FX 79-L-100 (fx79l100-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 79-L-100 (fx79l100-il) Reynolds number: 100,000 Max Cl/Cd: 38.61 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx79l100-il-100000.txt Download as CSV file: xf-fx79l100-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.6541 0.09102 0.08607 0.0022 1.0000 0.1744
-9.000 -0.8174 0.05953 0.05369 -0.0211 1.0000 0.0771
-8.750 -0.8135 0.05435 0.04839 -0.0205 1.0000 0.0743
-8.500 -0.8163 0.04895 0.04256 -0.0191 1.0000 0.0711
-8.250 -0.8110 0.04518 0.03839 -0.0176 1.0000 0.0720
-8.000 -0.8023 0.04149 0.03426 -0.0159 1.0000 0.0726
-7.750 -0.7903 0.03806 0.03037 -0.0142 1.0000 0.0731
-7.500 -0.7749 0.03485 0.02669 -0.0126 1.0000 0.0737
-7.250 -0.7573 0.03244 0.02377 -0.0109 1.0000 0.0767
-7.000 -0.7381 0.02992 0.02087 -0.0096 1.0000 0.0800
-6.750 -0.7156 0.02776 0.01861 -0.0088 1.0000 0.0838
-6.500 -0.6922 0.02607 0.01672 -0.0078 1.0000 0.0887
-6.250 -0.6689 0.02429 0.01483 -0.0069 1.0000 0.0952
-6.000 -0.6451 0.02286 0.01337 -0.0060 1.0000 0.1026
-5.750 -0.6222 0.02139 0.01194 -0.0051 1.0000 0.1122
-5.500 -0.6000 0.02010 0.01069 -0.0039 1.0000 0.1241
-5.250 -0.5795 0.01889 0.00962 -0.0026 1.0000 0.1395
-5.000 -0.5605 0.01775 0.00862 -0.0009 1.0000 0.1636
-4.750 -0.5456 0.01629 0.00759 0.0012 1.0000 0.2071
-4.500 -0.5419 0.01408 0.00678 0.0050 1.0000 0.3888
-4.250 -0.5301 0.01373 0.00696 0.0089 1.0000 0.5370
-4.000 -0.5125 0.01379 0.00709 0.0117 1.0000 0.5925
-3.750 -0.4941 0.01385 0.00717 0.0142 1.0000 0.6299
-3.500 -0.4756 0.01389 0.00722 0.0167 1.0000 0.6600
-3.250 -0.4582 0.01391 0.00723 0.0193 1.0000 0.6877
-3.000 -0.4410 0.01392 0.00730 0.0219 1.0000 0.7109
-2.750 -0.4271 0.01391 0.00730 0.0248 1.0000 0.7346
-2.500 -0.4141 0.01394 0.00739 0.0280 1.0000 0.7564
-2.250 -0.4040 0.01396 0.00740 0.0312 1.0000 0.7797
-2.000 -0.3921 0.01402 0.00752 0.0342 1.0000 0.8016
-1.750 -0.3765 0.01407 0.00756 0.0362 0.9981 0.8253
-1.500 -0.3305 0.01419 0.00768 0.0328 0.9863 0.8468
-1.250 -0.2820 0.01426 0.00768 0.0286 0.9747 0.8650
-1.000 -0.2327 0.01430 0.00767 0.0242 0.9638 0.8812
-0.750 -0.1799 0.01434 0.00767 0.0192 0.9541 0.8956
-0.500 -0.1195 0.01439 0.00769 0.0127 0.9469 0.9078
-0.250 -0.0623 0.01443 0.00771 0.0068 0.9372 0.9193
0.000 0.0000 0.01443 0.00770 0.0000 0.9296 0.9296
0.250 0.0622 0.01443 0.00771 -0.0068 0.9194 0.9372
0.500 0.1194 0.01440 0.00769 -0.0128 0.9078 0.9469
0.750 0.1801 0.01434 0.00767 -0.0193 0.8956 0.9542
1.000 0.2328 0.01430 0.00767 -0.0243 0.8815 0.9639
1.250 0.2822 0.01426 0.00769 -0.0287 0.8654 0.9748
1.500 0.3300 0.01420 0.00768 -0.0327 0.8469 0.9861
1.750 0.3764 0.01406 0.00756 -0.0362 0.8254 0.9981
2.000 0.3920 0.01402 0.00751 -0.0343 0.8015 1.0000
2.250 0.4039 0.01396 0.00742 -0.0312 0.7798 1.0000
2.500 0.4139 0.01393 0.00738 -0.0279 0.7562 1.0000
2.750 0.4270 0.01391 0.00729 -0.0248 0.7345 1.0000
3.000 0.4409 0.01392 0.00729 -0.0219 0.7108 1.0000
3.250 0.4581 0.01391 0.00725 -0.0193 0.6877 1.0000
3.500 0.4755 0.01389 0.00722 -0.0167 0.6602 1.0000
3.750 0.4940 0.01385 0.00716 -0.0142 0.6299 1.0000
4.000 0.5124 0.01379 0.00709 -0.0117 0.5924 1.0000
4.250 0.5301 0.01373 0.00696 -0.0089 0.5373 1.0000
4.500 0.5416 0.01409 0.00675 -0.0050 0.3870 1.0000
4.750 0.5457 0.01627 0.00759 -0.0013 0.2087 1.0000
5.000 0.5604 0.01774 0.00861 0.0009 0.1640 1.0000
5.250 0.5795 0.01889 0.00962 0.0025 0.1396 1.0000
5.500 0.6000 0.02010 0.01069 0.0039 0.1242 1.0000
5.750 0.6221 0.02137 0.01192 0.0051 0.1124 1.0000
6.000 0.6450 0.02285 0.01335 0.0060 0.1029 1.0000
6.250 0.6690 0.02427 0.01484 0.0069 0.0958 1.0000
6.500 0.6923 0.02610 0.01675 0.0078 0.0891 1.0000
6.750 0.7156 0.02776 0.01862 0.0088 0.0839 1.0000
7.000 0.7380 0.03002 0.02094 0.0095 0.0796 1.0000
7.250 0.7571 0.03241 0.02376 0.0110 0.0763 1.0000
7.500 0.7748 0.03488 0.02672 0.0126 0.0737 1.0000
7.750 0.7900 0.03805 0.03036 0.0143 0.0727 1.0000
8.000 0.8027 0.04116 0.03390 0.0159 0.0711 1.0000
8.250 0.8214 0.04322 0.03589 0.0164 0.0672 1.0000
8.500 0.8173 0.04871 0.04228 0.0190 0.0702 1.0000
8.750 0.8126 0.05439 0.04845 0.0205 0.0739 1.0000
9.000 0.8145 0.05961 0.05382 0.0212 0.0768 1.0000
9.250 0.6974 0.05163 0.04678 0.0260 0.0836 1.0000
9.500 0.6540 0.05805 0.05332 0.0243 0.0871 1.0000
9.750 0.6518 0.09957 0.09453 -0.0048 0.1610 1.0000
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Polar data table (+)
Polar graphs
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