NACA M12 (nacam12-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA M12 (nacam12-il) Reynolds number: 1,000,000 Max Cl/Cd: 71.69 at α=9.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nacam12-il-1000000-n5.txt Download as CSV file: xf-nacam12-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.750 -1.3828 0.04723 0.04422 -0.0581 1.0000 0.0127
-17.500 -1.3936 0.04362 0.04048 -0.0584 1.0000 0.0128
-17.250 -1.3973 0.04098 0.03772 -0.0580 1.0000 0.0131
-17.000 -1.3962 0.03889 0.03554 -0.0572 1.0000 0.0133
-16.750 -1.3922 0.03712 0.03369 -0.0562 1.0000 0.0136
-16.500 -1.3872 0.03550 0.03197 -0.0549 1.0000 0.0139
-16.250 -1.3816 0.03400 0.03038 -0.0534 1.0000 0.0142
-16.000 -1.3756 0.03263 0.02890 -0.0516 1.0000 0.0145
-15.750 -1.3685 0.03137 0.02754 -0.0497 1.0000 0.0147
-15.500 -1.3605 0.03022 0.02628 -0.0477 1.0000 0.0149
-15.250 -1.3508 0.02918 0.02513 -0.0457 1.0000 0.0151
-15.000 -1.3372 0.02818 0.02407 -0.0443 1.0000 0.0154
-14.750 -1.3203 0.02740 0.02323 -0.0432 1.0000 0.0157
-14.500 -1.3018 0.02675 0.02255 -0.0423 1.0000 0.0160
-14.250 -1.2822 0.02618 0.02195 -0.0414 1.0000 0.0163
-14.000 -1.2621 0.02565 0.02138 -0.0406 1.0000 0.0166
-13.750 -1.2419 0.02510 0.02079 -0.0398 1.0000 0.0170
-13.500 -1.2219 0.02453 0.02016 -0.0390 1.0000 0.0173
-13.250 -1.2021 0.02390 0.01946 -0.0381 1.0000 0.0176
-13.000 -1.1823 0.02326 0.01874 -0.0372 1.0000 0.0179
-12.750 -1.1621 0.02262 0.01803 -0.0363 1.0000 0.0182
-12.500 -1.1415 0.02202 0.01735 -0.0354 1.0000 0.0185
-12.250 -1.1201 0.02149 0.01675 -0.0346 1.0000 0.0187
-12.000 -1.0981 0.02103 0.01623 -0.0338 1.0000 0.0188
-11.750 -1.0797 0.02020 0.01532 -0.0326 1.0000 0.0192
-11.500 -1.0592 0.01963 0.01470 -0.0316 1.0000 0.0195
-11.250 -1.0380 0.01915 0.01420 -0.0307 1.0000 0.0198
-11.000 -1.0167 0.01876 0.01378 -0.0297 1.0000 0.0201
-10.750 -0.9956 0.01841 0.01341 -0.0286 1.0000 0.0203
-10.500 -0.9697 0.01801 0.01297 -0.0285 0.9985 0.0207
-10.250 -0.9398 0.01752 0.01242 -0.0294 0.9959 0.0210
-10.000 -0.9094 0.01704 0.01191 -0.0303 0.9931 0.0214
-9.750 -0.8807 0.01661 0.01142 -0.0308 0.9881 0.0218
-9.500 -0.8507 0.01611 0.01086 -0.0316 0.9834 0.0221
-9.250 -0.8224 0.01564 0.01033 -0.0320 0.9763 0.0224
-9.000 -0.7931 0.01524 0.00988 -0.0325 0.9686 0.0227
-8.750 -0.7653 0.01488 0.00946 -0.0326 0.9579 0.0229
-8.500 -0.7393 0.01451 0.00903 -0.0324 0.9448 0.0231
-8.250 -0.7143 0.01417 0.00861 -0.0318 0.9304 0.0232
-8.000 -0.6910 0.01364 0.00799 -0.0310 0.9161 0.0235
-7.750 -0.6674 0.01313 0.00739 -0.0303 0.9029 0.0239
-7.250 -0.6172 0.01244 0.00657 -0.0293 0.8783 0.0247
-7.000 -0.5914 0.01215 0.00623 -0.0289 0.8669 0.0250
-6.750 -0.5656 0.01188 0.00589 -0.0285 0.8552 0.0253
-6.500 -0.5393 0.01162 0.00556 -0.0282 0.8433 0.0256
-6.250 -0.5130 0.01137 0.00526 -0.0279 0.8319 0.0259
-6.000 -0.4865 0.01114 0.00496 -0.0276 0.8201 0.0262
-5.750 -0.4598 0.01092 0.00468 -0.0274 0.8081 0.0266
-5.500 -0.4330 0.01071 0.00441 -0.0272 0.7963 0.0269
-5.250 -0.4061 0.01051 0.00416 -0.0270 0.7850 0.0273
-5.000 -0.3790 0.01034 0.00393 -0.0268 0.7732 0.0277
-4.750 -0.3517 0.01017 0.00370 -0.0267 0.7621 0.0280
-4.500 -0.3244 0.01002 0.00350 -0.0266 0.7514 0.0283
-4.250 -0.2969 0.00988 0.00333 -0.0265 0.7403 0.0286
-4.000 -0.2697 0.00969 0.00308 -0.0264 0.7302 0.0295
-3.750 -0.2424 0.00953 0.00289 -0.0262 0.7196 0.0302
-3.500 -0.2147 0.00939 0.00272 -0.0262 0.7093 0.0310
-3.250 -0.1871 0.00927 0.00256 -0.0261 0.6992 0.0319
-3.000 -0.1594 0.00915 0.00242 -0.0261 0.6885 0.0328
-2.750 -0.1316 0.00905 0.00229 -0.0261 0.6782 0.0338
-2.500 -0.1038 0.00897 0.00217 -0.0260 0.6676 0.0352
-2.250 -0.0760 0.00885 0.00205 -0.0260 0.6564 0.0393
-2.000 -0.0486 0.00870 0.00194 -0.0260 0.6453 0.0510
-1.750 -0.0212 0.00856 0.00183 -0.0259 0.6338 0.0705
-1.500 0.0074 0.00861 0.00203 -0.0261 0.6216 0.1088
-1.250 0.0362 0.00869 0.00208 -0.0262 0.6097 0.1152
-1.000 0.0645 0.00871 0.00204 -0.0263 0.5975 0.1180
-0.500 0.1217 0.00885 0.00212 -0.0265 0.5724 0.1209
-0.250 0.1502 0.00890 0.00215 -0.0266 0.5604 0.1222
0.000 0.1784 0.00894 0.00214 -0.0267 0.5487 0.1232
0.250 0.2066 0.00898 0.00215 -0.0267 0.5367 0.1245
0.500 0.2351 0.00904 0.00218 -0.0269 0.5258 0.1260
0.750 0.2633 0.00909 0.00220 -0.0269 0.5145 0.1273
1.000 0.2913 0.00910 0.00219 -0.0270 0.5031 0.1281
1.250 0.3193 0.00910 0.00218 -0.0270 0.4918 0.1285
1.500 0.3471 0.00915 0.00219 -0.0271 0.4782 0.1292
1.750 0.3747 0.00919 0.00219 -0.0271 0.4610 0.1296
2.000 0.4023 0.00922 0.00219 -0.0271 0.4471 0.1297
2.250 0.4300 0.00924 0.00219 -0.0271 0.4357 0.1298
2.500 0.4578 0.00926 0.00219 -0.0271 0.4240 0.1299
2.750 0.4855 0.00930 0.00221 -0.0272 0.4134 0.1301
3.000 0.5131 0.00935 0.00225 -0.0272 0.4014 0.1303
3.250 0.5407 0.00940 0.00228 -0.0272 0.3888 0.1306
3.500 0.5683 0.00946 0.00233 -0.0272 0.3776 0.1308
3.750 0.5953 0.00958 0.00240 -0.0271 0.3578 0.1311
4.000 0.6213 0.00981 0.00250 -0.0269 0.3252 0.1314
4.250 0.6473 0.01004 0.00262 -0.0268 0.2960 0.1317
4.500 0.6728 0.01032 0.00277 -0.0265 0.2628 0.1320
4.750 0.6984 0.01059 0.00293 -0.0263 0.2341 0.1324
5.000 0.7243 0.01083 0.00309 -0.0261 0.2115 0.1327
5.250 0.7499 0.01109 0.00328 -0.0258 0.1898 0.1331
5.500 0.7756 0.01134 0.00346 -0.0256 0.1709 0.1334
5.750 0.8012 0.01159 0.00366 -0.0253 0.1536 0.1337
6.000 0.8266 0.01186 0.00388 -0.0251 0.1363 0.1341
6.250 0.8511 0.01221 0.00413 -0.0247 0.1149 0.1344
6.500 0.8753 0.01258 0.00441 -0.0242 0.0925 0.1347
6.750 0.8991 0.01298 0.00473 -0.0238 0.0739 0.1349
7.000 0.9235 0.01330 0.00501 -0.0233 0.0620 0.1355
7.250 0.9481 0.01358 0.00528 -0.0230 0.0549 0.1361
7.500 0.9729 0.01385 0.00556 -0.0226 0.0496 0.1367
7.750 0.9972 0.01415 0.00586 -0.0222 0.0449 0.1373
8.000 1.0217 0.01442 0.00615 -0.0218 0.0417 0.1380
8.250 1.0460 0.01470 0.00644 -0.0214 0.0392 0.1388
8.500 1.0697 0.01502 0.00677 -0.0208 0.0365 0.1396
8.750 1.0936 0.01531 0.00710 -0.0204 0.0348 0.1405
9.000 1.1174 0.01559 0.00742 -0.0199 0.0335 0.1414
9.250 1.1406 0.01591 0.00776 -0.0193 0.0320 0.1423
9.500 1.1631 0.01627 0.00813 -0.0187 0.0302 0.1432
9.750 1.1851 0.01664 0.00854 -0.0179 0.0288 0.1447
10.000 1.2077 0.01695 0.00890 -0.0173 0.0280 0.1465
10.250 1.2296 0.01729 0.00929 -0.0166 0.0268 0.1480
10.500 1.2505 0.01768 0.00970 -0.0157 0.0255 0.1496
10.750 1.2703 0.01812 0.01017 -0.0147 0.0240 0.1512
11.000 1.2901 0.01853 0.01063 -0.0137 0.0231 0.1533
11.250 1.3095 0.01894 0.01109 -0.0126 0.0221 0.1567
11.750 1.3398 0.01977 0.01212 -0.0090 0.0197 0.2886
12.000 1.3547 0.01916 0.01290 -0.0076 0.0187 0.9015
12.500 1.3851 0.02029 0.01423 -0.0046 0.0165 1.0000
12.750 1.3980 0.02105 0.01501 -0.0030 0.0155 1.0000
13.000 1.4111 0.02184 0.01585 -0.0016 0.0148 1.0000
13.250 1.4237 0.02270 0.01676 -0.0002 0.0141 1.0000
13.500 1.4355 0.02366 0.01777 0.0011 0.0134 1.0000
13.750 1.4461 0.02474 0.01890 0.0024 0.0128 1.0000
14.000 1.4556 0.02596 0.02016 0.0036 0.0122 1.0000
14.250 1.4651 0.02724 0.02150 0.0047 0.0117 1.0000
14.500 1.4746 0.02857 0.02289 0.0056 0.0113 1.0000
14.750 1.4830 0.03005 0.02444 0.0064 0.0109 1.0000
15.000 1.4901 0.03168 0.02615 0.0071 0.0105 1.0000
15.250 1.4962 0.03349 0.02802 0.0077 0.0102 1.0000
15.500 1.5008 0.03549 0.03009 0.0082 0.0098 1.0000
15.750 1.5039 0.03771 0.03238 0.0085 0.0095 1.0000
16.000 1.5055 0.04017 0.03492 0.0088 0.0092 1.0000
16.250 1.5074 0.04265 0.03748 0.0088 0.0090 1.0000
16.500 1.5087 0.04526 0.04018 0.0088 0.0089 1.0000
16.750 1.5088 0.04808 0.04309 0.0085 0.0087 1.0000
17.000 1.5075 0.05116 0.04627 0.0081 0.0086 1.0000
17.250 1.5048 0.05448 0.04969 0.0075 0.0084 1.0000
17.500 1.5012 0.05803 0.05334 0.0068 0.0083 1.0000
17.750 1.4960 0.06190 0.05731 0.0058 0.0082 1.0000
18.000 1.4894 0.06601 0.06152 0.0046 0.0080 1.0000
18.250 1.4816 0.07038 0.06599 0.0033 0.0079 1.0000
18.500 1.4721 0.07511 0.07083 0.0018 0.0078 1.0000
18.750 1.4613 0.08009 0.07591 0.0000 0.0077 1.0000
19.000 1.4493 0.08533 0.08125 -0.0019 0.0076 1.0000
19.250 1.4354 0.09098 0.08702 -0.0040 0.0075 1.0000
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