NACA M12 (nacam12-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA M12 (nacam12-il) Reynolds number: 1,000,000 Max Cl/Cd: 78.29 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nacam12-il-1000000.txt Download as CSV file: xf-nacam12-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NACA M12
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -1.0039 0.05301 0.05070 -0.0517 1.0000 0.0187
-14.000 -1.0365 0.04588 0.04331 -0.0554 1.0000 0.0187
-13.750 -1.0523 0.04204 0.03927 -0.0553 1.0000 0.0189
-13.500 -1.0626 0.03921 0.03627 -0.0537 1.0000 0.0191
-13.250 -1.0686 0.03703 0.03391 -0.0513 1.0000 0.0193
-13.000 -1.0709 0.03530 0.03202 -0.0484 1.0000 0.0195
-12.750 -1.0644 0.03390 0.03046 -0.0464 1.0000 0.0197
-12.500 -1.0527 0.03285 0.02927 -0.0449 1.0000 0.0199
-12.250 -1.0582 0.02955 0.02564 -0.0418 1.0000 0.0203
-12.000 -1.0482 0.02788 0.02387 -0.0401 1.0000 0.0206
-11.750 -1.0306 0.02715 0.02310 -0.0389 1.0000 0.0209
-11.500 -1.0113 0.02664 0.02257 -0.0380 1.0000 0.0212
-11.250 -0.9921 0.02610 0.02198 -0.0369 1.0000 0.0215
-11.000 -0.9732 0.02551 0.02133 -0.0358 1.0000 0.0219
-10.750 -0.9555 0.02475 0.02050 -0.0344 1.0000 0.0222
-10.500 -0.9388 0.02391 0.01955 -0.0328 1.0000 0.0226
-10.250 -0.9226 0.02308 0.01862 -0.0311 1.0000 0.0230
-10.000 -0.9065 0.02233 0.01776 -0.0292 1.0000 0.0233
-9.750 -0.8906 0.02174 0.01708 -0.0272 1.0000 0.0236
-9.500 -0.8748 0.02140 0.01666 -0.0250 1.0000 0.0239
-9.250 -0.8455 0.02012 0.01520 -0.0261 0.9982 0.0244
-9.000 -0.8174 0.01836 0.01334 -0.0271 0.9962 0.0250
-8.750 -0.7851 0.01757 0.01251 -0.0285 0.9944 0.0254
-8.500 -0.7528 0.01692 0.01182 -0.0298 0.9923 0.0259
-8.250 -0.7208 0.01634 0.01119 -0.0311 0.9891 0.0264
-8.000 -0.6879 0.01580 0.01060 -0.0324 0.9858 0.0270
-7.750 -0.6552 0.01518 0.00993 -0.0337 0.9825 0.0275
-7.500 -0.6270 0.01462 0.00932 -0.0339 0.9748 0.0279
-7.250 -0.5969 0.01411 0.00874 -0.0345 0.9684 0.0283
-7.000 -0.5707 0.01369 0.00827 -0.0342 0.9577 0.0286
-6.750 -0.5448 0.01334 0.00787 -0.0338 0.9468 0.0289
-6.500 -0.5215 0.01262 0.00707 -0.0329 0.9352 0.0294
-6.250 -0.4987 0.01194 0.00631 -0.0319 0.9229 0.0300
-6.000 -0.4741 0.01150 0.00583 -0.0312 0.9109 0.0306
-5.750 -0.4489 0.01116 0.00544 -0.0306 0.8996 0.0311
-5.250 -0.3974 0.01058 0.00475 -0.0297 0.8768 0.0322
-5.000 -0.3711 0.01033 0.00444 -0.0293 0.8658 0.0328
-4.500 -0.3179 0.00989 0.00389 -0.0287 0.8433 0.0341
-4.250 -0.2908 0.00973 0.00368 -0.0285 0.8324 0.0346
-3.750 -0.2375 0.00921 0.00306 -0.0279 0.8095 0.0370
-3.500 -0.2102 0.00904 0.00285 -0.0277 0.7985 0.0385
-3.000 -0.1553 0.00876 0.00249 -0.0274 0.7760 0.0419
-2.750 -0.1281 0.00857 0.00231 -0.0273 0.7652 0.0479
-2.500 -0.1018 0.00827 0.00210 -0.0270 0.7542 0.0758
-2.250 -0.0711 0.00861 0.00260 -0.0274 0.7432 0.1154
-2.000 -0.0408 0.00892 0.00285 -0.0277 0.7326 0.1215
-1.750 -0.0115 0.00909 0.00296 -0.0279 0.7214 0.1242
-1.500 0.0173 0.00915 0.00300 -0.0280 0.7107 0.1270
-1.250 0.0461 0.00926 0.00306 -0.0281 0.6999 0.1300
-1.000 0.0748 0.00936 0.00311 -0.0282 0.6885 0.1328
-0.750 0.1040 0.00959 0.00326 -0.0284 0.6771 0.1345
-0.500 0.1307 0.00923 0.00293 -0.0282 0.6659 0.1375
-0.250 0.1585 0.00918 0.00285 -0.0282 0.6538 0.1397
0.000 0.1866 0.00913 0.00279 -0.0283 0.6415 0.1413
0.250 0.2149 0.00919 0.00280 -0.0284 0.6291 0.1438
0.500 0.2437 0.00937 0.00291 -0.0285 0.6162 0.1457
0.750 0.2708 0.00922 0.00274 -0.0284 0.6031 0.1460
1.000 0.2984 0.00911 0.00263 -0.0284 0.5898 0.1463
1.250 0.3255 0.00895 0.00247 -0.0283 0.5767 0.1473
1.500 0.3529 0.00891 0.00241 -0.0282 0.5622 0.1478
1.750 0.3805 0.00893 0.00239 -0.0282 0.5462 0.1475
2.000 0.4081 0.00895 0.00238 -0.0282 0.5317 0.1473
2.250 0.4357 0.00898 0.00237 -0.0282 0.5192 0.1470
2.500 0.4635 0.00900 0.00238 -0.0282 0.5068 0.1468
2.750 0.4913 0.00902 0.00240 -0.0282 0.4948 0.1466
3.000 0.5189 0.00906 0.00242 -0.0282 0.4834 0.1464
3.500 0.5741 0.00913 0.00247 -0.0282 0.4589 0.1462
3.750 0.6015 0.00918 0.00250 -0.0282 0.4450 0.1462
4.000 0.6281 0.00928 0.00253 -0.0281 0.4224 0.1466
4.250 0.6549 0.00937 0.00257 -0.0280 0.4010 0.1469
4.500 0.6817 0.00949 0.00264 -0.0279 0.3804 0.1470
4.750 0.7085 0.00960 0.00273 -0.0278 0.3623 0.1472
5.000 0.7349 0.00976 0.00282 -0.0276 0.3418 0.1475
5.250 0.7612 0.00993 0.00293 -0.0275 0.3201 0.1479
5.500 0.7872 0.01013 0.00307 -0.0273 0.2966 0.1485
5.750 0.8127 0.01038 0.00324 -0.0270 0.2711 0.1492
6.000 0.8376 0.01070 0.00344 -0.0266 0.2410 0.1499
6.250 0.8619 0.01107 0.00368 -0.0262 0.2095 0.1507
6.500 0.8861 0.01146 0.00395 -0.0258 0.1814 0.1515
6.750 0.9099 0.01186 0.00424 -0.0253 0.1548 0.1524
7.000 0.9333 0.01229 0.00455 -0.0248 0.1273 0.1532
7.250 0.9554 0.01285 0.00494 -0.0240 0.0951 0.1539
7.500 0.9771 0.01343 0.00537 -0.0232 0.0689 0.1546
7.750 1.0001 0.01387 0.00576 -0.0226 0.0569 0.1552
8.000 1.0236 0.01425 0.00612 -0.0220 0.0503 0.1558
8.250 1.0469 0.01462 0.00650 -0.0214 0.0459 0.1566
8.500 1.0702 0.01499 0.00688 -0.0208 0.0427 0.1578
8.750 1.0940 0.01529 0.00721 -0.0203 0.0405 0.1594
9.000 1.1164 0.01569 0.00762 -0.0196 0.0379 0.1612
9.250 1.1382 0.01613 0.00810 -0.0188 0.0359 0.1634
9.500 1.1613 0.01643 0.00846 -0.0182 0.0346 0.1666
9.750 1.1833 0.01671 0.00890 -0.0176 0.0330 0.2699
10.000 1.2034 0.01716 0.00944 -0.0166 0.0312 0.3130
10.250 1.2215 0.01629 0.01017 -0.0153 0.0298 0.9935
10.500 1.2451 0.01668 0.01060 -0.0150 0.0287 1.0000
10.750 1.2648 0.01711 0.01105 -0.0140 0.0276 1.0000
11.000 1.2826 0.01764 0.01159 -0.0126 0.0264 1.0000
11.250 1.2942 0.01844 0.01242 -0.0103 0.0249 1.0000
11.500 1.3117 0.01882 0.01284 -0.0089 0.0242 1.0000
11.750 1.3274 0.01932 0.01338 -0.0072 0.0233 1.0000
12.000 1.3424 0.01989 0.01398 -0.0056 0.0224 1.0000
12.250 1.3551 0.02064 0.01475 -0.0039 0.0215 1.0000
12.500 1.3615 0.02182 0.01599 -0.0015 0.0205 1.0000
12.750 1.3767 0.02250 0.01672 -0.0003 0.0201 1.0000
13.000 1.3902 0.02332 0.01760 0.0009 0.0194 1.0000
13.250 1.4031 0.02422 0.01854 0.0021 0.0188 1.0000
13.500 1.4150 0.02523 0.01960 0.0032 0.0181 1.0000
13.750 1.4235 0.02655 0.02095 0.0044 0.0175 1.0000
14.000 1.4252 0.02849 0.02297 0.0059 0.0168 1.0000
14.250 1.4364 0.02974 0.02430 0.0066 0.0165 1.0000
14.500 1.4454 0.03121 0.02584 0.0073 0.0161 1.0000
14.750 1.4532 0.03285 0.02755 0.0079 0.0156 1.0000
15.000 1.4600 0.03465 0.02941 0.0083 0.0153 1.0000
15.250 1.4656 0.03660 0.03145 0.0087 0.0149 1.0000
15.500 1.4690 0.03885 0.03376 0.0090 0.0146 1.0000
15.750 1.4689 0.04155 0.03653 0.0091 0.0142 1.0000
16.000 1.4631 0.04495 0.04002 0.0090 0.0139 1.0000
16.250 1.4531 0.04897 0.04415 0.0087 0.0136 1.0000
16.500 1.4541 0.05183 0.04711 0.0083 0.0135 1.0000
16.750 1.4531 0.05500 0.05038 0.0077 0.0133 1.0000
17.000 1.4504 0.05849 0.05398 0.0069 0.0131 1.0000
17.250 1.4466 0.06222 0.05781 0.0059 0.0129 1.0000
17.500 1.4416 0.06616 0.06185 0.0048 0.0127 1.0000
17.750 1.4354 0.07036 0.06614 0.0036 0.0126 1.0000
18.000 1.4282 0.07480 0.07069 0.0021 0.0124 1.0000
18.250 1.4202 0.07943 0.07541 0.0005 0.0122 1.0000
18.500 1.4109 0.08429 0.08038 -0.0013 0.0121 1.0000
18.750 1.4000 0.08951 0.08569 -0.0032 0.0119 1.0000
19.000 1.3886 0.09490 0.09119 -0.0054 0.0118 1.0000
19.250 1.3762 0.10049 0.09687 -0.0077 0.0117 1.0000
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Polar data table (+)
Polar graphs
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