NACA M12 (nacam12-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA M12 (nacam12-il) Reynolds number: 100,000 Max Cl/Cd: 48.82 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nacam12-il-100000-n5.txt Download as CSV file: xf-nacam12-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.5441 0.09202 0.08665 -0.0279 1.0000 0.0483
-10.000 -0.5534 0.08546 0.08011 -0.0323 1.0000 0.0479
-9.750 -0.5734 0.07666 0.07132 -0.0399 1.0000 0.0473
-9.500 -0.6000 0.07012 0.06472 -0.0427 1.0000 0.0468
-9.250 -0.6223 0.06498 0.05944 -0.0425 1.0000 0.0465
-9.000 -0.6382 0.06008 0.05436 -0.0416 1.0000 0.0464
-8.750 -0.6484 0.05559 0.04962 -0.0399 1.0000 0.0464
-8.500 -0.6541 0.05149 0.04524 -0.0378 1.0000 0.0468
-8.250 -0.6575 0.04756 0.04099 -0.0352 1.0000 0.0476
-8.000 -0.6595 0.04360 0.03662 -0.0322 1.0000 0.0485
-7.750 -0.6581 0.04002 0.03261 -0.0291 1.0000 0.0491
-7.500 -0.6528 0.03701 0.02917 -0.0263 1.0000 0.0494
-7.250 -0.6446 0.03446 0.02621 -0.0236 1.0000 0.0498
-7.000 -0.6337 0.03233 0.02369 -0.0211 1.0000 0.0503
-6.750 -0.6205 0.03072 0.02190 -0.0190 1.0000 0.0509
-6.500 -0.6063 0.02965 0.02077 -0.0172 1.0000 0.0518
-6.250 -0.5806 0.02857 0.01956 -0.0175 0.9968 0.0534
-6.000 -0.5462 0.02718 0.01794 -0.0194 0.9912 0.0553
-5.750 -0.5115 0.02570 0.01621 -0.0211 0.9854 0.0567
-5.500 -0.4765 0.02439 0.01468 -0.0228 0.9794 0.0581
-5.250 -0.4407 0.02328 0.01339 -0.0246 0.9732 0.0596
-5.000 -0.4062 0.02228 0.01241 -0.0263 0.9667 0.0615
-4.750 -0.3708 0.02151 0.01166 -0.0281 0.9599 0.0647
-4.500 -0.3357 0.02076 0.01085 -0.0298 0.9532 0.0691
-4.250 -0.3027 0.02006 0.01021 -0.0310 0.9451 0.0734
-4.000 -0.2693 0.01951 0.00968 -0.0322 0.9373 0.0794
-3.750 -0.2354 0.01937 0.00966 -0.0335 0.9283 0.0869
-3.500 -0.2013 0.01953 0.00979 -0.0346 0.9192 0.0983
-3.250 -0.1670 0.01968 0.00962 -0.0355 0.9100 0.1237
-3.000 -0.1369 0.01962 0.00931 -0.0359 0.8996 0.1380
-2.750 -0.1049 0.01916 0.00873 -0.0366 0.8910 0.1495
-2.500 -0.0790 0.01836 0.00802 -0.0365 0.8796 0.1633
-2.250 -0.0528 0.01745 0.00723 -0.0362 0.8698 0.1767
-2.000 -0.0270 0.01686 0.00667 -0.0359 0.8589 0.1855
-1.750 -0.0010 0.01650 0.00633 -0.0354 0.8472 0.1925
-1.500 0.0264 0.01617 0.00603 -0.0352 0.8369 0.1996
-1.250 0.0529 0.01592 0.00589 -0.0348 0.8252 0.2085
-1.000 0.0788 0.01563 0.00584 -0.0344 0.8133 0.2729
-0.750 0.1069 0.01560 0.00573 -0.0341 0.8024 0.2905
-0.500 0.1343 0.01558 0.00563 -0.0338 0.7906 0.3015
-0.250 0.1613 0.01557 0.00558 -0.0334 0.7782 0.3098
0.000 0.1888 0.01556 0.00552 -0.0331 0.7666 0.3153
0.250 0.2162 0.01553 0.00545 -0.0327 0.7553 0.3233
0.500 0.2430 0.01557 0.00545 -0.0324 0.7422 0.3275
0.750 0.2701 0.01560 0.00544 -0.0320 0.7301 0.3319
1.000 0.2974 0.01561 0.00542 -0.0317 0.7185 0.3371
1.250 0.3243 0.01565 0.00545 -0.0314 0.7058 0.3435
1.500 0.3510 0.01568 0.00551 -0.0310 0.6929 0.3515
2.000 0.4031 0.01552 0.00557 -0.0301 0.6690 0.4145
2.250 0.4211 0.01451 0.00591 -0.0275 0.6564 0.7683
2.500 0.4551 0.01457 0.00613 -0.0283 0.6430 0.8370
2.750 0.4882 0.01468 0.00629 -0.0291 0.6300 0.8752
3.000 0.5192 0.01482 0.00642 -0.0296 0.6170 0.8976
3.250 0.5494 0.01497 0.00658 -0.0299 0.6032 0.9169
3.500 0.5793 0.01514 0.00676 -0.0303 0.5886 0.9338
3.750 0.6094 0.01531 0.00694 -0.0307 0.5735 0.9486
4.000 0.6397 0.01550 0.00711 -0.0311 0.5577 0.9618
4.250 0.6703 0.01570 0.00731 -0.0317 0.5415 0.9733
4.500 0.7011 0.01591 0.00753 -0.0324 0.5256 0.9834
4.750 0.7337 0.01614 0.00777 -0.0335 0.5097 0.9927
5.000 0.7659 0.01639 0.00804 -0.0345 0.4936 1.0000
5.250 0.7879 0.01664 0.00829 -0.0334 0.4786 1.0000
5.500 0.8096 0.01691 0.00856 -0.0322 0.4633 1.0000
5.750 0.8308 0.01718 0.00884 -0.0310 0.4461 1.0000
6.000 0.8507 0.01747 0.00912 -0.0295 0.4237 1.0000
6.250 0.8694 0.01781 0.00937 -0.0278 0.3966 1.0000
6.500 0.8873 0.01820 0.00966 -0.0261 0.3674 1.0000
6.750 0.9057 0.01863 0.01005 -0.0245 0.3391 1.0000
7.000 0.9236 0.01912 0.01046 -0.0229 0.3111 1.0000
7.250 0.9405 0.01968 0.01093 -0.0212 0.2817 1.0000
7.500 0.9567 0.02034 0.01147 -0.0194 0.2516 1.0000
7.750 0.9717 0.02109 0.01210 -0.0175 0.2212 1.0000
8.000 0.9861 0.02193 0.01283 -0.0157 0.1918 1.0000
8.250 0.9994 0.02286 0.01364 -0.0137 0.1638 1.0000
8.500 1.0117 0.02387 0.01453 -0.0117 0.1388 1.0000
8.750 1.0233 0.02492 0.01550 -0.0096 0.1188 1.0000
9.000 1.0341 0.02600 0.01653 -0.0074 0.1050 1.0000
9.250 1.0439 0.02711 0.01763 -0.0051 0.0953 1.0000
9.500 1.0517 0.02828 0.01877 -0.0027 0.0880 1.0000
9.750 1.0593 0.02937 0.01992 -0.0001 0.0823 1.0000
10.000 1.0659 0.03056 0.02115 0.0023 0.0777 1.0000
10.500 1.0790 0.03328 0.02396 0.0066 0.0709 1.0000
10.750 1.0869 0.03465 0.02543 0.0083 0.0674 1.0000
11.000 1.0933 0.03619 0.02701 0.0099 0.0646 1.0000
11.250 1.0993 0.03791 0.02872 0.0115 0.0622 1.0000
11.500 1.1088 0.03943 0.03040 0.0127 0.0596 1.0000
11.750 1.1169 0.04107 0.03216 0.0139 0.0570 1.0000
12.000 1.1239 0.04282 0.03397 0.0149 0.0547 1.0000
12.250 1.1305 0.04471 0.03588 0.0159 0.0529 1.0000
12.500 1.1382 0.04665 0.03794 0.0169 0.0510 1.0000
12.750 1.1442 0.04871 0.04021 0.0176 0.0489 1.0000
13.000 1.1492 0.05087 0.04252 0.0183 0.0471 1.0000
13.250 1.1537 0.05311 0.04486 0.0188 0.0455 1.0000
13.500 1.1582 0.05537 0.04716 0.0193 0.0442 1.0000
13.750 1.1631 0.05779 0.04960 0.0198 0.0428 1.0000
14.000 1.1605 0.06094 0.05305 0.0199 0.0416 1.0000
14.250 1.1569 0.06432 0.05670 0.0196 0.0404 1.0000
14.500 1.1524 0.06787 0.06046 0.0192 0.0393 1.0000
14.750 1.1473 0.07160 0.06438 0.0186 0.0384 1.0000
15.000 1.1410 0.07553 0.06848 0.0176 0.0377 1.0000
15.250 1.1346 0.07956 0.07265 0.0165 0.0369 1.0000
15.500 1.1290 0.08359 0.07679 0.0152 0.0363 1.0000
15.750 1.1256 0.08737 0.08062 0.0141 0.0356 1.0000
16.000 1.1121 0.09295 0.08638 0.0118 0.0351 1.0000
16.250 1.0910 0.10021 0.09391 0.0080 0.0349 1.0000
16.500 1.0674 0.10841 0.10236 0.0033 0.0348 1.0000
16.750 1.0406 0.11785 0.11204 -0.0023 0.0348 1.0000
17.000 1.0092 0.12913 0.12354 -0.0093 0.0350 1.0000
17.250 0.9693 0.14370 0.13826 -0.0184 0.0353 1.0000
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Polar data table (+)
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