NACA 22112 (naca22112-jf) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: NACA 22112 (naca22112-jf) Reynolds number: 100,000 Max Cl/Cd: 33.9 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca22112-jf-100000.txt Download as CSV file: xf-naca22112-jf-100000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 22112
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.6173 0.10048 0.09554 -0.0086 1.0000 0.1537
-9.750 -0.5756 0.09940 0.09442 -0.0008 1.0000 0.1609
-9.500 -0.6320 0.09134 0.08650 -0.0134 1.0000 0.1687
-9.250 -0.5801 0.09188 0.08700 -0.0033 1.0000 0.1798
-9.000 -0.5836 0.08789 0.08307 -0.0043 1.0000 0.1899
-8.750 -0.6312 0.08140 0.07666 -0.0121 1.0000 0.1987
-8.500 -0.6096 0.07941 0.07472 -0.0090 1.0000 0.2129
-8.250 -0.6057 0.07686 0.07221 -0.0074 1.0000 0.2279
-6.750 -0.6547 0.03882 0.03103 -0.0083 1.0000 0.1079
-6.500 -0.6346 0.03555 0.02718 -0.0057 1.0000 0.0931
-6.250 -0.6151 0.03261 0.02395 -0.0039 1.0000 0.0876
-6.000 -0.5955 0.03128 0.02195 -0.0011 1.0000 0.0829
-5.750 -0.5744 0.02928 0.01978 0.0004 1.0000 0.0833
-5.500 -0.5524 0.02749 0.01785 0.0017 1.0000 0.0841
-5.250 -0.5292 0.02603 0.01625 0.0031 1.0000 0.0840
-5.000 -0.5055 0.02460 0.01476 0.0043 1.0000 0.0844
-4.750 -0.4824 0.02330 0.01348 0.0054 1.0000 0.0864
-4.500 -0.4601 0.02225 0.01246 0.0066 1.0000 0.0897
-4.250 -0.4382 0.02132 0.01154 0.0080 1.0000 0.0923
-4.000 -0.4172 0.02051 0.01074 0.0096 1.0000 0.0945
-3.750 -0.3990 0.01948 0.00985 0.0113 1.0000 0.0986
-3.500 -0.3816 0.01873 0.00918 0.0130 1.0000 0.1044
-3.250 -0.3630 0.01822 0.00862 0.0147 1.0000 0.1100
-3.000 -0.3447 0.01754 0.00802 0.0161 1.0000 0.1202
-2.750 -0.3250 0.01685 0.00754 0.0173 1.0000 0.1453
-2.500 -0.3129 0.01444 0.00743 0.0195 1.0000 0.5590
-2.250 -0.2997 0.01413 0.00803 0.0241 1.0000 0.7563
-2.000 -0.2832 0.01455 0.00869 0.0281 1.0000 0.8497
-1.750 -0.2517 0.01529 0.00943 0.0291 1.0000 0.9155
-1.500 -0.1684 0.01640 0.01035 0.0205 0.9998 0.9614
-1.250 -0.0326 0.01705 0.01074 0.0019 1.0000 0.9896
-1.000 0.0387 0.01695 0.01054 -0.0077 0.9957 1.0000
-0.750 0.1123 0.01657 0.01008 -0.0174 0.9778 1.0000
-0.500 0.1851 0.01601 0.00947 -0.0263 0.9569 1.0000
-0.250 0.2386 0.01542 0.00883 -0.0311 0.9243 1.0000
0.000 0.2690 0.01500 0.00833 -0.0312 0.8846 1.0000
0.250 0.2904 0.01471 0.00793 -0.0293 0.8464 1.0000
0.500 0.3097 0.01451 0.00759 -0.0272 0.8102 1.0000
0.750 0.3290 0.01438 0.00731 -0.0251 0.7749 1.0000
1.000 0.3489 0.01432 0.00709 -0.0232 0.7395 1.0000
1.250 0.3696 0.01432 0.00692 -0.0215 0.7034 1.0000
1.500 0.3906 0.01437 0.00679 -0.0199 0.6669 1.0000
1.750 0.4120 0.01447 0.00670 -0.0185 0.6301 1.0000
2.000 0.4332 0.01461 0.00665 -0.0170 0.5930 1.0000
2.250 0.4543 0.01482 0.00662 -0.0156 0.5557 1.0000
2.500 0.4753 0.01506 0.00668 -0.0142 0.5149 1.0000
2.750 0.4959 0.01539 0.00675 -0.0128 0.4746 1.0000
3.000 0.5164 0.01578 0.00691 -0.0114 0.4339 1.0000
3.250 0.5369 0.01626 0.00713 -0.0101 0.3968 1.0000
3.500 0.5575 0.01678 0.00744 -0.0088 0.3653 1.0000
3.750 0.5784 0.01736 0.00775 -0.0076 0.3410 1.0000
4.000 0.5998 0.01790 0.00818 -0.0065 0.3198 1.0000
4.250 0.6217 0.01848 0.00865 -0.0054 0.3038 1.0000
4.500 0.6437 0.01910 0.00913 -0.0044 0.2906 1.0000
4.750 0.6659 0.01967 0.00964 -0.0034 0.2784 1.0000
5.000 0.6881 0.02030 0.01029 -0.0025 0.2680 1.0000
5.250 0.7112 0.02106 0.01088 -0.0017 0.2599 1.0000
5.500 0.7332 0.02168 0.01165 -0.0007 0.2511 1.0000
5.750 0.7567 0.02250 0.01228 0.0000 0.2440 1.0000
6.000 0.7781 0.02319 0.01320 0.0011 0.2366 1.0000
6.250 0.8012 0.02398 0.01393 0.0019 0.2306 1.0000
6.500 0.8231 0.02493 0.01499 0.0028 0.2247 1.0000
6.750 0.8445 0.02575 0.01591 0.0038 0.2184 1.0000
7.000 0.8682 0.02678 0.01684 0.0043 0.2132 1.0000
7.250 0.8875 0.02786 0.01822 0.0056 0.2081 1.0000
7.500 0.9085 0.02883 0.01932 0.0066 0.2026 1.0000
7.750 0.9319 0.02996 0.02036 0.0071 0.1979 1.0000
8.000 0.9487 0.03137 0.02214 0.0086 0.1933 1.0000
8.250 0.9676 0.03261 0.02358 0.0097 0.1883 1.0000
8.500 0.9900 0.03368 0.02463 0.0103 0.1837 1.0000
8.750 1.0056 0.03552 0.02674 0.0116 0.1796 1.0000
9.000 1.0183 0.03732 0.02892 0.0132 0.1750 1.0000
9.250 1.0387 0.03849 0.03013 0.0140 0.1704 1.0000
9.500 1.0594 0.04028 0.03188 0.0144 0.1664 1.0000
9.750 1.0598 0.04293 0.03514 0.0170 0.1626 1.0000
10.000 1.0665 0.04522 0.03775 0.0188 0.1584 1.0000
10.250 1.0922 0.04591 0.03833 0.0190 0.1540 1.0000
10.500 1.0979 0.04881 0.04143 0.0205 0.1507 1.0000
10.750 1.0780 0.05310 0.04628 0.0235 0.1482 1.0000
11.000 1.0516 0.05795 0.05152 0.0261 0.1463 1.0000
11.250 1.0021 0.06433 0.05819 0.0284 0.1466 1.0000
11.500 0.9173 0.07737 0.07142 0.0234 0.1497 1.0000
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Polar data table (+)
Polar graphs
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