USA 5 AIRFOIL (usa5-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
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Airfoil: USA 5 AIRFOIL (usa5-il) Reynolds number: 1,000,000 Max Cl/Cd: 99.74 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa5-il-1000000-n5.txt Download as CSV file: xf-usa5-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: USA 5 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3567 0.12420 0.12254 -0.0196 1.0000 0.0035
-10.500 -0.3521 0.12098 0.11933 -0.0204 1.0000 0.0035
-8.500 -0.3205 0.09756 0.09603 -0.0251 0.9994 0.0042
-8.000 -0.2955 0.09048 0.08895 -0.0314 0.9915 0.0048
-7.750 -0.2823 0.08689 0.08537 -0.0350 0.9865 0.0046
-7.500 -0.2705 0.08313 0.08162 -0.0387 0.9800 0.0046
-7.250 -0.2538 0.07900 0.07748 -0.0441 0.9726 0.0054
-7.000 -0.2314 0.07464 0.07311 -0.0508 0.9678 0.0049
-6.750 -0.2037 0.06771 0.06615 -0.0610 0.9596 0.0034
-6.500 -0.1757 0.06283 0.06122 -0.0689 0.9507 0.0032
-6.250 -0.1503 0.05807 0.05639 -0.0756 0.9375 0.0031
-6.000 -0.1301 0.05388 0.05212 -0.0800 0.9224 0.0030
-5.000 -0.0932 0.01412 0.01028 -0.0863 0.8554 0.0029
-4.750 -0.0721 0.01246 0.00822 -0.0849 0.8407 0.0031
-4.500 -0.0493 0.01149 0.00694 -0.0838 0.8228 0.0033
-4.250 -0.0262 0.01083 0.00600 -0.0826 0.8010 0.0035
-4.000 -0.0030 0.01022 0.00513 -0.0815 0.7765 0.0036
-3.750 0.0199 0.00953 0.00418 -0.0803 0.7523 0.0040
-3.500 0.0439 0.00933 0.00381 -0.0795 0.7255 0.0044
-3.250 0.0671 0.00914 0.00342 -0.0784 0.6905 0.0049
-3.000 0.0913 0.00886 0.00295 -0.0774 0.6657 0.0053
-2.750 0.1161 0.00866 0.00260 -0.0767 0.6466 0.0058
-2.500 0.1406 0.00836 0.00212 -0.0758 0.6283 0.0070
-2.250 0.1656 0.00823 0.00189 -0.0751 0.6089 0.0086
-2.000 0.1902 0.00817 0.00169 -0.0744 0.5824 0.0104
-1.750 0.2148 0.00808 0.00150 -0.0736 0.5579 0.0168
-1.500 0.2391 0.00806 0.00137 -0.0728 0.5262 0.0283
-1.250 0.2627 0.00817 0.00129 -0.0719 0.4808 0.0345
-1.000 0.2864 0.00828 0.00124 -0.0711 0.4418 0.0419
-0.750 0.3110 0.00829 0.00122 -0.0704 0.4182 0.0627
-0.500 0.3365 0.00834 0.00123 -0.0699 0.4013 0.0769
-0.250 0.3622 0.00840 0.00121 -0.0694 0.3876 0.0814
0.000 0.3882 0.00844 0.00121 -0.0690 0.3767 0.0864
0.250 0.4141 0.00849 0.00120 -0.0686 0.3669 0.0898
0.500 0.4402 0.00855 0.00120 -0.0682 0.3579 0.0920
0.750 0.4662 0.00857 0.00120 -0.0678 0.3508 0.0960
1.000 0.4921 0.00861 0.00121 -0.0674 0.3436 0.0991
1.250 0.5182 0.00865 0.00123 -0.0670 0.3374 0.1021
1.500 0.5441 0.00870 0.00126 -0.0667 0.3306 0.1051
1.750 0.5700 0.00875 0.00129 -0.0663 0.3241 0.1090
2.000 0.5958 0.00880 0.00133 -0.0659 0.3170 0.1128
2.250 0.6215 0.00886 0.00138 -0.0654 0.3107 0.1171
2.750 0.6732 0.00894 0.00150 -0.0647 0.3008 0.1348
3.000 0.6984 0.00894 0.00160 -0.0642 0.2963 0.1809
3.250 0.7222 0.00876 0.00175 -0.0635 0.2916 0.3402
3.750 0.8687 0.00871 0.00255 -0.0861 0.1700 1.0000
4.000 0.8922 0.00899 0.00276 -0.0853 0.1555 1.0000
4.250 0.9157 0.00927 0.00297 -0.0845 0.1408 1.0000
4.500 0.9311 0.01038 0.00358 -0.0825 0.0428 1.0000
4.750 0.9528 0.01085 0.00397 -0.0813 0.0115 1.0000
5.000 0.9767 0.01108 0.00424 -0.0806 0.0093 1.0000
5.250 0.9997 0.01140 0.00459 -0.0797 0.0068 1.0000
5.500 1.0230 0.01168 0.00491 -0.0789 0.0059 1.0000
5.750 1.0459 0.01200 0.00525 -0.0780 0.0050 1.0000
6.000 1.0673 0.01247 0.00578 -0.0768 0.0041 1.0000
6.250 1.0902 0.01275 0.00609 -0.0759 0.0036 1.0000
6.500 1.1116 0.01319 0.00658 -0.0748 0.0033 1.0000
6.750 1.1332 0.01358 0.00700 -0.0737 0.0028 1.0000
7.000 1.1526 0.01420 0.00769 -0.0722 0.0026 1.0000
7.250 1.1706 0.01492 0.00850 -0.0705 0.0024 1.0000
7.500 1.1888 0.01559 0.00930 -0.0688 0.0022 1.0000
7.750 1.2051 0.01638 0.01018 -0.0668 0.0022 1.0000
8.000 1.2217 0.01710 0.01099 -0.0649 0.0020 1.0000
8.250 1.2384 0.01776 0.01172 -0.0630 0.0018 1.0000
8.500 1.2490 0.01888 0.01296 -0.0601 0.0017 1.0000
8.750 1.2698 0.01914 0.01323 -0.0592 0.0015 1.0000
9.000 1.2826 0.01999 0.01415 -0.0568 0.0015 1.0000
9.250 1.2910 0.02112 0.01538 -0.0537 0.0014 1.0000
9.500 1.2902 0.02279 0.01720 -0.0490 0.0013 1.0000
9.750 1.2939 0.02385 0.01837 -0.0450 0.0013 1.0000
10.000 1.2941 0.02537 0.02001 -0.0408 0.0013 1.0000
10.250 1.2955 0.02711 0.02187 -0.0370 0.0013 1.0000
10.500 1.2980 0.02971 0.02466 -0.0335 0.0011 1.0000
10.750 1.3051 0.03354 0.02874 -0.0305 0.0009 1.0000
11.000 1.3082 0.03654 0.03195 -0.0275 0.0009 1.0000
11.250 1.3069 0.03948 0.03510 -0.0243 0.0009 1.0000
11.500 1.3011 0.04246 0.03834 -0.0210 0.0008 1.0000
11.750 1.2927 0.04544 0.04153 -0.0181 0.0009 1.0000
12.000 1.2832 0.04848 0.04475 -0.0157 0.0009 1.0000
12.250 1.2684 0.05231 0.04879 -0.0137 0.0009 1.0000
12.500 1.2532 0.05635 0.05302 -0.0126 0.0009 1.0000
12.750 1.2391 0.06049 0.05733 -0.0123 0.0009 1.0000
13.000 1.2229 0.06523 0.06224 -0.0129 0.0009 1.0000
13.250 1.2045 0.07076 0.06794 -0.0143 0.0009 1.0000
13.500 1.1896 0.07602 0.07333 -0.0163 0.0009 1.0000
13.750 1.1736 0.08191 0.07937 -0.0189 0.0009 1.0000
14.000 1.1548 0.08881 0.08641 -0.0224 0.0009 1.0000
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