NACA 0012-64 a=0.8 c(li)=0.2 (naca001264a08cli02-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 0012-64 a=0.8 c(li)=0.2 (naca001264a08cli02-il) Reynolds number: 100,000 Max Cl/Cd: 49.91 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca001264a08cli02-il-100000.txt Download as CSV file: xf-naca001264a08cli02-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0012-64 a=0.8 c(li)=0.2
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4149 0.09407 0.08947 -0.0416 1.0000 0.0969
-9.500 -0.3982 0.09145 0.08686 -0.0378 1.0000 0.1049
-9.250 -0.4169 0.08766 0.08314 -0.0390 1.0000 0.1081
-9.000 -0.4402 0.08355 0.07911 -0.0405 1.0000 0.1088
-8.750 -0.4626 0.07948 0.07511 -0.0412 1.0000 0.1089
-8.500 -0.4878 0.07623 0.07189 -0.0397 1.0000 0.1089
-8.250 -0.5123 0.07368 0.06937 -0.0363 1.0000 0.1088
-8.000 -0.5386 0.07127 0.06697 -0.0323 1.0000 0.1089
-7.750 -0.5661 0.06876 0.06441 -0.0286 1.0000 0.1093
-7.500 -0.5928 0.06638 0.06190 -0.0246 1.0000 0.1097
-7.250 -0.6323 0.07043 0.06556 -0.0223 1.0000 0.1078
-7.000 -0.6351 0.06758 0.06273 -0.0194 1.0000 0.1149
-6.750 -0.6619 0.06819 0.06270 -0.0140 1.0000 0.1232
-6.500 -0.6419 0.06297 0.05796 -0.0133 1.0000 0.1335
-6.250 -0.6432 0.06010 0.05504 -0.0105 1.0000 0.1426
-6.000 -0.6449 0.05754 0.05236 -0.0075 1.0000 0.1548
-5.750 -0.6427 0.05503 0.04980 -0.0047 1.0000 0.1691
-5.500 -0.6384 0.05277 0.04750 -0.0018 1.0000 0.1871
-5.250 -0.6347 0.05072 0.04548 0.0013 1.0000 0.2136
-4.250 -0.6217 0.04419 0.03952 0.0194 1.0000 0.3958
-4.000 -0.6166 0.04280 0.03844 0.0268 1.0000 0.4535
-3.500 -0.4984 0.03178 0.02281 0.0149 1.0000 0.1107
-3.250 -0.4703 0.02938 0.02001 0.0162 1.0000 0.0964
-3.000 -0.4424 0.02767 0.01789 0.0176 1.0000 0.0845
-2.750 -0.4153 0.02589 0.01598 0.0183 1.0000 0.0781
-2.500 -0.3907 0.02547 0.01522 0.0198 1.0000 0.0731
-2.250 -0.3657 0.02438 0.01411 0.0206 1.0000 0.0716
-2.000 -0.3424 0.02368 0.01335 0.0215 1.0000 0.0728
-1.750 -0.3199 0.02264 0.01240 0.0224 1.0000 0.0741
-1.500 -0.2991 0.02206 0.01182 0.0237 1.0000 0.0746
-1.250 -0.2784 0.02163 0.01133 0.0248 1.0000 0.0762
-1.000 -0.2571 0.02136 0.01096 0.0258 1.0000 0.0807
-0.750 -0.2350 0.02117 0.01075 0.0266 1.0000 0.0892
-0.500 -0.0702 0.02017 0.01293 0.0008 1.0000 1.0000
-0.250 -0.0569 0.02042 0.01302 0.0029 1.0000 1.0000
0.000 -0.0433 0.02070 0.01315 0.0048 1.0000 1.0000
0.250 -0.0098 0.02114 0.01343 0.0027 0.9956 1.0000
0.500 0.0307 0.02161 0.01375 -0.0009 0.9884 1.0000
0.750 0.0714 0.02213 0.01416 -0.0045 0.9813 1.0000
1.000 0.1098 0.02257 0.01452 -0.0076 0.9732 1.0000
1.250 0.1457 0.02298 0.01489 -0.0101 0.9646 1.0000
1.500 0.1889 0.02347 0.01535 -0.0140 0.9571 1.0000
1.750 0.2208 0.02378 0.01567 -0.0156 0.9466 1.0000
2.000 0.2591 0.02415 0.01604 -0.0184 0.9371 1.0000
2.250 0.3062 0.02443 0.01637 -0.0227 0.9281 1.0000
2.500 0.3570 0.02436 0.01639 -0.0273 0.9139 1.0000
2.750 0.4217 0.02385 0.01599 -0.0340 0.8986 1.0000
3.000 0.4692 0.02349 0.01577 -0.0374 0.8849 1.0000
3.250 0.5170 0.02302 0.01544 -0.0408 0.8715 1.0000
3.500 0.5917 0.02146 0.01412 -0.0481 0.8562 1.0000
3.750 0.6512 0.01980 0.01270 -0.0521 0.8398 1.0000
4.000 0.6789 0.01907 0.01213 -0.0507 0.8188 1.0000
4.250 0.7193 0.01787 0.01111 -0.0512 0.7975 1.0000
4.500 0.7466 0.01690 0.01027 -0.0490 0.7604 1.0000
4.750 0.7751 0.01599 0.00928 -0.0467 0.6914 1.0000
5.000 0.7951 0.01593 0.00865 -0.0433 0.5514 1.0000
5.250 0.7990 0.01728 0.00893 -0.0382 0.3813 1.0000
5.500 0.8004 0.01895 0.00977 -0.0335 0.2673 1.0000
5.750 0.8069 0.02047 0.01076 -0.0298 0.2043 1.0000
6.000 0.8169 0.02184 0.01180 -0.0266 0.1653 1.0000
6.250 0.8306 0.02306 0.01284 -0.0241 0.1398 1.0000
6.500 0.8478 0.02426 0.01392 -0.0222 0.1246 1.0000
6.750 0.8701 0.02561 0.01527 -0.0212 0.1151 1.0000
7.000 0.8962 0.02717 0.01668 -0.0211 0.1081 1.0000
7.250 0.9228 0.02868 0.01839 -0.0207 0.1037 1.0000
7.500 0.9467 0.03008 0.01996 -0.0200 0.0989 1.0000
7.750 0.9739 0.03226 0.02207 -0.0204 0.0941 1.0000
8.000 0.9940 0.03400 0.02419 -0.0188 0.0922 1.0000
8.250 1.0125 0.03606 0.02666 -0.0170 0.0906 1.0000
8.500 1.0277 0.03831 0.02932 -0.0147 0.0889 1.0000
8.750 1.0405 0.04036 0.03169 -0.0122 0.0861 1.0000
9.000 1.0548 0.04252 0.03403 -0.0103 0.0837 1.0000
9.250 1.0657 0.04536 0.03717 -0.0078 0.0826 1.0000
9.500 1.0736 0.04939 0.04140 -0.0057 0.0808 1.0000
9.750 1.0684 0.05226 0.04473 -0.0009 0.0798 1.0000
10.000 1.0605 0.05511 0.04802 0.0041 0.0791 1.0000
10.250 1.0527 0.05878 0.05202 0.0085 0.0792 1.0000
10.500 1.0426 0.06262 0.05614 0.0127 0.0795 1.0000
10.750 1.0296 0.06647 0.06023 0.0170 0.0797 1.0000
11.000 1.0148 0.07042 0.06438 0.0210 0.0800 1.0000
11.250 1.0000 0.07467 0.06876 0.0246 0.0803 1.0000
11.500 0.7987 0.07027 0.06508 0.0402 0.0911 1.0000
11.750 0.7742 0.07595 0.07082 0.0405 0.0923 1.0000
12.000 0.7591 0.08169 0.07659 0.0404 0.0932 1.0000
12.250 0.5856 0.12249 0.11732 0.0159 0.1777 1.0000
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Polar data table (+)
Polar graphs
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