NACA 22112 (naca22112-jf) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NACA 22112 (naca22112-jf) Reynolds number: 50,000 Max Cl/Cd: 26.4 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca22112-jf-50000-n5.txt Download as CSV file: xf-naca22112-jf-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.6993 0.08066 0.07283 -0.0281 1.0000 0.0576
-10.000 -0.7073 0.07683 0.06892 -0.0275 1.0000 0.0573
-9.750 -0.7143 0.07296 0.06494 -0.0269 1.0000 0.0569
-9.500 -0.7204 0.06917 0.06098 -0.0260 1.0000 0.0566
-9.250 -0.7245 0.06548 0.05708 -0.0248 1.0000 0.0563
-9.000 -0.7259 0.06192 0.05326 -0.0234 1.0000 0.0561
-8.750 -0.7245 0.05851 0.04956 -0.0219 1.0000 0.0559
-8.500 -0.7207 0.05529 0.04600 -0.0201 1.0000 0.0560
-8.250 -0.7152 0.05237 0.04264 -0.0181 1.0000 0.0566
-8.000 -0.7074 0.04978 0.03956 -0.0160 1.0000 0.0574
-7.750 -0.6950 0.04700 0.03650 -0.0144 1.0000 0.0584
-7.500 -0.6780 0.04441 0.03378 -0.0133 1.0000 0.0594
-7.250 -0.6607 0.04206 0.03120 -0.0119 1.0000 0.0600
-7.000 -0.6420 0.03990 0.02879 -0.0105 1.0000 0.0607
-6.750 -0.6220 0.03794 0.02663 -0.0092 1.0000 0.0619
-6.500 -0.6014 0.03623 0.02470 -0.0079 1.0000 0.0641
-6.250 -0.5798 0.03467 0.02288 -0.0066 1.0000 0.0663
-6.000 -0.5566 0.03321 0.02118 -0.0054 1.0000 0.0680
-5.750 -0.5319 0.03174 0.01960 -0.0044 1.0000 0.0693
-5.500 -0.5076 0.03016 0.01812 -0.0036 1.0000 0.0722
-5.250 -0.4848 0.02902 0.01698 -0.0025 1.0000 0.0759
-5.000 -0.4625 0.02802 0.01591 -0.0011 1.0000 0.0791
-4.500 -0.4236 0.02603 0.01389 0.0021 1.0000 0.0863
-4.250 -0.4054 0.02519 0.01300 0.0038 1.0000 0.0918
-4.000 -0.3872 0.02441 0.01215 0.0055 1.0000 0.0969
-3.750 -0.3694 0.02354 0.01130 0.0070 1.0000 0.1055
-3.500 -0.3511 0.02268 0.01054 0.0084 1.0000 0.1187
-3.250 -0.3350 0.02134 0.00980 0.0098 1.0000 0.1762
-3.000 -0.3308 0.01932 0.00970 0.0136 1.0000 0.5047
-2.750 -0.3169 0.01891 0.00996 0.0176 1.0000 0.6488
-2.500 -0.2972 0.01897 0.01033 0.0208 1.0000 0.7458
-2.250 -0.2703 0.01933 0.01079 0.0228 1.0000 0.8225
-2.000 -0.2178 0.02021 0.01160 0.0210 1.0000 0.9015
-1.750 -0.1541 0.02074 0.01190 0.0151 1.0000 0.9415
-1.500 -0.1042 0.02082 0.01180 0.0102 1.0000 0.9593
-1.250 -0.0405 0.02083 0.01164 0.0024 0.9898 0.9734
-1.000 0.0287 0.02072 0.01138 -0.0063 0.9742 0.9848
-0.750 0.0986 0.02049 0.01104 -0.0150 0.9567 0.9944
-0.500 0.1561 0.02019 0.01067 -0.0213 0.9311 1.0000
-0.250 0.1980 0.01992 0.01033 -0.0243 0.9002 1.0000
0.000 0.2338 0.01967 0.01000 -0.0257 0.8665 1.0000
0.250 0.2636 0.01946 0.00970 -0.0258 0.8309 1.0000
0.500 0.2890 0.01930 0.00941 -0.0248 0.7943 1.0000
0.750 0.3114 0.01921 0.00916 -0.0231 0.7576 1.0000
1.000 0.3317 0.01919 0.00898 -0.0212 0.7200 1.0000
1.250 0.3516 0.01923 0.00885 -0.0192 0.6828 1.0000
1.500 0.3714 0.01932 0.00875 -0.0173 0.6464 1.0000
1.750 0.3911 0.01946 0.00871 -0.0154 0.6108 1.0000
2.000 0.4108 0.01965 0.00872 -0.0136 0.5758 1.0000
2.250 0.4306 0.01989 0.00877 -0.0119 0.5417 1.0000
2.500 0.4503 0.02016 0.00887 -0.0103 0.5085 1.0000
2.750 0.4699 0.02048 0.00903 -0.0086 0.4757 1.0000
3.000 0.4895 0.02085 0.00924 -0.0071 0.4440 1.0000
3.250 0.5099 0.02126 0.00949 -0.0058 0.4139 1.0000
3.500 0.5302 0.02173 0.00979 -0.0045 0.3863 1.0000
3.750 0.5506 0.02223 0.01016 -0.0032 0.3610 1.0000
4.000 0.5713 0.02278 0.01056 -0.0020 0.3396 1.0000
4.250 0.5924 0.02335 0.01105 -0.0009 0.3197 1.0000
4.500 0.6134 0.02395 0.01158 0.0002 0.3028 1.0000
4.750 0.6347 0.02459 0.01212 0.0012 0.2887 1.0000
5.000 0.6561 0.02524 0.01269 0.0023 0.2767 1.0000
5.250 0.6778 0.02592 0.01340 0.0032 0.2648 1.0000
5.500 0.6995 0.02664 0.01412 0.0042 0.2548 1.0000
5.750 0.7214 0.02737 0.01481 0.0051 0.2462 1.0000
6.000 0.7434 0.02819 0.01571 0.0060 0.2381 1.0000
6.250 0.7652 0.02898 0.01650 0.0068 0.2306 1.0000
6.500 0.7868 0.02988 0.01750 0.0077 0.2234 1.0000
6.750 0.8084 0.03079 0.01847 0.0086 0.2169 1.0000
7.000 0.8306 0.03175 0.01943 0.0093 0.2116 1.0000
7.250 0.8505 0.03287 0.02080 0.0102 0.2051 1.0000
7.500 0.8717 0.03383 0.02179 0.0110 0.1996 1.0000
7.750 0.8920 0.03505 0.02313 0.0119 0.1947 1.0000
8.000 0.9100 0.03644 0.02480 0.0129 0.1894 1.0000
8.250 0.9302 0.03756 0.02599 0.0137 0.1845 1.0000
8.500 0.9490 0.03891 0.02745 0.0145 0.1801 1.0000
8.750 0.9623 0.04074 0.02964 0.0158 0.1752 1.0000
9.000 0.9788 0.04223 0.03131 0.0168 0.1708 1.0000
9.250 1.0005 0.04334 0.03236 0.0174 0.1670 1.0000
9.500 1.0047 0.04587 0.03537 0.0191 0.1626 1.0000
9.750 1.0114 0.04818 0.03799 0.0206 0.1586 1.0000
10.000 1.0241 0.04987 0.03983 0.0217 0.1549 1.0000
10.250 1.0417 0.05129 0.04124 0.0224 0.1514 1.0000
10.500 1.0252 0.05526 0.04573 0.0247 0.1483 1.0000
10.750 1.0069 0.05928 0.05008 0.0264 0.1457 1.0000
11.000 0.9811 0.06364 0.05467 0.0281 0.1438 1.0000
11.250 0.9302 0.07140 0.06262 0.0266 0.1430 1.0000
11.500 0.8138 0.09465 0.08590 0.0112 0.1418 1.0000
11.750 0.8220 0.09692 0.08822 0.0112 0.1391 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 22112 (naca22112-jf)