1700 0.04902 0.04512 -0.0190 1.0000 0.0078
-13.750 -1.1804 0.04436 0.04026 -0.0212 1.0000 0.0078
-13.500 -1.1904 0.04012 0.03585 -0.0228 1.0000 0.0079
-13.250 -1.1944 0.03690 0.03246 -0.0235 1.0000 0.0080
-13.000 -1.1941 0.03444 0.02984 -0.0235 1.0000 0.0080
-12.750 -1.1946 0.03214 0.02741 -0.0228 1.0000 0.0082
-12.500 -1.1880 0.03069 0.02584 -0.0216 1.0000 0.0084
-12.250 -1.1801 0.02941 0.02445 -0.0200 1.0000 0.0086
-12.000 -1.1714 0.02807 0.02297 -0.0183 1.0000 0.0087
-11.750 -1.1573 0.02699 0.02179 -0.0172 1.0000 0.0091
-11.500 -1.1432 0.02584 0.02051 -0.0160 1.0000 0.0092
-11.250 -1.1288 0.02463 0.01916 -0.0147 1.0000 0.0095
-11.000 -1.1124 0.02358 0.01799 -0.0136 1.0000 0.0098
-10.750 -1.0945 0.02266 0.01695 -0.0126 1.0000 0.0101
-10.500 -1.0752 0.02187 0.01604 -0.0116 1.0000 0.0106
-10.250 -1.0575 0.02087 0.01494 -0.0105 1.0000 0.0111
-10.000 -1.0386 0.02000 0.01400 -0.0095 1.0000 0.0116
-9.750 -1.0175 0.01938 0.01333 -0.0087 1.0000 0.0122
-9.500 -0.9968 0.01869 0.01256 -0.0079 1.0000 0.0127
-9.250 -0.9755 0.01806 0.01185 -0.0070 1.0000 0.0134
-9.000 -0.9543 0.01739 0.01109 -0.0061 1.0000 0.0140
-8.750 -0.9326 0.01680 0.01041 -0.0052 1.0000 0.0145
-8.500 -0.9115 0.01611 0.00969 -0.0043 1.0000 0.0156
-8.250 -0.8892 0.01559 0.00913 -0.0035 1.0000 0.0165
-8.000 -0.8663 0.01514 0.00864 -0.0027 1.0000 0.0177
-7.750 -0.8433 0.01470 0.00813 -0.0019 1.0000 0.0186
-7.500 -0.8208 0.01419 0.00757 -0.0011 1.0000 0.0199
-7.250 -0.7978 0.01376 0.00715 -0.0003 1.0000 0.0218
-7.000 -0.7745 0.01337 0.00672 0.0005 1.0000 0.0232
-6.750 -0.7507 0.01304 0.00635 0.0012 1.0000 0.0249
-6.500 -0.7280 0.01258 0.00589 0.0021 1.0000 0.0271
-6.250 -0.7046 0.01222 0.00552 0.0029 1.0000 0.0293
-6.000 -0.6808 0.01192 0.00519 0.0036 1.0000 0.0317
-5.750 -0.6575 0.01157 0.00483 0.0045 1.0000 0.0346
-5.250 -0.6017 0.01095 0.00419 0.0042 0.9828 0.0419
-5.000 -0.5619 0.01057 0.00385 0.0014 0.9633 0.0495
-4.750 -0.5137 0.01022 0.00352 -0.0033 0.9407 0.0596
-4.500 -0.4631 0.00988 0.00317 -0.0085 0.9106 0.0745
-4.250 -0.4250 0.00963 0.00289 -0.0109 0.8744 0.0936
-4.000 -0.3976 0.00941 0.00266 -0.0108 0.8433 0.1175
-3.750 -0.3735 0.00913 0.00242 -0.0101 0.8189 0.1528
-3.500 -0.3508 0.00878 0.00220 -0.0092 0.7973 0.2043
-3.250 -0.3287 0.00838 0.00197 -0.0081 0.7787 0.2692
-3.000 -0.3066 0.00799 0.00177 -0.0071 0.7615 0.3369
-2.750 -0.2838 0.00767 0.00163 -0.0061 0.7471 0.4023
-2.250 -0.2350 0.00736 0.00149 -0.0045 0.7218 0.4821
-2.000 -0.2097 0.00727 0.00143 -0.0039 0.7106 0.5113
-1.750 -0.1840 0.00722 0.00140 -0.0033 0.7005 0.5350
-1.500 -0.1586 0.00716 0.00138 -0.0027 0.6904 0.5595
-1.250 -0.1325 0.00712 0.00136 -0.0022 0.6808 0.5777
-1.000 -0.1064 0.00711 0.00134 -0.0016 0.6721 0.5949
-0.750 -0.0800 0.00708 0.00132 -0.0012 0.6629 0.6079
-0.500 -0.0535 0.00707 0.00131 -0.0008 0.6548 0.6190
-0.250 -0.0267 0.00707 0.00130 -0.0004 0.6460 0.6286
0.000 0.0000 0.00706 0.00130 0.0000 0.6378 0.6380
0.250 0.0267 0.00706 0.00130 0.0004 0.6290 0.6461
0.500 0.0535 0.00707 0.00131 0.0007 0.6192 0.6548
0.750 0.0799 0.00708 0.00132 0.0012 0.6082 0.6631
1.000 0.1064 0.00711 0.00134 0.0016 0.5953 0.6722
1.250 0.1324 0.00712 0.00136 0.0021 0.5781 0.6809
1.500 0.1584 0.00716 0.00137 0.0027 0.5577 0.6900
1.750 0.1840 0.00722 0.00140 0.0033 0.5354 0.7003
2.000 0.2096 0.00727 0.00143 0.0039 0.5106 0.7106
2.250 0.2349 0.00736 0.00148 0.0045 0.4820 0.7219
2.750 0.2841 0.00764 0.00163 0.0060 0.4071 0.7475
3.000 0.3066 0.00798 0.00178 0.0071 0.3389 0.7620
3.250 0.3283 0.00841 0.00198 0.0082 0.2638 0.7785
3.500 0.3505 0.00880 0.00220 0.0092 0.2011 0.7968
3.750 0.3736 0.00911 0.00242 0.0101 0.1558 0.8186
4.000 0.3976 0.00940 0.00265 0.0108 0.1193 0.8438
4.250 0.4251 0.00963 0.00289 0.0108 0.0937 0.8753
4.500 0.4630 0.00989 0.00317 0.0085 0.0737 0.9106
4.750 0.5132 0.01022 0.00351 0.0034 0.0600 0.9402
5.000 0.5617 0.01057 0.00385 -0.0013 0.0501 0.9631
5.250 0.6017 0.01094 0.00419 -0.0042 0.0422 0.9828
5.750 0.6575 0.01157 0.00484 -0.0045 0.0353 1.0000
6.000 0.6807 0.01193 0.00520 -0.0036 0.0320 1.0000
6.250 0.7046 0.01222 0.00552 -0.0029 0.0295 1.0000
6.500 0.7280 0.01257 0.00586 -0.0021 0.0268 1.0000
6.750 0.7510 0.01299 0.00630 -0.0013 0.0246 1.0000
7.000 0.7746 0.01335 0.00670 -0.0005 0.0230 1.0000
7.250 0.7979 0.01373 0.00712 0.0003 0.0216 1.0000
7.500 0.8208 0.01418 0.00756 0.0010 0.0200 1.0000
7.750 0.8435 0.01466 0.00810 0.0019 0.0185 1.0000
8.000 0.8665 0.01509 0.00858 0.0026 0.0173 1.0000
8.250 0.8893 0.01556 0.00909 0.0034 0.0163 1.0000
8.500 0.9114 0.01610 0.00966 0.0042 0.0153 1.0000
8.750 0.9322 0.01682 0.01042 0.0052 0.0143 1.0000
9.000 0.9540 0.01741 0.01112 0.0061 0.0137 1.0000
9.250 0.9756 0.01802 0.01181 0.0070 0.0131 1.0000
9.500 0.9969 0.01864 0.01250 0.0078 0.0124 1.0000
9.750 1.0175 0.01935 0.01329 0.0087 0.0120 1.0000
10.000 1.0379 0.02007 0.01407 0.0096 0.0114 1.0000
10.250 1.0567 0.02096 0.01502 0.0106 0.0110 1.0000
10.500 1.0738 0.02202 0.01620 0.0118 0.0106 1.0000
10.750 1.0917 0.02299 0.01730 0.0129 0.0103 1.0000
11.000 1.1108 0.02375 0.01818 0.0138 0.0099 1.0000
11.250 1.1277 0.02473 0.01928 0.0148 0.0095 1.0000
11.500 1.1426 0.02589 0.02056 0.0160 0.0092 1.0000
11.750 1.1572 0.02699 0.02178 0.0172 0.0090 1.0000
12.000 1.1697 0.02825 0.02317 0.0185 0.0088 1.0000
12.250 1.1789 0.02952 0.02458 0.0201 0.0087 1.0000
12.500 1.1859 0.03089 0.02607 0.0217 0.0085 1.0000
12.750 1.1910 0.03252 0.02783 0.0229 0.0083 1.0000
13.000 1.1937 0.03452 0.02996 0.0235 0.0082 1.0000
13.250 1.1927 0.03713 0.03272 0.0234 0.0081 1.0000
13.500 1.1924 0.03993 0.03566 0.0228 0.0080 1.0000
13.750 1.1838 0.04401 0.03991 0.0212 0.0077 1.0000
14.000 1.1737 0.04858 0.04466 0.0191 0.0078 1.0000
14.250 1.1667 0.05300 0.04925 0.0168 0.0079 1.0000
14.500 1.1494 0.05929 0.05572 0.0131 0.0077 1.0000
14.750 1.1350 0.06552 0.06213 0.0092 0.0078 1.0000
15.000 1.1139 0.07343 0.07021 0.0041 0.0078 1.0000
15.250 1.0868 0.08319 0.08016 -0.0021 0.0078 1.0000
15.500 1.0577 0.09403 0.09119 -0.0086 0.0079 1.0000
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