NACA 64(1)-212 MOD A (n64212ma-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 64(1)-212 MOD A (n64212ma-il) Reynolds number: 100,000 Max Cl/Cd: 42.53 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n64212ma-il-100000.txt Download as CSV file: xf-n64212ma-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64(1)-212 MOD A
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3718 0.10186 0.09670 -0.0284 1.0000 0.0936
-9.250 -0.3740 0.09860 0.09351 -0.0307 1.0000 0.0971
-9.000 -0.4026 0.09474 0.08976 -0.0383 1.0000 0.0990
-8.750 -0.3886 0.09077 0.08584 -0.0365 1.0000 0.1008
-8.500 -0.3720 0.08820 0.08330 -0.0344 1.0000 0.1039
-8.250 -0.3757 0.08495 0.08013 -0.0360 1.0000 0.1073
-8.000 -0.3998 0.08116 0.07647 -0.0396 1.0000 0.1093
-7.750 -0.4347 0.07896 0.07433 -0.0398 1.0000 0.1102
-7.500 -0.4712 0.07813 0.07348 -0.0368 1.0000 0.1107
-7.250 -0.5073 0.07796 0.07318 -0.0331 1.0000 0.1111
-6.750 -0.4955 0.07104 0.06662 -0.0277 1.0000 0.1149
-6.500 -0.5027 0.06924 0.06484 -0.0251 1.0000 0.1174
-6.250 -0.5132 0.06740 0.06293 -0.0235 1.0000 0.1211
-6.000 -0.5006 0.06316 0.05849 -0.0274 0.9946 0.1279
-5.750 -0.4754 0.06038 0.05529 -0.0329 0.9857 0.1413
-5.500 -0.4459 0.05631 0.05149 -0.0345 0.9813 0.1495
-5.250 -0.4234 0.05302 0.04807 -0.0373 0.9735 0.1640
-5.000 -0.3942 0.04984 0.04479 -0.0407 0.9674 0.1828
-4.750 -0.3719 0.04714 0.04203 -0.0423 0.9588 0.2033
-4.500 -0.3418 0.04421 0.03902 -0.0455 0.9522 0.2426
-4.250 -0.3199 0.04169 0.03665 -0.0454 0.9428 0.2715
-4.000 -0.2866 0.03886 0.03390 -0.0475 0.9361 0.3147
-3.750 -0.2620 0.03771 0.03246 -0.0485 0.9257 0.3468
-3.500 -0.2260 0.03432 0.02943 -0.0493 0.9194 0.3799
-3.250 -0.1233 0.01736 0.01117 -0.0611 0.8995 0.2464
-3.000 -0.0873 0.03031 0.02221 -0.0595 0.9045 0.1222
-2.750 -0.0375 0.02823 0.01973 -0.0620 0.8991 0.1086
-2.500 -0.0058 0.02697 0.01836 -0.0622 0.8907 0.1069
-2.250 0.0272 0.02584 0.01710 -0.0625 0.8831 0.1049
-2.000 0.0673 0.02470 0.01579 -0.0636 0.8782 0.1020
-1.750 0.0944 0.02404 0.01508 -0.0629 0.8697 0.1014
-1.500 0.1263 0.02313 0.01421 -0.0628 0.8607 0.1020
-1.250 0.1653 0.02204 0.01323 -0.0635 0.8536 0.1064
-1.000 0.1859 0.02158 0.01283 -0.0615 0.8403 0.1096
-0.750 0.2199 0.02052 0.01183 -0.0609 0.8320 0.1131
-0.500 0.2386 0.02013 0.01149 -0.0589 0.8183 0.1178
-0.250 0.2700 0.01933 0.01065 -0.0583 0.8100 0.1290
0.000 0.2916 0.01893 0.01031 -0.0568 0.7965 0.1472
0.250 0.3069 0.01674 0.01012 -0.0533 0.7883 0.6856
0.500 0.3074 0.01708 0.01087 -0.0449 0.7770 0.8208
0.750 0.3148 0.01715 0.01098 -0.0372 0.7679 0.8806
1.000 0.3362 0.01710 0.01090 -0.0328 0.7561 0.9266
1.250 0.4713 0.01630 0.00986 -0.0483 0.7333 0.9778
1.500 0.5134 0.01577 0.00921 -0.0506 0.7144 0.9860
1.750 0.5528 0.01534 0.00868 -0.0526 0.6944 0.9946
2.000 0.5826 0.01500 0.00828 -0.0531 0.6706 1.0000
2.250 0.5963 0.01480 0.00804 -0.0506 0.6453 1.0000
2.500 0.6089 0.01460 0.00772 -0.0477 0.6113 1.0000
2.750 0.6175 0.01452 0.00744 -0.0441 0.5505 1.0000
3.000 0.6141 0.01514 0.00711 -0.0385 0.3841 1.0000
3.250 0.6091 0.01630 0.00756 -0.0336 0.3014 1.0000
3.500 0.6133 0.01716 0.00803 -0.0301 0.2706 1.0000
3.750 0.6281 0.01790 0.00852 -0.0282 0.2523 1.0000
4.000 0.6489 0.01856 0.00899 -0.0273 0.2404 1.0000
4.250 0.6721 0.01924 0.00946 -0.0268 0.2321 1.0000
4.500 0.6977 0.01990 0.00998 -0.0265 0.2261 1.0000
4.750 0.7242 0.02050 0.01052 -0.0264 0.2211 1.0000
5.000 0.7512 0.02115 0.01105 -0.0264 0.2171 1.0000
5.250 0.7790 0.02192 0.01167 -0.0266 0.2139 1.0000
5.500 0.8074 0.02275 0.01241 -0.0268 0.2116 1.0000
5.750 0.8352 0.02344 0.01315 -0.0269 0.2098 1.0000
6.000 0.8628 0.02416 0.01391 -0.0270 0.2077 1.0000
6.250 0.8897 0.02488 0.01467 -0.0270 0.2051 1.0000
6.500 0.9161 0.02559 0.01539 -0.0270 0.2019 1.0000
6.750 0.9427 0.02636 0.01607 -0.0271 0.1985 1.0000
7.000 0.9695 0.02734 0.01700 -0.0272 0.1954 1.0000
7.250 0.9937 0.02803 0.01786 -0.0269 0.1927 1.0000
7.500 1.0183 0.02880 0.01876 -0.0266 0.1899 1.0000
7.750 1.0428 0.02958 0.01963 -0.0264 0.1870 1.0000
8.000 1.0677 0.03037 0.02042 -0.0262 0.1841 1.0000
8.250 1.0945 0.03148 0.02144 -0.0265 0.1811 1.0000
8.500 1.1150 0.03228 0.02252 -0.0257 0.1784 1.0000
8.750 1.1361 0.03305 0.02347 -0.0250 0.1746 1.0000
9.000 1.1590 0.03376 0.02423 -0.0246 0.1708 1.0000
9.250 1.1846 0.03468 0.02504 -0.0247 0.1671 1.0000
9.500 1.1999 0.03554 0.02628 -0.0234 0.1629 1.0000
9.750 1.2211 0.03592 0.02666 -0.0227 0.1574 1.0000
10.000 1.2382 0.03670 0.02758 -0.0217 0.1521 1.0000
10.250 1.2574 0.03697 0.02787 -0.0208 0.1459 1.0000
10.500 1.2695 0.03772 0.02881 -0.0191 0.1392 1.0000
10.750 1.2841 0.03826 0.02938 -0.0177 0.1323 1.0000
11.000 1.2982 0.03890 0.03001 -0.0163 0.1251 1.0000
11.250 1.3122 0.03991 0.03099 -0.0150 0.1181 1.0000
11.500 1.3297 0.04128 0.03227 -0.0142 0.1119 1.0000
11.750 1.3379 0.04333 0.03451 -0.0125 0.1066 1.0000
12.000 1.3423 0.04572 0.03714 -0.0106 0.1027 1.0000
12.250 1.3618 0.04756 0.03893 -0.0103 0.0990 1.0000
12.500 1.3485 0.05023 0.04202 -0.0067 0.0968 1.0000
12.750 1.3768 0.05196 0.04360 -0.0074 0.0938 1.0000
13.000 1.3508 0.05509 0.04719 -0.0033 0.0929 1.0000
13.250 1.3274 0.05868 0.05115 -0.0006 0.0921 1.0000
13.500 1.3031 0.06279 0.05559 0.0010 0.0914 1.0000
13.750 1.2753 0.06765 0.06076 0.0016 0.0910 1.0000
14.000 1.2366 0.07414 0.06757 0.0007 0.0910 1.0000
14.250 1.1727 0.08470 0.07852 -0.0036 0.0919 1.0000
14.500 1.0938 0.10065 0.09476 -0.0128 0.0935 1.0000
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Polar data table (+)
Polar graphs
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