NACA M12 (nacam12-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NACA M12 (nacam12-il) Reynolds number: 200,000 Max Cl/Cd: 56.6 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nacam12-il-200000-n5.txt Download as CSV file: xf-nacam12-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.5816 0.08950 0.08568 -0.0257 1.0000 0.0315
-10.500 -0.6118 0.07738 0.07361 -0.0349 1.0000 0.0314
-10.250 -0.6955 0.05986 0.05583 -0.0460 1.0000 0.0308
-10.000 -0.7393 0.05139 0.04699 -0.0441 1.0000 0.0310
-9.750 -0.7630 0.04448 0.03961 -0.0413 1.0000 0.0314
-9.500 -0.7692 0.04010 0.03480 -0.0385 1.0000 0.0321
-9.250 -0.7694 0.03665 0.03092 -0.0357 1.0000 0.0329
-9.000 -0.7654 0.03386 0.02772 -0.0329 1.0000 0.0336
-8.750 -0.7575 0.03165 0.02512 -0.0303 1.0000 0.0340
-8.500 -0.7469 0.02988 0.02303 -0.0278 1.0000 0.0344
-8.250 -0.7347 0.02847 0.02134 -0.0255 1.0000 0.0347
-8.000 -0.7225 0.02689 0.01962 -0.0232 1.0000 0.0353
-7.750 -0.6956 0.02562 0.01826 -0.0239 0.9967 0.0361
-7.500 -0.6635 0.02452 0.01704 -0.0255 0.9926 0.0369
-7.250 -0.6320 0.02338 0.01576 -0.0267 0.9875 0.0377
-7.000 -0.5985 0.02225 0.01448 -0.0284 0.9833 0.0384
-6.750 -0.5667 0.02124 0.01334 -0.0295 0.9774 0.0391
-6.500 -0.5334 0.02030 0.01227 -0.0309 0.9721 0.0398
-6.250 -0.5022 0.01947 0.01135 -0.0318 0.9648 0.0406
-6.000 -0.4693 0.01876 0.01054 -0.0331 0.9583 0.0416
-5.750 -0.4394 0.01803 0.00975 -0.0337 0.9497 0.0426
-5.500 -0.4079 0.01733 0.00905 -0.0347 0.9422 0.0438
-5.250 -0.3791 0.01679 0.00848 -0.0349 0.9324 0.0448
-5.000 -0.3481 0.01629 0.00792 -0.0356 0.9245 0.0461
-4.750 -0.3207 0.01587 0.00744 -0.0355 0.9134 0.0474
-4.500 -0.2924 0.01547 0.00699 -0.0355 0.9037 0.0490
-4.250 -0.2650 0.01511 0.00657 -0.0353 0.8930 0.0508
-4.000 -0.2386 0.01475 0.00621 -0.0350 0.8819 0.0539
-3.750 -0.2120 0.01443 0.00587 -0.0346 0.8713 0.0587
-3.500 -0.1864 0.01408 0.00557 -0.0341 0.8598 0.0665
-3.250 -0.1598 0.01390 0.00550 -0.0337 0.8484 0.0808
-3.000 -0.1297 0.01441 0.00598 -0.0338 0.8376 0.1080
-2.750 -0.1019 0.01456 0.00592 -0.0335 0.8257 0.1213
-2.500 -0.0744 0.01468 0.00588 -0.0332 0.8142 0.1282
-2.250 -0.0473 0.01476 0.00580 -0.0329 0.8030 0.1343
-2.000 -0.0207 0.01464 0.00562 -0.0326 0.7914 0.1409
-1.750 0.0059 0.01444 0.00537 -0.0323 0.7797 0.1468
-1.500 0.0324 0.01424 0.00511 -0.0320 0.7686 0.1530
-1.250 0.0584 0.01388 0.00478 -0.0316 0.7569 0.1586
-1.000 0.0851 0.01375 0.00461 -0.0313 0.7452 0.1611
-0.750 0.1111 0.01348 0.00437 -0.0309 0.7339 0.1623
-0.500 0.1372 0.01328 0.00417 -0.0306 0.7221 0.1639
-0.250 0.1637 0.01314 0.00404 -0.0303 0.7102 0.1652
0.000 0.1903 0.01307 0.00393 -0.0300 0.6985 0.1658
0.250 0.2171 0.01302 0.00384 -0.0297 0.6868 0.1661
0.500 0.2439 0.01296 0.00378 -0.0294 0.6742 0.1666
0.750 0.2708 0.01293 0.00372 -0.0292 0.6622 0.1670
1.000 0.2976 0.01293 0.00368 -0.0290 0.6502 0.1671
1.250 0.3245 0.01293 0.00366 -0.0287 0.6375 0.1672
1.500 0.3514 0.01293 0.00366 -0.0285 0.6248 0.1672
1.750 0.3783 0.01296 0.00366 -0.0283 0.6124 0.1673
2.000 0.4051 0.01300 0.00367 -0.0280 0.6000 0.1675
2.250 0.4319 0.01304 0.00370 -0.0278 0.5870 0.1676
2.500 0.4586 0.01309 0.00375 -0.0276 0.5739 0.1678
2.750 0.4853 0.01316 0.00380 -0.0274 0.5610 0.1681
3.000 0.5117 0.01324 0.00387 -0.0271 0.5472 0.1684
3.250 0.5380 0.01334 0.00394 -0.0268 0.5321 0.1687
3.500 0.5641 0.01345 0.00403 -0.0264 0.5169 0.1691
3.750 0.5904 0.01356 0.00414 -0.0262 0.5028 0.1695
4.250 0.6429 0.01380 0.00441 -0.0256 0.4763 0.1707
4.500 0.6689 0.01394 0.00457 -0.0253 0.4630 0.1715
4.750 0.6946 0.01410 0.00473 -0.0250 0.4494 0.1724
5.000 0.7203 0.01426 0.00490 -0.0246 0.4347 0.1736
5.250 0.7453 0.01445 0.00510 -0.0242 0.4159 0.1750
5.500 0.7694 0.01469 0.00529 -0.0236 0.3886 0.1769
6.000 0.8153 0.01523 0.00582 -0.0222 0.3290 0.2470
6.250 0.8382 0.01555 0.00615 -0.0215 0.3029 0.2830
6.500 0.8609 0.01592 0.00650 -0.0208 0.2758 0.2990
6.750 0.8827 0.01636 0.00689 -0.0200 0.2474 0.3120
7.250 0.9164 0.01619 0.00784 -0.0167 0.1931 0.7849
7.750 0.9757 0.01744 0.00925 -0.0185 0.1347 0.9868
8.250 1.0141 0.01901 0.01060 -0.0166 0.0900 1.0000
8.500 1.0300 0.01975 0.01128 -0.0149 0.0782 1.0000
8.750 1.0458 0.02047 0.01199 -0.0132 0.0709 1.0000
9.000 1.0609 0.02122 0.01276 -0.0114 0.0653 1.0000
9.250 1.0751 0.02201 0.01356 -0.0096 0.0612 1.0000
9.500 1.0899 0.02272 0.01435 -0.0078 0.0577 1.0000
9.750 1.1016 0.02354 0.01520 -0.0057 0.0546 1.0000
10.000 1.1083 0.02457 0.01622 -0.0029 0.0521 1.0000
10.250 1.1204 0.02535 0.01712 -0.0009 0.0501 1.0000
10.500 1.1313 0.02627 0.01812 0.0010 0.0479 1.0000
10.750 1.1413 0.02730 0.01921 0.0028 0.0459 1.0000
11.000 1.1489 0.02855 0.02049 0.0046 0.0441 1.0000
11.250 1.1554 0.02996 0.02195 0.0063 0.0425 1.0000
11.500 1.1658 0.03116 0.02327 0.0076 0.0410 1.0000
11.750 1.1749 0.03250 0.02472 0.0088 0.0393 1.0000
12.000 1.1831 0.03396 0.02626 0.0099 0.0378 1.0000
12.250 1.1896 0.03562 0.02797 0.0108 0.0365 1.0000
12.500 1.1925 0.03767 0.03004 0.0118 0.0353 1.0000
12.750 1.2005 0.03935 0.03187 0.0125 0.0341 1.0000
13.000 1.2069 0.04121 0.03386 0.0131 0.0329 1.0000
13.250 1.2124 0.04320 0.03596 0.0136 0.0317 1.0000
13.500 1.2168 0.04535 0.03821 0.0138 0.0306 1.0000
13.750 1.2195 0.04773 0.04065 0.0140 0.0297 1.0000
14.000 1.2198 0.05040 0.04336 0.0141 0.0289 1.0000
14.250 1.2230 0.05288 0.04602 0.0142 0.0280 1.0000
14.500 1.2246 0.05558 0.04887 0.0141 0.0272 1.0000
14.750 1.2251 0.05845 0.05188 0.0138 0.0263 1.0000
15.000 1.2249 0.06149 0.05503 0.0133 0.0256 1.0000
15.250 1.2239 0.06471 0.05835 0.0126 0.0249 1.0000
15.500 1.2221 0.06812 0.06186 0.0117 0.0243 1.0000
15.750 1.2191 0.07176 0.06557 0.0106 0.0238 1.0000
16.000 1.2153 0.07559 0.06952 0.0096 0.0233 1.0000
16.250 1.2105 0.07975 0.07389 0.0082 0.0227 1.0000
16.500 1.2047 0.08418 0.07849 0.0066 0.0222 1.0000
16.750 1.1978 0.08887 0.08334 0.0048 0.0217 1.0000
17.000 1.1900 0.09380 0.08843 0.0028 0.0213 1.0000
17.250 1.1816 0.09898 0.09376 0.0005 0.0209 1.0000
17.500 1.1725 0.10440 0.09932 -0.0020 0.0206 1.0000
17.750 1.1627 0.11007 0.10512 -0.0048 0.0203 1.0000
18.000 1.1523 0.11598 0.11116 -0.0078 0.0201 1.0000
18.250 1.1416 0.12212 0.11743 -0.0111 0.0198 1.0000
18.500 1.1306 0.12847 0.12389 -0.0146 0.0196 1.0000
18.750 1.1192 0.13507 0.13062 -0.0184 0.0194 1.0000
19.000 1.1070 0.14197 0.13762 -0.0224 0.0192 1.0000
19.250 1.0938 0.14933 0.14510 -0.0268 0.0190 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA M12 (nacam12-il)