NACA 0012-64 (naca001264-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 0012-64 (naca001264-il) Reynolds number: 500,000 Max Cl/Cd: 50.85 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca001264-il-500000.txt Download as CSV file: xf-naca001264-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0012-64
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.250 -0.6742 0.17732 0.17473 0.0125 1.0000 0.0275
-16.000 -0.9991 0.08308 0.07993 -0.0373 1.0000 0.0221
-15.750 -1.0281 0.07406 0.07069 -0.0434 1.0000 0.0221
-15.500 -1.0555 0.06647 0.06288 -0.0477 1.0000 0.0221
-15.250 -1.0806 0.06005 0.05625 -0.0503 1.0000 0.0222
-15.000 -1.0994 0.05497 0.05099 -0.0515 1.0000 0.0223
-14.750 -1.1090 0.05133 0.04724 -0.0518 1.0000 0.0225
-14.500 -1.1130 0.04860 0.04442 -0.0516 1.0000 0.0228
-14.250 -1.1162 0.04617 0.04189 -0.0510 1.0000 0.0230
-14.000 -1.1178 0.04405 0.03967 -0.0500 1.0000 0.0233
-13.750 -1.1192 0.04207 0.03757 -0.0486 1.0000 0.0236
-13.500 -1.1182 0.04035 0.03575 -0.0470 1.0000 0.0240
-13.250 -1.1181 0.03863 0.03389 -0.0450 1.0000 0.0244
-13.000 -1.1180 0.03696 0.03206 -0.0427 1.0000 0.0249
-12.750 -1.1174 0.03547 0.03039 -0.0400 1.0000 0.0254
-12.500 -1.1162 0.03420 0.02893 -0.0369 1.0000 0.0259
-12.250 -1.1150 0.03333 0.02788 -0.0333 1.0000 0.0263
-12.000 -1.1150 0.03132 0.02564 -0.0298 1.0000 0.0268
-11.750 -1.1047 0.02962 0.02389 -0.0278 1.0000 0.0275
-11.500 -1.0933 0.02874 0.02298 -0.0257 1.0000 0.0280
-11.250 -1.0824 0.02797 0.02214 -0.0232 1.0000 0.0286
-11.000 -1.0715 0.02719 0.02127 -0.0206 1.0000 0.0292
-10.750 -1.0600 0.02645 0.02045 -0.0181 1.0000 0.0299
-10.500 -1.0485 0.02576 0.01964 -0.0154 1.0000 0.0306
-10.250 -1.0371 0.02516 0.01893 -0.0127 1.0000 0.0313
-10.000 -1.0256 0.02472 0.01836 -0.0098 1.0000 0.0317
-9.750 -1.0121 0.02286 0.01639 -0.0077 1.0000 0.0326
-9.500 -0.9989 0.02196 0.01547 -0.0054 1.0000 0.0333
-9.250 -0.9857 0.02140 0.01489 -0.0029 1.0000 0.0341
-9.000 -0.9722 0.02090 0.01436 -0.0004 1.0000 0.0349
-8.750 -0.9582 0.02039 0.01379 0.0020 1.0000 0.0357
-8.500 -0.9438 0.01984 0.01318 0.0043 1.0000 0.0365
-8.250 -0.9289 0.01931 0.01258 0.0066 1.0000 0.0372
-8.000 -0.9135 0.01887 0.01207 0.0088 1.0000 0.0378
-7.750 -0.8988 0.01819 0.01133 0.0111 1.0000 0.0385
-7.500 -0.8739 0.01719 0.01032 0.0110 0.9988 0.0400
-7.250 -0.8430 0.01660 0.00972 0.0099 0.9969 0.0411
-7.000 -0.8110 0.01609 0.00918 0.0086 0.9951 0.0424
-6.750 -0.7783 0.01564 0.00869 0.0072 0.9935 0.0439
-6.500 -0.7480 0.01525 0.00825 0.0064 0.9909 0.0452
-6.250 -0.7188 0.01454 0.00752 0.0057 0.9882 0.0470
-6.000 -0.6868 0.01404 0.00704 0.0044 0.9860 0.0494
-5.750 -0.6530 0.01368 0.00666 0.0029 0.9843 0.0519
-5.500 -0.6184 0.01329 0.00626 0.0011 0.9829 0.0555
-5.250 -0.5914 0.01288 0.00589 0.0011 0.9787 0.0610
-5.000 -0.5603 0.01245 0.00552 0.0001 0.9757 0.0708
-4.750 -0.5272 0.01202 0.00517 -0.0013 0.9735 0.0893
-4.500 -0.4932 0.01157 0.00486 -0.0030 0.9718 0.1158
-4.250 -0.4586 0.01107 0.00459 -0.0049 0.9705 0.1569
-4.000 -0.4335 0.01063 0.00435 -0.0046 0.9655 0.2023
-3.750 -0.4036 0.01008 0.00408 -0.0054 0.9621 0.2647
-3.500 -0.3741 0.00931 0.00377 -0.0064 0.9595 0.3691
-3.250 -0.3462 0.00851 0.00349 -0.0068 0.9571 0.4922
-3.000 -0.3249 0.00799 0.00334 -0.0056 0.9516 0.5807
-2.750 -0.3003 0.00761 0.00324 -0.0048 0.9466 0.6505
-2.500 -0.2716 0.00735 0.00315 -0.0048 0.9432 0.7028
-2.250 -0.2413 0.00716 0.00310 -0.0051 0.9406 0.7413
-2.000 -0.2188 0.00709 0.00308 -0.0037 0.9332 0.7670
-1.750 -0.1898 0.00698 0.00301 -0.0037 0.9289 0.7844
-1.500 -0.1595 0.00689 0.00294 -0.0039 0.9254 0.8003
-1.250 -0.1352 0.00686 0.00296 -0.0029 0.9182 0.8169
-1.000 -0.1072 0.00680 0.00293 -0.0026 0.9130 0.8331
-0.750 -0.0794 0.00678 0.00292 -0.0022 0.9081 0.8477
-0.500 -0.0544 0.00678 0.00295 -0.0013 0.9005 0.8618
-0.250 -0.0258 0.00679 0.00299 -0.0009 0.8948 0.8742
0.000 0.0000 0.00682 0.00304 0.0000 0.8850 0.8850
0.250 0.0259 0.00679 0.00299 0.0009 0.8742 0.8948
0.750 0.0794 0.00678 0.00292 0.0022 0.8477 0.9080
1.000 0.1072 0.00680 0.00293 0.0026 0.8331 0.9130
1.250 0.1352 0.00686 0.00296 0.0029 0.8169 0.9182
1.500 0.1595 0.00689 0.00294 0.0039 0.8004 0.9254
1.750 0.1898 0.00698 0.00301 0.0037 0.7844 0.9289
2.000 0.2188 0.00708 0.00308 0.0037 0.7670 0.9332
2.250 0.2413 0.00716 0.00310 0.0051 0.7415 0.9406
2.500 0.2716 0.00735 0.00315 0.0048 0.7027 0.9432
2.750 0.3002 0.00761 0.00324 0.0048 0.6503 0.9466
3.000 0.3249 0.00799 0.00334 0.0056 0.5809 0.9516
3.250 0.3462 0.00851 0.00349 0.0069 0.4920 0.9571
3.500 0.3741 0.00930 0.00377 0.0064 0.3694 0.9595
3.750 0.4037 0.01008 0.00408 0.0054 0.2648 0.9621
4.000 0.4334 0.01063 0.00435 0.0046 0.2022 0.9655
4.250 0.4586 0.01107 0.00459 0.0048 0.1569 0.9705
4.500 0.4933 0.01157 0.00486 0.0030 0.1158 0.9718
4.750 0.5272 0.01201 0.00517 0.0013 0.0893 0.9735
5.000 0.5603 0.01245 0.00551 -0.0001 0.0708 0.9757
5.250 0.5914 0.01288 0.00589 -0.0011 0.0610 0.9787
5.500 0.6184 0.01329 0.00626 -0.0012 0.0554 0.9829
5.750 0.6530 0.01368 0.00666 -0.0029 0.0519 0.9843
6.000 0.6868 0.01404 0.00704 -0.0044 0.0493 0.9860
6.250 0.7188 0.01454 0.00752 -0.0057 0.0470 0.9882
6.500 0.7481 0.01524 0.00825 -0.0064 0.0452 0.9909
6.750 0.7783 0.01564 0.00869 -0.0072 0.0439 0.9936
7.000 0.8111 0.01609 0.00918 -0.0087 0.0424 0.9951
7.250 0.8431 0.01660 0.00972 -0.0099 0.0411 0.9969
7.500 0.8741 0.01719 0.01031 -0.0111 0.0399 0.9988
7.750 0.8987 0.01818 0.01132 -0.0110 0.0385 1.0000
8.000 0.9133 0.01887 0.01207 -0.0088 0.0378 1.0000
8.250 0.9288 0.01931 0.01258 -0.0066 0.0372 1.0000
8.500 0.9436 0.01984 0.01317 -0.0043 0.0365 1.0000
8.750 0.9581 0.02038 0.01378 -0.0019 0.0358 1.0000
9.000 0.9721 0.02090 0.01435 0.0005 0.0349 1.0000
9.250 0.9856 0.02139 0.01488 0.0029 0.0341 1.0000
9.500 0.9987 0.02195 0.01546 0.0054 0.0333 1.0000
9.750 1.0120 0.02286 0.01638 0.0078 0.0326 1.0000
10.000 1.0255 0.02472 0.01835 0.0098 0.0317 1.0000
10.250 1.0370 0.02516 0.01892 0.0127 0.0313 1.0000
10.500 1.0485 0.02576 0.01965 0.0154 0.0306 1.0000
10.750 1.0600 0.02645 0.02044 0.0181 0.0299 1.0000
11.000 1.0715 0.02720 0.02128 0.0206 0.0292 1.0000
11.250 1.0825 0.02796 0.02213 0.0232 0.0286 1.0000
11.500 1.0935 0.02875 0.02298 0.0256 0.0280 1.0000
11.750 1.1050 0.02963 0.02390 0.0278 0.0275 1.0000
12.000 1.1154 0.03133 0.02565 0.0297 0.0268 1.0000
12.250 1.1154 0.03333 0.02789 0.0332 0.0263 1.0000
12.500 1.1168 0.03422 0.02896 0.0368 0.0259 1.0000
12.750 1.1180 0.03548 0.03040 0.0399 0.0254 1.0000
13.000 1.1187 0.03700 0.03210 0.0425 0.0249 1.0000
13.250 1.1189 0.03864 0.03391 0.0449 0.0244 1.0000
13.500 1.1192 0.04036 0.03576 0.0469 0.0240 1.0000
13.750 1.1204 0.04205 0.03755 0.0484 0.0236 1.0000
14.000 1.1190 0.04405 0.03967 0.0498 0.0233 1.0000
14.250 1.1177 0.04613 0.04185 0.0507 0.0230 1.0000
14.500 1.1151 0.04852 0.04433 0.0513 0.0228 1.0000
14.750 1.1104 0.05134 0.04725 0.0516 0.0225 1.0000
15.000 1.1008 0.05498 0.05101 0.0513 0.0223 1.0000
15.250 1.0814 0.06015 0.05636 0.0500 0.0221 1.0000
15.500 1.0554 0.06673 0.06315 0.0473 0.0221 1.0000
15.750 1.0285 0.07430 0.07093 0.0429 0.0221 1.0000
16.000 0.9995 0.08335 0.08021 0.0368 0.0221 1.0000
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