NACA 66(1)-212 (naca661212-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 66(1)-212 (naca661212-il) Reynolds number: 100,000 Max Cl/Cd: 37.64 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca661212-il-100000.txt Download as CSV file: xf-naca661212-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4800 0.09883 0.09386 -0.0451 1.0000 0.1295
-10.000 -0.5165 0.09384 0.08903 -0.0515 1.0000 0.1332
-9.750 -0.5039 0.09046 0.08568 -0.0487 1.0000 0.1374
-9.500 -0.5033 0.08778 0.08305 -0.0476 1.0000 0.1435
-9.250 -0.5382 0.08402 0.07943 -0.0488 1.0000 0.1458
-9.000 -0.5718 0.08212 0.07762 -0.0456 1.0000 0.1459
-8.750 -0.6070 0.08088 0.07647 -0.0406 1.0000 0.1456
-8.500 -0.6409 0.07962 0.07526 -0.0353 1.0000 0.1455
-8.250 -0.6759 0.07800 0.07361 -0.0309 1.0000 0.1465
-8.000 -0.7180 0.07692 0.07236 -0.0263 1.0000 0.1480
-6.750 -0.7349 0.06236 0.05773 -0.0131 1.0000 0.1866
-6.500 -0.7369 0.05981 0.05513 -0.0104 1.0000 0.2009
-5.250 -0.6719 0.03689 0.02883 -0.0022 1.0000 0.0856
-5.000 -0.6489 0.03487 0.02593 0.0002 1.0000 0.0765
-4.750 -0.6278 0.03236 0.02317 0.0013 1.0000 0.0753
-4.500 -0.6066 0.03099 0.02144 0.0026 1.0000 0.0764
-4.250 -0.5847 0.02959 0.01976 0.0038 1.0000 0.0769
-4.000 -0.5620 0.02814 0.01811 0.0049 1.0000 0.0770
-3.750 -0.5392 0.02656 0.01644 0.0058 1.0000 0.0779
-3.500 -0.5175 0.02517 0.01513 0.0068 1.0000 0.0811
-3.250 -0.4968 0.02438 0.01434 0.0078 1.0000 0.0866
-3.000 -0.4759 0.02368 0.01359 0.0090 1.0000 0.0904
-2.750 -0.4569 0.02271 0.01274 0.0103 1.0000 0.0953
-2.500 -0.4372 0.02218 0.01216 0.0115 1.0000 0.1050
-2.250 -0.4176 0.02151 0.01157 0.0126 1.0000 0.1208
-2.000 -0.4033 0.01896 0.01089 0.0138 1.0000 0.4331
-1.750 -0.4203 0.01935 0.01289 0.0272 1.0000 0.8245
-1.500 -0.1148 0.02659 0.01930 -0.0137 1.0000 0.9982
-1.250 -0.0976 0.02656 0.01917 -0.0134 1.0000 1.0000
-1.000 -0.0769 0.02649 0.01901 -0.0136 0.9975 1.0000
-0.750 -0.0505 0.02655 0.01898 -0.0150 0.9939 1.0000
-0.500 -0.0290 0.02652 0.01888 -0.0154 0.9901 1.0000
-0.250 -0.0050 0.02662 0.01892 -0.0162 0.9862 1.0000
0.000 0.0207 0.02680 0.01906 -0.0173 0.9822 1.0000
0.250 0.0392 0.02684 0.01907 -0.0170 0.9775 1.0000
0.500 0.0655 0.02708 0.01927 -0.0182 0.9727 1.0000
0.750 0.0867 0.02725 0.01944 -0.0184 0.9674 1.0000
1.000 0.1081 0.02742 0.01961 -0.0186 0.9614 1.0000
1.250 0.1374 0.02781 0.02001 -0.0202 0.9558 1.0000
1.500 0.1520 0.02790 0.02012 -0.0191 0.9485 1.0000
1.750 0.1865 0.02839 0.02064 -0.0216 0.9423 1.0000
2.000 0.1981 0.02847 0.02075 -0.0198 0.9335 1.0000
2.250 0.2257 0.02885 0.02119 -0.0209 0.9258 1.0000
2.500 0.2489 0.02911 0.02150 -0.0212 0.9167 1.0000
2.750 0.2672 0.02934 0.02180 -0.0204 0.9064 1.0000
3.000 0.3025 0.02974 0.02231 -0.0226 0.8973 1.0000
3.250 0.3292 0.02995 0.02262 -0.0232 0.8862 1.0000
3.500 0.3491 0.03010 0.02286 -0.0224 0.8735 1.0000
3.750 0.3731 0.03025 0.02315 -0.0222 0.8609 1.0000
4.000 0.4032 0.03034 0.02339 -0.0228 0.8481 1.0000
4.250 0.6914 0.01837 0.00967 -0.0452 0.2615 1.0000
4.500 0.6814 0.02039 0.01062 -0.0391 0.1272 1.0000
4.750 0.6846 0.02132 0.01141 -0.0349 0.1095 1.0000
5.000 0.6884 0.02207 0.01215 -0.0309 0.0987 1.0000
5.250 0.6925 0.02278 0.01288 -0.0268 0.0916 1.0000
5.500 0.6975 0.02354 0.01361 -0.0230 0.0867 1.0000
5.750 0.7110 0.02481 0.01475 -0.0206 0.0824 1.0000
6.000 0.7284 0.02565 0.01570 -0.0187 0.0779 1.0000
6.250 0.7498 0.02678 0.01681 -0.0177 0.0732 1.0000
6.500 0.7992 0.02993 0.01984 -0.0214 0.0700 1.0000
6.750 0.8222 0.03160 0.02173 -0.0203 0.0694 1.0000
7.000 0.8384 0.03307 0.02350 -0.0180 0.0687 1.0000
7.250 0.8490 0.03437 0.02511 -0.0149 0.0671 1.0000
7.500 0.8613 0.03624 0.02727 -0.0121 0.0669 1.0000
7.750 0.8736 0.03873 0.03003 -0.0094 0.0679 1.0000
8.000 0.8884 0.04239 0.03388 -0.0076 0.0695 1.0000
8.250 0.8916 0.04410 0.03645 -0.0021 0.0766 1.0000
8.500 0.8994 0.05085 0.04421 0.0023 0.1065 1.0000
10.750 0.7250 0.09928 0.09462 0.0092 0.1807 1.0000
11.000 0.6943 0.10563 0.10087 0.0035 0.1710 1.0000
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Polar data table (+)
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