NACA 0012-64 a=0.8 c(li)=0.2 (naca001264a08cli02-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| 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: 48.24 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca001264a08cli02-il-100000-n5.txt Download as CSV file: xf-naca001264a08cli02-il-100000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4745 0.09186 0.08695 -0.0427 1.0000 0.0397
-9.000 -0.4869 0.08803 0.08319 -0.0439 1.0000 0.0398
-8.750 -0.5045 0.08470 0.07991 -0.0438 1.0000 0.0397
-8.500 -0.5257 0.08227 0.07752 -0.0411 1.0000 0.0396
-8.250 -0.5461 0.07997 0.07525 -0.0376 1.0000 0.0396
-8.000 -0.5619 0.07730 0.07256 -0.0346 1.0000 0.0398
-7.750 -0.5755 0.07458 0.06980 -0.0316 1.0000 0.0400
-7.500 -0.5866 0.07180 0.06695 -0.0285 1.0000 0.0405
-7.250 -0.5952 0.06900 0.06405 -0.0254 1.0000 0.0410
-7.000 -0.6016 0.06620 0.06111 -0.0223 1.0000 0.0418
-6.750 -0.5940 0.06448 0.05854 -0.0217 0.9946 0.0449
-6.500 -0.5826 0.05992 0.05368 -0.0215 0.9902 0.0455
-6.250 -0.5660 0.05425 0.04812 -0.0225 0.9875 0.0468
-6.000 -0.5490 0.05074 0.04450 -0.0226 0.9838 0.0482
-5.750 -0.5309 0.04774 0.04128 -0.0224 0.9796 0.0508
-5.250 -0.4821 0.04138 0.03382 -0.0196 0.9716 0.0321
-5.000 -0.4599 0.03817 0.03029 -0.0192 0.9679 0.0299
-4.750 -0.4329 0.03547 0.02714 -0.0189 0.9652 0.0279
-4.500 -0.4110 0.03339 0.02462 -0.0173 0.9606 0.0267
-4.250 -0.3842 0.03152 0.02231 -0.0166 0.9569 0.0259
-4.000 -0.3539 0.02980 0.02024 -0.0168 0.9541 0.0260
-3.750 -0.3220 0.02836 0.01857 -0.0177 0.9519 0.0281
-3.500 -0.2979 0.02723 0.01722 -0.0168 0.9473 0.0295
-3.250 -0.2686 0.02602 0.01582 -0.0168 0.9437 0.0300
-3.000 -0.2364 0.02490 0.01457 -0.0174 0.9409 0.0307
-2.750 -0.2030 0.02410 0.01363 -0.0183 0.9385 0.0328
-2.500 -0.1737 0.02297 0.01254 -0.0188 0.9358 0.0356
-2.250 -0.1533 0.02217 0.01177 -0.0174 0.9302 0.0372
-2.000 -0.1257 0.02151 0.01106 -0.0175 0.9264 0.0400
-1.750 -0.0939 0.02110 0.01052 -0.0183 0.9235 0.0453
-1.500 -0.0724 0.02056 0.00988 -0.0172 0.9179 0.0492
-1.250 -0.0448 0.02025 0.00943 -0.0172 0.9131 0.0572
-1.000 -0.0125 0.01974 0.00901 -0.0181 0.9098 0.0795
-0.750 0.1043 0.01798 0.01029 -0.0357 0.9234 0.9522
-0.500 0.2144 0.01831 0.01043 -0.0533 0.9303 1.0000
-0.250 0.2498 0.01821 0.01022 -0.0553 0.9252 1.0000
0.000 0.2801 0.01815 0.01008 -0.0561 0.9187 1.0000
0.250 0.3087 0.01811 0.00998 -0.0566 0.9119 1.0000
0.500 0.3448 0.01800 0.00983 -0.0586 0.9081 1.0000
0.750 0.3640 0.01807 0.00988 -0.0572 0.8987 1.0000
1.000 0.3982 0.01797 0.00977 -0.0587 0.8942 1.0000
1.250 0.4190 0.01804 0.00985 -0.0575 0.8852 1.0000
1.500 0.4520 0.01792 0.00976 -0.0586 0.8801 1.0000
1.750 0.4735 0.01797 0.00983 -0.0575 0.8707 1.0000
2.000 0.5065 0.01766 0.00958 -0.0583 0.8617 1.0000
2.250 0.5360 0.01720 0.00915 -0.0579 0.8461 1.0000
2.500 0.5632 0.01678 0.00877 -0.0571 0.8288 1.0000
2.750 0.5890 0.01654 0.00860 -0.0562 0.8141 1.0000
3.000 0.6147 0.01629 0.00841 -0.0554 0.7974 1.0000
3.250 0.6418 0.01595 0.00811 -0.0545 0.7748 1.0000
3.500 0.6686 0.01566 0.00785 -0.0536 0.7471 1.0000
3.750 0.6934 0.01551 0.00771 -0.0525 0.7157 1.0000
4.000 0.7173 0.01547 0.00765 -0.0512 0.6782 1.0000
4.250 0.7407 0.01549 0.00761 -0.0498 0.6240 1.0000
4.500 0.7617 0.01579 0.00745 -0.0478 0.5287 1.0000
4.750 0.7724 0.01669 0.00769 -0.0444 0.4147 1.0000
5.000 0.7794 0.01785 0.00819 -0.0407 0.3071 1.0000
5.250 0.7901 0.01884 0.00877 -0.0378 0.2382 1.0000
5.500 0.8037 0.01963 0.00934 -0.0355 0.1946 1.0000
5.750 0.8183 0.02036 0.00991 -0.0333 0.1597 1.0000
6.000 0.8328 0.02107 0.01050 -0.0311 0.1329 1.0000
6.250 0.8474 0.02178 0.01114 -0.0289 0.1141 1.0000
6.500 0.8616 0.02251 0.01188 -0.0266 0.1010 1.0000
6.750 0.8750 0.02329 0.01265 -0.0242 0.0915 1.0000
7.000 0.8882 0.02408 0.01347 -0.0217 0.0842 1.0000
7.250 0.9006 0.02495 0.01436 -0.0191 0.0791 1.0000
7.500 0.9145 0.02576 0.01529 -0.0168 0.0748 1.0000
7.750 0.9281 0.02663 0.01625 -0.0145 0.0715 1.0000
8.000 0.9416 0.02763 0.01728 -0.0122 0.0690 1.0000
8.250 0.9576 0.02876 0.01846 -0.0104 0.0670 1.0000
8.500 0.9764 0.02983 0.01970 -0.0091 0.0654 1.0000
8.750 0.9967 0.03102 0.02107 -0.0080 0.0638 1.0000
9.000 1.0160 0.03221 0.02244 -0.0068 0.0617 1.0000
9.250 1.0328 0.03331 0.02373 -0.0053 0.0594 1.0000
9.500 1.0492 0.03449 0.02502 -0.0038 0.0575 1.0000
9.750 1.0684 0.03607 0.02672 -0.0028 0.0561 1.0000
10.000 1.0881 0.03815 0.02899 -0.0021 0.0548 1.0000
10.250 1.0992 0.03973 0.03097 0.0004 0.0532 1.0000
10.500 1.1057 0.04117 0.03275 0.0034 0.0507 1.0000
10.750 1.1099 0.04240 0.03423 0.0067 0.0481 1.0000
11.000 1.1126 0.04326 0.03517 0.0100 0.0458 1.0000
11.250 1.1171 0.04483 0.03670 0.0126 0.0435 1.0000
11.500 1.1095 0.04644 0.03873 0.0174 0.0418 1.0000
11.750 1.1022 0.04835 0.04099 0.0215 0.0398 1.0000
12.000 1.0952 0.05030 0.04327 0.0251 0.0379 1.0000
12.250 1.0902 0.05196 0.04509 0.0280 0.0360 1.0000
12.500 1.0891 0.05332 0.04648 0.0302 0.0343 1.0000
12.750 1.0812 0.05605 0.04929 0.0324 0.0330 1.0000
13.000 1.0629 0.05965 0.05328 0.0348 0.0322 1.0000
13.250 1.0422 0.06388 0.05785 0.0363 0.0316 1.0000
13.500 1.0196 0.06872 0.06297 0.0368 0.0312 1.0000
13.750 0.9952 0.07430 0.06880 0.0361 0.0311 1.0000
14.000 0.9692 0.08077 0.07547 0.0340 0.0313 1.0000
14.250 0.9422 0.08832 0.08319 0.0304 0.0316 1.0000
14.500 0.9148 0.09707 0.09207 0.0255 0.0322 1.0000
14.750 0.8872 0.10709 0.10211 0.0196 0.0328 1.0000
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Polar data table (+)
Polar graphs
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