FX 79-L-100 (fx79l100-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 79-L-100 (fx79l100-il) Reynolds number: 50,000 Max Cl/Cd: 26.98 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx79l100-il-50000-n5.txt Download as CSV file: xf-fx79l100-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.7189 0.09755 0.09019 -0.0084 1.0000 0.0529
-11.000 -0.7332 0.09035 0.08300 -0.0129 1.0000 0.0526
-10.750 -0.7483 0.08392 0.07655 -0.0171 1.0000 0.0523
-10.500 -0.7696 0.07760 0.07015 -0.0210 1.0000 0.0521
-10.250 -0.7866 0.07276 0.06523 -0.0231 1.0000 0.0518
-10.000 -0.8064 0.06838 0.06072 -0.0234 1.0000 0.0518
-9.750 -0.8215 0.06420 0.05631 -0.0229 1.0000 0.0518
-9.500 -0.8317 0.06005 0.05184 -0.0221 1.0000 0.0521
-9.250 -0.8381 0.05605 0.04739 -0.0210 1.0000 0.0527
-9.000 -0.8319 0.05287 0.04412 -0.0202 1.0000 0.0546
-8.750 -0.8217 0.05037 0.04148 -0.0194 1.0000 0.0570
-8.500 -0.8129 0.04734 0.03809 -0.0182 1.0000 0.0592
-8.250 -0.8019 0.04408 0.03438 -0.0170 1.0000 0.0609
-8.000 -0.7875 0.04107 0.03086 -0.0158 1.0000 0.0633
-7.750 -0.7705 0.03853 0.02798 -0.0148 1.0000 0.0668
-7.500 -0.7508 0.03662 0.02598 -0.0140 1.0000 0.0711
-7.250 -0.7287 0.03447 0.02351 -0.0131 1.0000 0.0752
-7.000 -0.7061 0.03259 0.02141 -0.0123 1.0000 0.0806
-6.750 -0.6839 0.03109 0.01985 -0.0114 1.0000 0.0877
-6.500 -0.6598 0.02950 0.01811 -0.0105 1.0000 0.0941
-6.250 -0.6384 0.02822 0.01679 -0.0095 1.0000 0.1039
-6.000 -0.6181 0.02692 0.01551 -0.0083 1.0000 0.1145
-5.750 -0.5987 0.02566 0.01423 -0.0070 1.0000 0.1283
-5.500 -0.5801 0.02441 0.01303 -0.0057 1.0000 0.1479
-5.250 -0.5631 0.02304 0.01185 -0.0043 1.0000 0.1746
-5.000 -0.5476 0.02150 0.01073 -0.0029 1.0000 0.2267
-4.750 -0.5347 0.01994 0.00998 -0.0009 1.0000 0.3335
-4.500 -0.5203 0.01928 0.00991 0.0019 1.0000 0.4592
-4.250 -0.5033 0.01912 0.00988 0.0047 1.0000 0.5327
-4.000 -0.4857 0.01906 0.00983 0.0074 1.0000 0.5838
-3.750 -0.4680 0.01904 0.00980 0.0101 1.0000 0.6252
-3.500 -0.4501 0.01904 0.00981 0.0130 1.0000 0.6612
-3.250 -0.4319 0.01903 0.00980 0.0158 1.0000 0.6930
-3.000 -0.4137 0.01895 0.00970 0.0184 1.0000 0.7209
-2.750 -0.3944 0.01883 0.00957 0.0207 1.0000 0.7447
-2.500 -0.3757 0.01864 0.00931 0.0226 1.0000 0.7654
-2.250 -0.3557 0.01845 0.00909 0.0242 1.0000 0.7831
-2.000 -0.3363 0.01826 0.00887 0.0256 1.0000 0.8001
-1.750 -0.3172 0.01810 0.00867 0.0269 1.0000 0.8170
-1.500 -0.2977 0.01797 0.00851 0.0279 1.0000 0.8345
-1.250 -0.2555 0.01793 0.00838 0.0246 0.9853 0.8504
-1.000 -0.2083 0.01794 0.00832 0.0204 0.9712 0.8659
-0.750 -0.1590 0.01795 0.00826 0.0158 0.9580 0.8806
-0.500 -0.1066 0.01797 0.00824 0.0107 0.9462 0.8946
-0.250 -0.0534 0.01798 0.00822 0.0053 0.9337 0.9078
0.000 0.0000 0.01798 0.00822 0.0000 0.9210 0.9211
0.250 0.0533 0.01798 0.00822 -0.0054 0.9078 0.9337
0.500 0.1063 0.01797 0.00824 -0.0107 0.8946 0.9462
0.750 0.1589 0.01795 0.00826 -0.0158 0.8807 0.9580
1.000 0.2080 0.01794 0.00831 -0.0204 0.8659 0.9711
1.250 0.2553 0.01793 0.00838 -0.0246 0.8505 0.9852
1.500 0.2976 0.01797 0.00852 -0.0280 0.8345 1.0000
1.750 0.3171 0.01810 0.00867 -0.0270 0.8172 1.0000
2.000 0.3362 0.01826 0.00887 -0.0257 0.8003 1.0000
2.250 0.3556 0.01845 0.00909 -0.0242 0.7832 1.0000
2.500 0.3756 0.01864 0.00931 -0.0227 0.7655 1.0000
2.750 0.3944 0.01883 0.00956 -0.0207 0.7449 1.0000
3.000 0.4136 0.01895 0.00971 -0.0185 0.7213 1.0000
3.250 0.4318 0.01903 0.00980 -0.0159 0.6932 1.0000
3.500 0.4500 0.01904 0.00983 -0.0130 0.6611 1.0000
3.750 0.4679 0.01904 0.00980 -0.0101 0.6253 1.0000
4.000 0.4856 0.01906 0.00982 -0.0074 0.5837 1.0000
4.250 0.5033 0.01912 0.00987 -0.0047 0.5333 1.0000
4.500 0.5201 0.01928 0.00991 -0.0019 0.4583 1.0000
4.750 0.5348 0.01993 0.00998 0.0009 0.3358 1.0000
5.000 0.5476 0.02148 0.01073 0.0029 0.2275 1.0000
5.250 0.5630 0.02303 0.01185 0.0043 0.1745 1.0000
5.500 0.5800 0.02441 0.01302 0.0057 0.1478 1.0000
5.750 0.5986 0.02564 0.01421 0.0070 0.1282 1.0000
6.000 0.6181 0.02691 0.01550 0.0083 0.1148 1.0000
6.250 0.6384 0.02823 0.01678 0.0094 0.1045 1.0000
6.500 0.6599 0.02949 0.01812 0.0105 0.0943 1.0000
6.750 0.6838 0.03108 0.01984 0.0114 0.0878 1.0000
7.000 0.7058 0.03257 0.02139 0.0123 0.0804 1.0000
7.250 0.7287 0.03447 0.02352 0.0131 0.0751 1.0000
7.500 0.7508 0.03663 0.02599 0.0140 0.0711 1.0000
7.750 0.7704 0.03855 0.02800 0.0148 0.0667 1.0000
8.000 0.7872 0.04109 0.03090 0.0158 0.0630 1.0000
8.250 0.8017 0.04412 0.03443 0.0170 0.0608 1.0000
8.500 0.8127 0.04734 0.03808 0.0182 0.0590 1.0000
8.750 0.8220 0.05030 0.04139 0.0193 0.0568 1.0000
9.000 0.8334 0.05261 0.04376 0.0201 0.0540 1.0000
9.250 0.8377 0.05608 0.04743 0.0210 0.0527 1.0000
9.500 0.8303 0.06015 0.05196 0.0221 0.0519 1.0000
9.750 0.8203 0.06432 0.05644 0.0229 0.0517 1.0000
10.000 0.8049 0.06851 0.06086 0.0233 0.0517 1.0000
10.250 0.7861 0.07283 0.06530 0.0230 0.0518 1.0000
10.500 0.7681 0.07782 0.07038 0.0208 0.0521 1.0000
10.750 0.7458 0.08436 0.07698 0.0165 0.0522 1.0000
11.000 0.7317 0.09071 0.08335 0.0125 0.0526 1.0000
11.250 0.7188 0.09771 0.09036 0.0081 0.0529 1.0000
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Polar data table (+)
Polar graphs
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