NACA M12 (nacam12-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA M12 (nacam12-il) Reynolds number: 500,000 Max Cl/Cd: 62.65 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nacam12-il-500000-n5.txt Download as CSV file: xf-nacam12-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -1.0198 0.05439 0.05125 -0.0510 1.0000 0.0190
-14.250 -1.0441 0.04803 0.04466 -0.0547 1.0000 0.0190
-14.000 -1.0534 0.04462 0.04112 -0.0552 1.0000 0.0192
-13.750 -1.0568 0.04225 0.03864 -0.0546 1.0000 0.0193
-13.500 -1.0548 0.04059 0.03691 -0.0535 1.0000 0.0195
-13.250 -1.0519 0.03914 0.03537 -0.0519 1.0000 0.0197
-13.000 -1.0485 0.03781 0.03395 -0.0498 1.0000 0.0199
-12.750 -1.0436 0.03657 0.03262 -0.0476 1.0000 0.0201
-12.500 -1.0355 0.03520 0.03111 -0.0459 1.0000 0.0203
-12.250 -1.0254 0.03388 0.02966 -0.0444 1.0000 0.0206
-12.000 -1.0139 0.03257 0.02820 -0.0429 1.0000 0.0210
-11.750 -1.0014 0.03126 0.02673 -0.0414 1.0000 0.0215
-11.500 -0.9882 0.02994 0.02523 -0.0399 1.0000 0.0219
-11.250 -0.9738 0.02868 0.02379 -0.0384 1.0000 0.0224
-11.000 -0.9584 0.02751 0.02243 -0.0370 1.0000 0.0227
-10.750 -0.9417 0.02652 0.02127 -0.0356 1.0000 0.0230
-10.500 -0.9237 0.02576 0.02036 -0.0343 1.0000 0.0232
-10.250 -0.9107 0.02423 0.01870 -0.0325 1.0000 0.0237
-10.000 -0.8940 0.02338 0.01780 -0.0309 1.0000 0.0241
-9.750 -0.8769 0.02266 0.01703 -0.0293 1.0000 0.0244
-9.500 -0.8599 0.02199 0.01628 -0.0276 1.0000 0.0247
-9.250 -0.8304 0.02121 0.01542 -0.0285 0.9968 0.0251
-9.000 -0.7995 0.02049 0.01462 -0.0297 0.9938 0.0256
-8.750 -0.7700 0.01976 0.01380 -0.0305 0.9894 0.0262
-8.500 -0.7400 0.01899 0.01292 -0.0315 0.9847 0.0266
-8.250 -0.7105 0.01826 0.01209 -0.0322 0.9790 0.0270
-8.000 -0.6804 0.01757 0.01131 -0.0330 0.9727 0.0274
-7.750 -0.6512 0.01696 0.01062 -0.0335 0.9650 0.0278
-7.500 -0.6209 0.01645 0.01002 -0.0342 0.9568 0.0282
-7.250 -0.5931 0.01600 0.00950 -0.0343 0.9460 0.0285
-7.000 -0.5674 0.01523 0.00865 -0.0341 0.9347 0.0289
-6.750 -0.5422 0.01461 0.00797 -0.0337 0.9232 0.0294
-6.500 -0.5174 0.01413 0.00743 -0.0331 0.9108 0.0298
-6.250 -0.4924 0.01372 0.00697 -0.0325 0.8992 0.0303
-6.000 -0.4673 0.01336 0.00654 -0.0320 0.8876 0.0307
-5.750 -0.4420 0.01302 0.00614 -0.0315 0.8757 0.0312
-5.500 -0.4164 0.01271 0.00577 -0.0310 0.8642 0.0317
-5.250 -0.3906 0.01243 0.00542 -0.0305 0.8530 0.0323
-5.000 -0.3646 0.01217 0.00510 -0.0301 0.8411 0.0330
-4.750 -0.3382 0.01193 0.00480 -0.0298 0.8297 0.0337
-4.500 -0.3118 0.01172 0.00452 -0.0295 0.8183 0.0343
-4.250 -0.2852 0.01152 0.00425 -0.0292 0.8068 0.0348
-4.000 -0.2586 0.01127 0.00396 -0.0289 0.7951 0.0358
-3.750 -0.2318 0.01109 0.00374 -0.0286 0.7841 0.0371
-3.500 -0.2048 0.01094 0.00355 -0.0284 0.7727 0.0385
-3.250 -0.1775 0.01081 0.00338 -0.0282 0.7615 0.0403
-3.000 -0.1503 0.01069 0.00322 -0.0280 0.7507 0.0430
-2.750 -0.1233 0.01052 0.00306 -0.0279 0.7395 0.0495
-2.500 -0.0967 0.01029 0.00289 -0.0277 0.7287 0.0673
-2.250 -0.0655 0.01080 0.00357 -0.0281 0.7178 0.1000
-2.000 -0.0388 0.01060 0.00329 -0.0279 0.7067 0.1148
-1.750 -0.0106 0.01064 0.00325 -0.0279 0.6957 0.1194
-1.500 0.0182 0.01080 0.00335 -0.0280 0.6847 0.1231
-1.250 0.0465 0.01086 0.00333 -0.0280 0.6730 0.1261
-1.000 0.0744 0.01085 0.00328 -0.0280 0.6617 0.1276
-0.750 0.1023 0.01088 0.00327 -0.0279 0.6501 0.1297
-0.500 0.1303 0.01091 0.00325 -0.0279 0.6378 0.1321
-0.250 0.1586 0.01100 0.00328 -0.0280 0.6257 0.1347
0.000 0.1858 0.01090 0.00317 -0.0279 0.6135 0.1369
0.250 0.2131 0.01086 0.00310 -0.0278 0.6011 0.1381
0.500 0.2405 0.01081 0.00303 -0.0277 0.5883 0.1385
0.750 0.2680 0.01078 0.00298 -0.0277 0.5762 0.1395
1.000 0.2954 0.01076 0.00294 -0.0276 0.5639 0.1404
1.500 0.3500 0.01074 0.00287 -0.0274 0.5394 0.1410
1.750 0.3773 0.01073 0.00285 -0.0274 0.5276 0.1410
2.000 0.4044 0.01074 0.00284 -0.0273 0.5151 0.1410
2.250 0.4313 0.01077 0.00284 -0.0271 0.4997 0.1411
2.500 0.4582 0.01081 0.00285 -0.0270 0.4837 0.1412
2.750 0.4854 0.01084 0.00287 -0.0269 0.4705 0.1413
3.000 0.5126 0.01087 0.00290 -0.0269 0.4589 0.1414
3.250 0.5396 0.01092 0.00295 -0.0268 0.4467 0.1416
3.500 0.5666 0.01098 0.00300 -0.0267 0.4347 0.1418
3.750 0.5937 0.01104 0.00307 -0.0266 0.4220 0.1420
4.000 0.6206 0.01112 0.00315 -0.0265 0.4094 0.1422
4.250 0.6472 0.01123 0.00324 -0.0263 0.3945 0.1425
4.500 0.6726 0.01144 0.00336 -0.0260 0.3668 0.1427
4.750 0.6978 0.01169 0.00351 -0.0257 0.3354 0.1430
5.000 0.7229 0.01195 0.00367 -0.0254 0.3061 0.1433
5.250 0.7479 0.01221 0.00386 -0.0250 0.2791 0.1436
5.500 0.7724 0.01251 0.00406 -0.0246 0.2521 0.1440
5.750 0.7970 0.01282 0.00428 -0.0242 0.2258 0.1445
6.000 0.8212 0.01315 0.00454 -0.0238 0.2017 0.1450
6.250 0.8453 0.01350 0.00482 -0.0234 0.1788 0.1455
6.500 0.8691 0.01388 0.00512 -0.0229 0.1584 0.1461
6.750 0.8928 0.01425 0.00543 -0.0224 0.1382 0.1467
7.250 0.9375 0.01522 0.00620 -0.0210 0.0907 0.1481
7.500 0.9595 0.01572 0.00662 -0.0203 0.0739 0.1489
7.750 0.9819 0.01616 0.00704 -0.0196 0.0635 0.1497
8.000 1.0047 0.01654 0.00744 -0.0190 0.0570 0.1506
8.250 1.0267 0.01699 0.00788 -0.0182 0.0516 0.1515
8.500 1.0493 0.01735 0.00828 -0.0175 0.0483 0.1529
8.750 1.0707 0.01779 0.00875 -0.0167 0.0449 0.1548
9.000 1.0919 0.01823 0.00923 -0.0159 0.0423 0.1567
9.250 1.1134 0.01862 0.00968 -0.0151 0.0404 0.1586
9.500 1.1338 0.01907 0.01017 -0.0141 0.0384 0.1605
9.750 1.1529 0.01959 0.01072 -0.0130 0.0364 0.1636
10.000 1.1714 0.02011 0.01132 -0.0118 0.0349 0.1695
10.250 1.1905 0.02047 0.01190 -0.0108 0.0336 0.2867
10.500 1.2078 0.02094 0.01247 -0.0094 0.0322 0.3152
11.000 1.2365 0.02086 0.01396 -0.0059 0.0294 1.0000
11.500 1.2639 0.02221 0.01544 -0.0025 0.0274 1.0000
11.750 1.2776 0.02295 0.01623 -0.0010 0.0262 1.0000
12.000 1.2904 0.02378 0.01710 0.0004 0.0250 1.0000
12.250 1.3012 0.02480 0.01815 0.0019 0.0238 1.0000
12.500 1.3129 0.02580 0.01923 0.0032 0.0229 1.0000
12.750 1.3245 0.02685 0.02036 0.0043 0.0220 1.0000
13.000 1.3353 0.02801 0.02159 0.0054 0.0210 1.0000
13.250 1.3451 0.02930 0.02293 0.0064 0.0201 1.0000
13.500 1.3532 0.03080 0.02447 0.0073 0.0192 1.0000
13.750 1.3611 0.03237 0.02612 0.0080 0.0185 1.0000
14.000 1.3688 0.03401 0.02787 0.0087 0.0178 1.0000
14.250 1.3757 0.03580 0.02973 0.0091 0.0170 1.0000
14.500 1.3814 0.03775 0.03176 0.0095 0.0163 1.0000
14.750 1.3854 0.03995 0.03402 0.0098 0.0157 1.0000
15.000 1.3868 0.04249 0.03664 0.0099 0.0152 1.0000
15.250 1.3884 0.04507 0.03932 0.0099 0.0148 1.0000
15.500 1.3892 0.04782 0.04218 0.0097 0.0145 1.0000
15.750 1.3888 0.05078 0.04525 0.0094 0.0141 1.0000
16.000 1.3873 0.05394 0.04852 0.0089 0.0138 1.0000
16.250 1.3847 0.05735 0.05204 0.0082 0.0135 1.0000
16.500 1.3812 0.06099 0.05579 0.0073 0.0131 1.0000
16.750 1.3763 0.06491 0.05980 0.0063 0.0129 1.0000
17.000 1.3698 0.06914 0.06414 0.0050 0.0126 1.0000
17.250 1.3620 0.07367 0.06877 0.0035 0.0124 1.0000
17.500 1.3522 0.07859 0.07380 0.0017 0.0122 1.0000
17.750 1.3404 0.08389 0.07921 -0.0002 0.0120 1.0000
18.000 1.3288 0.08929 0.08472 -0.0023 0.0118 1.0000
18.250 1.3186 0.09457 0.09012 -0.0044 0.0117 1.0000
18.500 1.3075 0.10005 0.09573 -0.0067 0.0116 1.0000
18.750 1.2960 0.10570 0.10150 -0.0091 0.0114 1.0000
19.000 1.2842 0.11151 0.10743 -0.0117 0.0113 1.0000
19.250 1.2718 0.11751 0.11355 -0.0144 0.0112 1.0000
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Polar data table (+)
Polar graphs
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