NACA 66(1)-212 (naca661212-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 66(1)-212 (naca661212-il) Reynolds number: 50,000 Max Cl/Cd: 22.02 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca661212-il-50000.txt Download as CSV file: xf-naca661212-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 66(1)-212
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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4323 0.11298 0.10575 -0.0249 1.0000 0.3357
-10.000 -0.4362 0.11079 0.10364 -0.0241 1.0000 0.3543
-9.750 -0.4467 0.10913 0.10207 -0.0230 1.0000 0.3709
-9.500 -0.4186 0.10422 0.09713 -0.0220 1.0000 0.3901
-9.250 -0.4106 0.10119 0.09413 -0.0209 1.0000 0.4077
-9.000 -0.4071 0.09856 0.09155 -0.0195 1.0000 0.4256
-8.750 -0.4193 0.09710 0.09021 -0.0171 1.0000 0.4461
-8.500 -0.4123 0.09401 0.08713 -0.0157 1.0000 0.4615
-7.500 -0.5260 0.08060 0.07440 -0.0141 1.0000 0.3618
-7.250 -0.5802 0.07794 0.07195 -0.0110 1.0000 0.3462
-7.000 -0.6321 0.07527 0.06945 -0.0074 1.0000 0.3435
-6.500 -0.7203 0.05813 0.05087 -0.0150 1.0000 0.1744
-6.250 -0.7145 0.05380 0.04603 -0.0133 1.0000 0.1572
-6.000 -0.7059 0.05021 0.04178 -0.0113 1.0000 0.1458
-5.750 -0.6930 0.04678 0.03794 -0.0096 1.0000 0.1399
-5.500 -0.6770 0.04399 0.03438 -0.0076 1.0000 0.1322
-5.250 -0.6585 0.04114 0.03116 -0.0062 1.0000 0.1286
-5.000 -0.6377 0.03861 0.02816 -0.0048 1.0000 0.1257
-4.750 -0.6156 0.03652 0.02567 -0.0035 1.0000 0.1255
-4.500 -0.5934 0.03482 0.02364 -0.0023 1.0000 0.1293
-4.250 -0.5694 0.03325 0.02172 -0.0012 1.0000 0.1317
-4.000 -0.5441 0.03188 0.02001 0.0000 1.0000 0.1339
-3.750 -0.1493 0.03122 0.02198 -0.0384 1.0000 1.0000
-3.500 -0.1464 0.03094 0.02151 -0.0358 1.0000 1.0000
-3.250 -0.1427 0.03069 0.02109 -0.0333 1.0000 1.0000
-3.000 -0.1384 0.03046 0.02070 -0.0308 1.0000 1.0000
-2.750 -0.1335 0.03026 0.02034 -0.0282 1.0000 1.0000
-2.500 -0.1282 0.03008 0.02002 -0.0258 1.0000 1.0000
-2.250 -0.1225 0.02992 0.01970 -0.0233 1.0000 1.0000
-2.000 -0.1166 0.02977 0.01943 -0.0208 1.0000 1.0000
-1.750 -0.1103 0.02964 0.01918 -0.0183 1.0000 1.0000
-1.500 -0.1039 0.02952 0.01895 -0.0159 1.0000 1.0000
-1.250 -0.0974 0.02941 0.01874 -0.0134 1.0000 1.0000
-1.000 -0.0908 0.02930 0.01855 -0.0109 1.0000 1.0000
-0.750 -0.0841 0.02921 0.01838 -0.0085 1.0000 1.0000
-0.500 -0.0776 0.02912 0.01820 -0.0060 1.0000 1.0000
-0.250 -0.0711 0.02904 0.01805 -0.0034 1.0000 1.0000
0.000 -0.0647 0.02896 0.01792 -0.0009 1.0000 1.0000
0.250 -0.0584 0.02888 0.01779 0.0017 1.0000 1.0000
0.500 -0.0524 0.02880 0.01766 0.0043 1.0000 1.0000
0.750 -0.0466 0.02872 0.01756 0.0069 1.0000 1.0000
1.000 -0.0410 0.02864 0.01745 0.0095 1.0000 1.0000
1.250 -0.0357 0.02857 0.01735 0.0122 1.0000 1.0000
1.500 -0.0303 0.02849 0.01727 0.0149 1.0000 1.0000
1.750 -0.0249 0.02843 0.01720 0.0175 1.0000 1.0000
2.000 -0.0189 0.02840 0.01716 0.0199 1.0000 1.0000
2.250 -0.0120 0.02842 0.01717 0.0222 1.0000 1.0000
2.500 -0.0028 0.02854 0.01729 0.0241 1.0000 1.0000
2.750 0.0086 0.02877 0.01752 0.0254 1.0000 1.0000
3.000 0.0219 0.02912 0.01788 0.0264 1.0000 1.0000
3.250 0.0366 0.02956 0.01835 0.0270 1.0000 1.0000
3.500 0.0521 0.03009 0.01892 0.0274 1.0000 1.0000
3.750 0.0682 0.03070 0.01958 0.0276 1.0000 1.0000
4.000 0.0844 0.03139 0.02033 0.0278 1.0000 1.0000
4.250 0.1007 0.03216 0.02117 0.0278 1.0000 1.0000
4.500 0.1168 0.03301 0.02212 0.0277 1.0000 1.0000
4.750 0.1328 0.03394 0.02314 0.0276 1.0000 1.0000
5.000 0.1484 0.03495 0.02427 0.0273 1.0000 1.0000
5.250 0.2386 0.03914 0.02888 0.0131 0.9557 1.0000
5.500 0.2967 0.04120 0.03129 0.0061 0.9171 1.0000
5.750 0.3499 0.04279 0.03326 0.0009 0.8809 1.0000
6.000 0.5924 0.02722 0.01628 0.0037 0.2100 1.0000
6.250 0.6018 0.02883 0.01751 0.0067 0.1747 1.0000
6.500 0.6934 0.03183 0.02016 -0.0017 0.1385 1.0000
6.750 0.7730 0.03510 0.02354 -0.0090 0.1236 1.0000
7.000 0.8061 0.03741 0.02623 -0.0090 0.1206 1.0000
7.250 0.8282 0.03962 0.02879 -0.0077 0.1169 1.0000
7.500 0.8489 0.04206 0.03145 -0.0065 0.1138 1.0000
7.750 0.8648 0.04479 0.03463 -0.0043 0.1145 1.0000
8.000 0.8762 0.04778 0.03814 -0.0016 0.1169 1.0000
8.250 0.8856 0.05113 0.04192 0.0010 0.1199 1.0000
8.500 0.8964 0.05488 0.04597 0.0029 0.1228 1.0000
8.750 0.9092 0.05889 0.05023 0.0044 0.1253 1.0000
9.000 0.8877 0.06190 0.05405 0.0097 0.1326 1.0000
9.250 0.8896 0.06628 0.05864 0.0114 0.1367 1.0000
9.500 0.8635 0.07018 0.06302 0.0151 0.1454 1.0000
9.750 0.8546 0.07509 0.06815 0.0165 0.1556 1.0000
10.000 0.8082 0.07948 0.07270 0.0191 0.1630 1.0000
10.250 0.7926 0.08889 0.08228 0.0162 0.1966 1.0000
10.500 0.7100 0.09701 0.09029 0.0096 0.2000 1.0000
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Polar data table (+)
Polar graphs
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