WORTMANN FX 71-089A AIRFOIL (fx71089a-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: WORTMANN FX 71-089A AIRFOIL (fx71089a-il) Reynolds number: 50,000 Max Cl/Cd: 19.71 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx71089a-il-50000.txt Download as CSV file: xf-fx71089a-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 71-089A AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5954 0.12437 0.11624 0.0238 1.0000 0.3034
-9.750 -0.5677 0.11887 0.11071 0.0245 1.0000 0.3108
-9.500 -0.5896 0.11803 0.10998 0.0233 1.0000 0.3218
-9.250 -0.5554 0.11252 0.10439 0.0243 1.0000 0.3299
-9.000 -0.5634 0.11015 0.10210 0.0237 1.0000 0.3406
-8.750 -0.5508 0.10693 0.09889 0.0241 1.0000 0.3525
-8.500 -0.5390 0.10321 0.09518 0.0243 1.0000 0.3621
-7.750 -0.5489 0.09660 0.08877 0.0257 1.0000 0.4070
-7.500 -0.5103 0.09145 0.08357 0.0262 1.0000 0.4179
-7.250 -0.5040 0.08842 0.08059 0.0266 1.0000 0.4306
-7.000 -0.5019 0.08571 0.07795 0.0273 1.0000 0.4452
-6.750 -0.6644 0.05829 0.04994 -0.0098 1.0000 0.2008
-6.500 -0.6699 0.05163 0.04256 -0.0112 1.0000 0.1876
-6.250 -0.6542 0.04815 0.03891 -0.0107 1.0000 0.1849
-6.000 -0.6391 0.04473 0.03526 -0.0101 1.0000 0.1823
-5.750 -0.6239 0.04145 0.03162 -0.0093 1.0000 0.1800
-5.500 -0.6068 0.03853 0.02833 -0.0083 1.0000 0.1786
-5.250 -0.5879 0.03609 0.02556 -0.0073 1.0000 0.1794
-5.000 -0.5677 0.03398 0.02314 -0.0062 1.0000 0.1821
-4.750 -0.5465 0.03203 0.02080 -0.0051 1.0000 0.1850
-4.500 -0.5239 0.03014 0.01863 -0.0040 1.0000 0.1879
-4.250 -0.5000 0.02843 0.01693 -0.0031 1.0000 0.1921
-4.000 -0.4756 0.02694 0.01534 -0.0021 1.0000 0.1982
-3.750 -0.4510 0.02551 0.01384 -0.0012 1.0000 0.2072
-3.500 -0.4262 0.02427 0.01259 -0.0001 1.0000 0.2213
-3.250 -0.4008 0.02293 0.01145 0.0008 1.0000 0.2406
-3.000 -0.3749 0.02149 0.01027 0.0017 1.0000 0.2748
-2.750 -0.3526 0.01971 0.00916 0.0032 1.0000 0.3556
-2.500 -0.3457 0.01754 0.00868 0.0083 1.0000 0.5586
-2.250 -0.3209 0.01731 0.00957 0.0153 1.0000 0.8278
-2.000 -0.0786 0.01866 0.00983 -0.0175 1.0000 1.0000
-1.750 -0.0697 0.01804 0.00915 -0.0161 1.0000 1.0000
-1.500 -0.0600 0.01757 0.00862 -0.0144 1.0000 1.0000
-1.250 -0.0500 0.01720 0.00821 -0.0124 1.0000 1.0000
-1.000 -0.0401 0.01691 0.00789 -0.0102 1.0000 1.0000
-0.750 -0.0302 0.01670 0.00766 -0.0077 1.0000 1.0000
-0.500 -0.0203 0.01655 0.00750 -0.0052 1.0000 1.0000
-0.250 -0.0102 0.01647 0.00741 -0.0026 1.0000 1.0000
0.000 0.0000 0.01644 0.00738 0.0000 1.0000 1.0000
0.250 0.0102 0.01647 0.00741 0.0026 1.0000 1.0000
0.500 0.0203 0.01655 0.00750 0.0052 1.0000 1.0000
0.750 0.0302 0.01670 0.00766 0.0077 1.0000 1.0000
1.000 0.0401 0.01691 0.00789 0.0102 1.0000 1.0000
1.250 0.0500 0.01720 0.00821 0.0124 1.0000 1.0000
1.500 0.0600 0.01757 0.00862 0.0144 1.0000 1.0000
1.750 0.0697 0.01804 0.00915 0.0161 1.0000 1.0000
2.000 0.0787 0.01865 0.00982 0.0175 1.0000 1.0000
2.250 0.3206 0.01731 0.00958 -0.0153 0.8288 1.0000
2.500 0.3457 0.01754 0.00868 -0.0083 0.5590 1.0000
2.750 0.3526 0.01971 0.00915 -0.0032 0.3558 1.0000
3.000 0.3748 0.02148 0.01026 -0.0017 0.2748 1.0000
3.250 0.4008 0.02293 0.01145 -0.0008 0.2406 1.0000
3.500 0.4262 0.02427 0.01259 0.0001 0.2212 1.0000
3.750 0.4509 0.02551 0.01384 0.0012 0.2072 1.0000
4.000 0.4755 0.02694 0.01534 0.0021 0.1982 1.0000
4.250 0.5000 0.02842 0.01692 0.0031 0.1921 1.0000
4.500 0.5239 0.03014 0.01862 0.0040 0.1879 1.0000
4.750 0.5465 0.03202 0.02080 0.0051 0.1850 1.0000
5.000 0.5677 0.03398 0.02314 0.0062 0.1820 1.0000
5.250 0.5878 0.03608 0.02555 0.0073 0.1794 1.0000
5.500 0.6068 0.03853 0.02833 0.0083 0.1786 1.0000
5.750 0.6239 0.04145 0.03161 0.0093 0.1799 1.0000
6.000 0.6391 0.04473 0.03525 0.0101 0.1823 1.0000
6.250 0.6542 0.04814 0.03889 0.0107 0.1849 1.0000
6.500 0.6699 0.05163 0.04256 0.0112 0.1876 1.0000
6.750 0.6645 0.05829 0.04994 0.0098 0.2008 1.0000
7.000 0.5027 0.08573 0.07796 -0.0274 0.4451 1.0000
7.250 0.5046 0.08843 0.08059 -0.0267 0.4305 1.0000
7.500 0.5107 0.09144 0.08356 -0.0262 0.4177 1.0000
7.750 0.5469 0.09643 0.08859 -0.0258 0.4069 1.0000
8.500 0.5400 0.10323 0.09521 -0.0244 0.3619 1.0000
8.750 0.5518 0.10696 0.09891 -0.0242 0.3526 1.0000
9.000 0.5645 0.11019 0.10214 -0.0238 0.3405 1.0000
9.250 0.5563 0.11253 0.10441 -0.0244 0.3298 1.0000
9.500 0.5912 0.11815 0.11010 -0.0234 0.3217 1.0000
9.750 0.5687 0.11890 0.11074 -0.0247 0.3107 1.0000
10.000 0.5944 0.12423 0.11610 -0.0240 0.3032 1.0000
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