FX 79-L-120 (fx79l120-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 79-L-120 (fx79l120-il) Reynolds number: 50,000 Max Cl/Cd: 27.94 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx79l120-il-50000-n5.txt Download as CSV file: xf-fx79l120-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.7428 0.09777 0.09006 -0.0139 1.0000 0.0655
-12.000 -0.7660 0.08931 0.08157 -0.0191 1.0000 0.0649
-11.750 -0.7946 0.08129 0.07346 -0.0242 1.0000 0.0644
-11.500 -0.8234 0.07450 0.06654 -0.0280 1.0000 0.0641
-11.250 -0.8486 0.06905 0.06091 -0.0300 1.0000 0.0639
-11.000 -0.8713 0.06467 0.05631 -0.0303 1.0000 0.0642
-10.750 -0.8899 0.06103 0.05242 -0.0289 1.0000 0.0646
-10.500 -0.9052 0.05743 0.04844 -0.0271 1.0000 0.0656
-10.250 -0.9111 0.05404 0.04469 -0.0255 1.0000 0.0666
-10.000 -0.9000 0.05149 0.04211 -0.0247 1.0000 0.0686
-9.750 -0.8908 0.04894 0.03936 -0.0236 1.0000 0.0704
-9.500 -0.8809 0.04655 0.03673 -0.0224 1.0000 0.0733
-9.250 -0.8710 0.04405 0.03382 -0.0210 1.0000 0.0767
-9.000 -0.8558 0.04164 0.03110 -0.0199 1.0000 0.0797
-8.750 -0.8361 0.03975 0.02918 -0.0193 1.0000 0.0831
-8.500 -0.8177 0.03799 0.02720 -0.0183 1.0000 0.0883
-8.250 -0.7966 0.03616 0.02518 -0.0175 1.0000 0.0933
-8.000 -0.7748 0.03467 0.02368 -0.0168 1.0000 0.0987
-7.750 -0.7531 0.03325 0.02204 -0.0159 1.0000 0.1062
-7.500 -0.7321 0.03191 0.02079 -0.0150 1.0000 0.1133
-7.250 -0.7114 0.03065 0.01945 -0.0139 1.0000 0.1223
-7.000 -0.6926 0.02946 0.01822 -0.0127 1.0000 0.1332
-6.750 -0.6755 0.02823 0.01707 -0.0113 1.0000 0.1449
-6.500 -0.6596 0.02701 0.01594 -0.0098 1.0000 0.1609
-6.250 -0.6447 0.02576 0.01482 -0.0082 1.0000 0.1813
-6.000 -0.6316 0.02445 0.01375 -0.0064 1.0000 0.2113
-5.750 -0.6199 0.02309 0.01276 -0.0044 1.0000 0.2564
-5.500 -0.6092 0.02190 0.01216 -0.0020 1.0000 0.3273
-5.250 -0.5959 0.02133 0.01206 0.0008 1.0000 0.4083
-5.000 -0.5803 0.02116 0.01208 0.0034 1.0000 0.4696
-4.750 -0.5640 0.02113 0.01205 0.0060 1.0000 0.5136
-4.500 -0.5478 0.02115 0.01208 0.0086 1.0000 0.5489
-4.250 -0.5319 0.02121 0.01213 0.0112 1.0000 0.5788
-4.000 -0.5175 0.02124 0.01213 0.0139 1.0000 0.6057
-3.750 -0.5027 0.02136 0.01226 0.0168 1.0000 0.6284
-3.500 -0.4905 0.02139 0.01227 0.0198 1.0000 0.6500
-3.250 -0.4778 0.02139 0.01223 0.0223 0.9986 0.6703
-3.000 -0.4390 0.02155 0.01232 0.0206 0.9821 0.6906
-2.750 -0.4002 0.02159 0.01223 0.0186 0.9670 0.7081
-2.500 -0.3608 0.02153 0.01205 0.0163 0.9529 0.7231
-2.250 -0.3207 0.02143 0.01181 0.0138 0.9402 0.7369
-2.000 -0.2783 0.02134 0.01163 0.0109 0.9290 0.7492
-1.750 -0.2398 0.02125 0.01146 0.0089 0.9161 0.7597
-1.500 -0.2036 0.02113 0.01124 0.0071 0.9034 0.7709
-1.250 -0.1672 0.02104 0.01108 0.0054 0.8913 0.7819
-1.000 -0.1285 0.02096 0.01096 0.0034 0.8808 0.7915
-0.750 -0.0973 0.02089 0.01083 0.0026 0.8680 0.8025
-0.500 -0.0650 0.02086 0.01077 0.0017 0.8562 0.8130
-0.250 -0.0309 0.02083 0.01073 0.0006 0.8457 0.8232
0.000 0.0001 0.02080 0.01069 0.0000 0.8345 0.8345
0.250 0.0310 0.02083 0.01072 -0.0006 0.8231 0.8456
0.500 0.0651 0.02086 0.01077 -0.0017 0.8130 0.8562
0.750 0.0974 0.02089 0.01083 -0.0026 0.8025 0.8681
1.000 0.1285 0.02097 0.01096 -0.0033 0.7915 0.8810
1.250 0.1674 0.02104 0.01108 -0.0053 0.7818 0.8914
1.500 0.2037 0.02113 0.01124 -0.0070 0.7708 0.9035
1.750 0.2398 0.02125 0.01146 -0.0088 0.7596 0.9162
2.000 0.2784 0.02134 0.01163 -0.0109 0.7491 0.9291
2.250 0.3209 0.02143 0.01181 -0.0138 0.7369 0.9403
2.500 0.3610 0.02153 0.01205 -0.0163 0.7231 0.9531
2.750 0.4004 0.02158 0.01222 -0.0186 0.7080 0.9671
3.000 0.4391 0.02155 0.01232 -0.0206 0.6907 0.9821
3.250 0.4780 0.02139 0.01223 -0.0223 0.6703 0.9987
3.500 0.4905 0.02139 0.01227 -0.0198 0.6499 1.0000
3.750 0.5026 0.02135 0.01225 -0.0168 0.6282 1.0000
4.000 0.5176 0.02123 0.01212 -0.0139 0.6055 1.0000
4.250 0.5319 0.02121 0.01213 -0.0112 0.5787 1.0000
4.500 0.5479 0.02116 0.01208 -0.0086 0.5489 1.0000
4.750 0.5640 0.02113 0.01205 -0.0060 0.5135 1.0000
5.000 0.5803 0.02116 0.01207 -0.0034 0.4690 1.0000
5.250 0.5959 0.02133 0.01206 -0.0008 0.4081 1.0000
5.500 0.6093 0.02190 0.01216 0.0020 0.3276 1.0000
5.750 0.6199 0.02309 0.01276 0.0045 0.2565 1.0000
6.000 0.6316 0.02445 0.01375 0.0064 0.2111 1.0000
6.250 0.6448 0.02577 0.01483 0.0082 0.1812 1.0000
6.500 0.6597 0.02702 0.01594 0.0098 0.1606 1.0000
6.750 0.6756 0.02823 0.01708 0.0113 0.1450 1.0000
7.000 0.6927 0.02947 0.01823 0.0127 0.1330 1.0000
7.250 0.7115 0.03065 0.01945 0.0139 0.1222 1.0000
7.500 0.7322 0.03192 0.02080 0.0150 0.1131 1.0000
7.750 0.7531 0.03327 0.02204 0.0159 0.1060 1.0000
8.000 0.7751 0.03469 0.02370 0.0168 0.0987 1.0000
8.250 0.7968 0.03619 0.02520 0.0175 0.0933 1.0000
8.500 0.8178 0.03800 0.02722 0.0183 0.0882 1.0000
8.750 0.8363 0.03977 0.02919 0.0193 0.0831 1.0000
9.000 0.8560 0.04166 0.03111 0.0199 0.0796 1.0000
9.250 0.8708 0.04406 0.03384 0.0210 0.0766 1.0000
9.500 0.8810 0.04657 0.03675 0.0224 0.0732 1.0000
9.750 0.8910 0.04895 0.03937 0.0236 0.0703 1.0000
10.000 0.9004 0.05149 0.04210 0.0247 0.0685 1.0000
10.250 0.9115 0.05403 0.04468 0.0254 0.0666 1.0000
10.500 0.9049 0.05744 0.04847 0.0271 0.0655 1.0000
10.750 0.8903 0.06103 0.05242 0.0288 0.0646 1.0000
11.000 0.8697 0.06473 0.05639 0.0302 0.0640 1.0000
11.250 0.8482 0.06917 0.06103 0.0299 0.0639 1.0000
11.500 0.8233 0.07459 0.06663 0.0278 0.0640 1.0000
11.750 0.7941 0.08144 0.07362 0.0239 0.0642 1.0000
12.000 0.7643 0.08977 0.08203 0.0186 0.0648 1.0000
12.250 0.7374 0.09907 0.09137 0.0127 0.0653 1.0000
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Polar data table (+)
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