FX 79-L-100 (fx79l100-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 79-L-100 (fx79l100-il) Reynolds number: 200,000 Max Cl/Cd: 41.49 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx79l100-il-200000-n5.txt Download as CSV file: xf-fx79l100-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.9100 0.06784 0.06377 -0.0171 1.0000 0.0153
-12.250 -0.9436 0.05874 0.05436 -0.0233 1.0000 0.0151
-12.000 -0.9603 0.05342 0.04882 -0.0262 1.0000 0.0152
-11.750 -0.9706 0.04958 0.04480 -0.0277 1.0000 0.0154
-11.500 -0.9844 0.04560 0.04055 -0.0279 1.0000 0.0154
-11.250 -0.9899 0.04306 0.03782 -0.0268 1.0000 0.0156
-11.000 -0.9951 0.04054 0.03507 -0.0247 1.0000 0.0158
-10.750 -0.9936 0.03821 0.03250 -0.0229 1.0000 0.0161
-10.500 -0.9884 0.03601 0.03003 -0.0212 1.0000 0.0168
-10.250 -0.9798 0.03384 0.02759 -0.0197 1.0000 0.0172
-10.000 -0.9692 0.03166 0.02511 -0.0181 1.0000 0.0178
-9.750 -0.9554 0.02982 0.02296 -0.0167 1.0000 0.0186
-9.500 -0.9402 0.02814 0.02106 -0.0155 1.0000 0.0194
-9.250 -0.9230 0.02713 0.02000 -0.0145 1.0000 0.0204
-9.000 -0.9046 0.02606 0.01883 -0.0135 1.0000 0.0214
-8.750 -0.8853 0.02506 0.01769 -0.0125 1.0000 0.0228
-8.500 -0.8659 0.02384 0.01629 -0.0114 1.0000 0.0240
-8.250 -0.8462 0.02270 0.01500 -0.0102 1.0000 0.0253
-8.000 -0.8270 0.02167 0.01394 -0.0092 1.0000 0.0268
-7.750 -0.8059 0.02098 0.01319 -0.0083 1.0000 0.0287
-7.500 -0.7849 0.02017 0.01228 -0.0073 1.0000 0.0306
-7.250 -0.7636 0.01939 0.01138 -0.0062 1.0000 0.0324
-7.000 -0.7442 0.01845 0.01045 -0.0051 1.0000 0.0348
-6.750 -0.7225 0.01784 0.00981 -0.0041 1.0000 0.0377
-6.500 -0.7009 0.01722 0.00909 -0.0031 1.0000 0.0405
-6.250 -0.6801 0.01651 0.00833 -0.0020 1.0000 0.0432
-6.000 -0.6587 0.01592 0.00775 -0.0010 1.0000 0.0477
-5.750 -0.6364 0.01545 0.00721 0.0000 1.0000 0.0524
-5.500 -0.6153 0.01483 0.00661 0.0011 1.0000 0.0580
-5.250 -0.5930 0.01440 0.00613 0.0021 1.0000 0.0646
-5.000 -0.5715 0.01388 0.00567 0.0032 1.0000 0.0740
-4.750 -0.5497 0.01342 0.00524 0.0042 1.0000 0.0851
-4.500 -0.5282 0.01295 0.00485 0.0053 1.0000 0.1036
-4.250 -0.5073 0.01245 0.00448 0.0064 1.0000 0.1304
-4.000 -0.4823 0.01180 0.00407 0.0065 0.9898 0.1797
-3.750 -0.4487 0.01093 0.00366 0.0045 0.9711 0.2765
-3.500 -0.4148 0.01017 0.00338 0.0027 0.9497 0.3923
-3.250 -0.3772 0.00981 0.00327 0.0005 0.9281 0.4702
-3.000 -0.3384 0.00965 0.00318 -0.0017 0.9055 0.5167
-2.750 -0.3019 0.00956 0.00308 -0.0034 0.8831 0.5504
-2.500 -0.2693 0.00951 0.00302 -0.0042 0.8607 0.5772
-2.000 -0.2120 0.00948 0.00293 -0.0040 0.8210 0.6231
-1.750 -0.1853 0.00949 0.00289 -0.0035 0.8037 0.6411
-1.500 -0.1588 0.00948 0.00284 -0.0029 0.7882 0.6548
-1.250 -0.1323 0.00947 0.00280 -0.0024 0.7742 0.6660
-1.000 -0.1059 0.00947 0.00274 -0.0019 0.7612 0.6766
-0.500 -0.0530 0.00946 0.00268 -0.0009 0.7376 0.6963
-0.250 -0.0265 0.00946 0.00266 -0.0005 0.7265 0.7062
0.000 0.0000 0.00947 0.00265 0.0000 0.7165 0.7166
0.250 0.0264 0.00946 0.00266 0.0005 0.7062 0.7266
0.500 0.0529 0.00946 0.00268 0.0009 0.6965 0.7375
1.000 0.1058 0.00947 0.00274 0.0019 0.6768 0.7614
1.250 0.1323 0.00947 0.00280 0.0024 0.6663 0.7743
1.500 0.1588 0.00948 0.00284 0.0029 0.6549 0.7884
1.750 0.1853 0.00949 0.00289 0.0035 0.6413 0.8038
2.000 0.2119 0.00948 0.00293 0.0040 0.6231 0.8211
2.250 0.2393 0.00949 0.00297 0.0044 0.6017 0.8401
2.500 0.2692 0.00951 0.00302 0.0042 0.5770 0.8605
2.750 0.3018 0.00956 0.00308 0.0034 0.5504 0.8832
3.000 0.3384 0.00965 0.00318 0.0017 0.5159 0.9058
3.250 0.3771 0.00981 0.00327 -0.0005 0.4704 0.9278
3.500 0.4146 0.01016 0.00338 -0.0027 0.3952 0.9493
3.750 0.4485 0.01095 0.00366 -0.0045 0.2742 0.9711
4.000 0.4822 0.01180 0.00407 -0.0065 0.1797 0.9898
4.250 0.5073 0.01245 0.00448 -0.0064 0.1308 1.0000
4.500 0.5281 0.01295 0.00484 -0.0053 0.1034 1.0000
4.750 0.5497 0.01341 0.00524 -0.0042 0.0857 1.0000
5.000 0.5714 0.01388 0.00567 -0.0032 0.0740 1.0000
5.250 0.5929 0.01440 0.00613 -0.0021 0.0647 1.0000
5.500 0.6153 0.01483 0.00661 -0.0012 0.0578 1.0000
5.750 0.6363 0.01544 0.00721 0.0000 0.0525 1.0000
6.000 0.6585 0.01593 0.00777 0.0010 0.0481 1.0000
6.250 0.6802 0.01649 0.00832 0.0019 0.0437 1.0000
6.500 0.7008 0.01722 0.00909 0.0031 0.0407 1.0000
6.750 0.7224 0.01785 0.00982 0.0042 0.0379 1.0000
7.000 0.7443 0.01843 0.01042 0.0050 0.0346 1.0000
7.250 0.7636 0.01939 0.01138 0.0062 0.0324 1.0000
7.500 0.7851 0.02012 0.01223 0.0073 0.0305 1.0000
7.750 0.8063 0.02084 0.01304 0.0082 0.0282 1.0000
8.000 0.8273 0.02152 0.01377 0.0091 0.0263 1.0000
8.250 0.8459 0.02271 0.01499 0.0102 0.0249 1.0000
8.500 0.8659 0.02379 0.01625 0.0113 0.0237 1.0000
8.750 0.8852 0.02501 0.01765 0.0125 0.0225 1.0000
9.000 0.9041 0.02614 0.01891 0.0135 0.0213 1.0000
9.250 0.9230 0.02700 0.01984 0.0144 0.0202 1.0000
9.500 0.9391 0.02828 0.02117 0.0155 0.0191 1.0000
9.750 0.9551 0.02986 0.02303 0.0168 0.0184 1.0000
10.000 0.9686 0.03177 0.02523 0.0182 0.0177 1.0000
10.250 0.9797 0.03383 0.02758 0.0197 0.0171 1.0000
10.500 0.9880 0.03602 0.03005 0.0212 0.0167 1.0000
10.750 0.9926 0.03839 0.03269 0.0229 0.0162 1.0000
11.000 0.9936 0.04076 0.03531 0.0247 0.0159 1.0000
11.250 0.9895 0.04313 0.03789 0.0268 0.0156 1.0000
11.500 0.9833 0.04576 0.04072 0.0279 0.0154 1.0000
11.750 0.9726 0.04931 0.04450 0.0277 0.0153 1.0000
12.000 0.9574 0.05391 0.04934 0.0260 0.0153 1.0000
12.250 0.9374 0.05985 0.05553 0.0226 0.0153 1.0000
12.500 0.9063 0.06865 0.06460 0.0164 0.0154 1.0000
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Polar data table (+)
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