FX 79-L-120 (fx79l120-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 79-L-120 (fx79l120-il) Reynolds number: 100,000 Max Cl/Cd: 40.93 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx79l120-il-100000.txt Download as CSV file: xf-fx79l120-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: FX 79-L-120
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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.5916 0.09233 0.08741 -0.0162 1.0000 0.1063
-11.250 -0.5684 0.09158 0.08664 -0.0133 1.0000 0.1080
-11.000 -0.8801 0.06995 0.06414 -0.0299 1.0000 0.0782
-10.750 -0.8880 0.06520 0.05931 -0.0291 1.0000 0.0774
-10.500 -0.9024 0.06088 0.05478 -0.0276 1.0000 0.0770
-10.250 -0.9107 0.05669 0.05036 -0.0261 1.0000 0.0763
-10.000 -0.9176 0.05256 0.04591 -0.0242 1.0000 0.0761
-9.750 -0.9196 0.04877 0.04174 -0.0223 1.0000 0.0761
-9.500 -0.9185 0.04554 0.03805 -0.0201 1.0000 0.0772
-9.250 -0.9139 0.04303 0.03499 -0.0177 1.0000 0.0785
-9.000 -0.9010 0.03918 0.03100 -0.0168 1.0000 0.0808
-8.750 -0.8833 0.03682 0.02849 -0.0158 1.0000 0.0829
-8.500 -0.8655 0.03482 0.02629 -0.0146 1.0000 0.0863
-8.250 -0.8488 0.03303 0.02410 -0.0129 1.0000 0.0902
-8.000 -0.8287 0.03063 0.02148 -0.0119 1.0000 0.0936
-7.750 -0.8065 0.02898 0.01982 -0.0112 1.0000 0.0986
-7.500 -0.7852 0.02769 0.01828 -0.0101 1.0000 0.1045
-7.250 -0.7611 0.02581 0.01648 -0.0095 1.0000 0.1103
-7.000 -0.7391 0.02470 0.01525 -0.0085 1.0000 0.1184
-6.750 -0.7164 0.02323 0.01392 -0.0077 1.0000 0.1269
-6.500 -0.6947 0.02202 0.01272 -0.0066 1.0000 0.1373
-6.250 -0.6742 0.02095 0.01172 -0.0053 1.0000 0.1506
-6.000 -0.6561 0.01975 0.01075 -0.0037 1.0000 0.1676
-5.750 -0.6400 0.01861 0.00984 -0.0018 1.0000 0.1924
-5.500 -0.6282 0.01721 0.00889 0.0007 1.0000 0.2359
-5.250 -0.6238 0.01553 0.00814 0.0043 1.0000 0.3461
-5.000 -0.6149 0.01502 0.00827 0.0080 1.0000 0.4692
-4.750 -0.6005 0.01512 0.00846 0.0110 1.0000 0.5255
-4.500 -0.5864 0.01530 0.00866 0.0138 1.0000 0.5593
-4.250 -0.5750 0.01551 0.00887 0.0170 1.0000 0.5858
-4.000 -0.5649 0.01572 0.00909 0.0201 1.0000 0.6073
-3.750 -0.5542 0.01596 0.00934 0.0230 1.0000 0.6266
-3.500 -0.5346 0.01625 0.00962 0.0242 0.9971 0.6478
-3.250 -0.4896 0.01660 0.00991 0.0210 0.9848 0.6725
-3.000 -0.4458 0.01695 0.01028 0.0185 0.9735 0.6951
-2.750 -0.4036 0.01717 0.01045 0.0161 0.9621 0.7168
-2.500 -0.3622 0.01731 0.01057 0.0140 0.9514 0.7361
-2.250 -0.3141 0.01740 0.01061 0.0106 0.9441 0.7528
-2.000 -0.2755 0.01738 0.01057 0.0088 0.9328 0.7666
-1.750 -0.2341 0.01735 0.01052 0.0066 0.9231 0.7776
-1.500 -0.1914 0.01724 0.01035 0.0039 0.9143 0.7888
-1.250 -0.1597 0.01714 0.01019 0.0030 0.9023 0.8007
-1.000 -0.1224 0.01710 0.01015 0.0016 0.8924 0.8096
-0.750 -0.0879 0.01699 0.01000 0.0004 0.8824 0.8198
-0.500 -0.0607 0.01696 0.00996 0.0006 0.8705 0.8305
-0.250 -0.0284 0.01695 0.00994 0.0000 0.8607 0.8395
0.000 0.0000 0.01690 0.00988 0.0000 0.8506 0.8506
0.250 0.0285 0.01695 0.00994 0.0000 0.8395 0.8606
0.500 0.0607 0.01696 0.00996 -0.0005 0.8302 0.8706
0.750 0.0880 0.01699 0.01000 -0.0004 0.8197 0.8824
1.000 0.1225 0.01710 0.01015 -0.0016 0.8096 0.8924
1.250 0.1598 0.01714 0.01019 -0.0030 0.8007 0.9023
1.500 0.1914 0.01724 0.01035 -0.0038 0.7888 0.9143
1.750 0.2342 0.01735 0.01052 -0.0066 0.7777 0.9232
2.000 0.2757 0.01739 0.01057 -0.0088 0.7668 0.9328
2.250 0.3146 0.01740 0.01062 -0.0107 0.7528 0.9441
2.500 0.3627 0.01732 0.01058 -0.0141 0.7362 0.9517
2.750 0.4040 0.01717 0.01045 -0.0162 0.7167 0.9622
3.000 0.4459 0.01694 0.01027 -0.0185 0.6948 0.9735
3.250 0.4897 0.01660 0.00991 -0.0210 0.6724 0.9848
3.500 0.5346 0.01624 0.00959 -0.0242 0.6471 0.9971
3.750 0.5542 0.01596 0.00933 -0.0229 0.6264 1.0000
4.000 0.5649 0.01573 0.00909 -0.0201 0.6073 1.0000
4.250 0.5750 0.01551 0.00887 -0.0169 0.5857 1.0000
4.500 0.5864 0.01530 0.00866 -0.0138 0.5592 1.0000
4.750 0.6005 0.01512 0.00845 -0.0109 0.5252 1.0000
5.000 0.6148 0.01502 0.00827 -0.0080 0.4686 1.0000
5.250 0.6238 0.01553 0.00814 -0.0042 0.3454 1.0000
5.500 0.6283 0.01721 0.00889 -0.0007 0.2361 1.0000
5.750 0.6401 0.01861 0.00985 0.0018 0.1924 1.0000
6.000 0.6561 0.01975 0.01074 0.0037 0.1673 1.0000
6.250 0.6743 0.02095 0.01172 0.0053 0.1505 1.0000
6.500 0.6947 0.02203 0.01272 0.0066 0.1371 1.0000
6.750 0.7164 0.02323 0.01393 0.0077 0.1267 1.0000
7.000 0.7391 0.02469 0.01526 0.0085 0.1181 1.0000
7.250 0.7612 0.02582 0.01649 0.0095 0.1102 1.0000
7.500 0.7852 0.02770 0.01830 0.0101 0.1044 1.0000
7.750 0.8066 0.02902 0.01987 0.0113 0.0985 1.0000
8.000 0.8288 0.03065 0.02150 0.0120 0.0936 1.0000
8.250 0.8488 0.03305 0.02412 0.0130 0.0902 1.0000
8.500 0.8656 0.03483 0.02630 0.0146 0.0863 1.0000
8.750 0.8834 0.03683 0.02850 0.0158 0.0830 1.0000
9.000 0.9012 0.03922 0.03104 0.0167 0.0806 1.0000
9.250 0.9146 0.04326 0.03519 0.0175 0.0786 1.0000
9.500 0.9186 0.04558 0.03809 0.0201 0.0772 1.0000
9.750 0.9192 0.04881 0.04179 0.0223 0.0760 1.0000
10.000 0.9169 0.05264 0.04601 0.0243 0.0760 1.0000
10.250 0.9110 0.05669 0.05037 0.0261 0.0763 1.0000
10.500 0.9019 0.06092 0.05484 0.0276 0.0769 1.0000
10.750 0.8913 0.06537 0.05946 0.0288 0.0776 1.0000
11.000 0.8795 0.07002 0.06422 0.0299 0.0782 1.0000
11.250 0.6977 0.09835 0.09311 0.0092 0.1079 1.0000
11.500 0.7267 0.09788 0.09267 0.0143 0.1064 1.0000
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Polar data table (+)
Polar graphs
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