NACA M12 (nacam12-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: NACA M12 (nacam12-il) Reynolds number: 200,000 Max Cl/Cd: 66.31 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nacam12-il-200000.txt Download as CSV file: xf-nacam12-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5018 0.09627 0.09254 -0.0218 1.0000 0.0760
-9.500 -0.4024 0.08411 0.08061 -0.0315 1.0000 0.0824
-9.250 -0.5978 0.08053 0.07666 -0.0409 1.0000 0.0794
-9.000 -0.5811 0.07495 0.07122 -0.0407 1.0000 0.0805
-8.750 -0.5600 0.07308 0.06942 -0.0389 1.0000 0.0816
-8.500 -0.5539 0.07051 0.06686 -0.0381 1.0000 0.0830
-8.250 -0.5548 0.06739 0.06371 -0.0379 1.0000 0.0851
-8.000 -0.6093 0.06470 0.06031 -0.0348 1.0000 0.0905
-7.750 -0.5917 0.05917 0.05507 -0.0348 1.0000 0.0918
-7.500 -0.5795 0.05705 0.05304 -0.0331 1.0000 0.0933
-7.250 -0.5768 0.05513 0.05111 -0.0304 1.0000 0.0953
-6.750 -0.6412 0.03404 0.02782 -0.0158 1.0000 0.0585
-6.500 -0.6329 0.03170 0.02518 -0.0131 1.0000 0.0585
-6.250 -0.6018 0.02841 0.02148 -0.0147 0.9963 0.0587
-6.000 -0.5662 0.02580 0.01847 -0.0168 0.9926 0.0586
-5.750 -0.5310 0.02356 0.01597 -0.0187 0.9880 0.0591
-5.500 -0.4926 0.02193 0.01421 -0.0212 0.9841 0.0603
-5.250 -0.4546 0.02086 0.01307 -0.0235 0.9794 0.0623
-5.000 -0.4168 0.01977 0.01189 -0.0257 0.9740 0.0642
-4.750 -0.3758 0.01870 0.01072 -0.0284 0.9703 0.0659
-4.500 -0.3387 0.01784 0.00977 -0.0303 0.9644 0.0677
-4.250 -0.3009 0.01676 0.00871 -0.0325 0.9591 0.0707
-4.000 -0.2592 0.01601 0.00799 -0.0355 0.9554 0.0762
-3.750 -0.2257 0.01538 0.00740 -0.0366 0.9473 0.0827
-3.500 -0.1859 0.01531 0.00747 -0.0388 0.9411 0.0939
-3.250 -0.1487 0.01605 0.00807 -0.0401 0.9324 0.1162
-3.000 -0.1152 0.01629 0.00802 -0.0409 0.9240 0.1420
-2.750 -0.0874 0.01564 0.00732 -0.0409 0.9137 0.1577
-2.500 -0.0579 0.01471 0.00647 -0.0411 0.9057 0.1691
-2.250 -0.0339 0.01408 0.00593 -0.0403 0.8936 0.1774
-2.000 -0.0107 0.01336 0.00533 -0.0394 0.8828 0.1864
-1.750 0.0134 0.01282 0.00485 -0.0384 0.8724 0.1974
-1.500 0.0368 0.01244 0.00461 -0.0375 0.8599 0.2118
-1.250 0.0610 0.01211 0.00457 -0.0366 0.8486 0.2892
-1.000 0.0874 0.01200 0.00443 -0.0360 0.8380 0.3092
-0.750 0.1134 0.01195 0.00435 -0.0354 0.8252 0.3200
-0.500 0.1397 0.01189 0.00427 -0.0348 0.8132 0.3306
-0.250 0.1663 0.01183 0.00417 -0.0342 0.8021 0.3390
0.000 0.1929 0.01181 0.00411 -0.0338 0.7895 0.3456
0.250 0.2195 0.01179 0.00408 -0.0333 0.7766 0.3527
0.500 0.2462 0.01177 0.00405 -0.0328 0.7645 0.3618
0.750 0.2726 0.01170 0.00399 -0.0323 0.7529 0.3826
1.000 0.2959 0.01132 0.00399 -0.0314 0.7396 0.4942
1.250 0.3140 0.01061 0.00409 -0.0291 0.7270 0.7105
1.500 0.3395 0.01054 0.00419 -0.0282 0.7148 0.7721
1.750 0.3674 0.01056 0.00427 -0.0277 0.7028 0.8201
2.000 0.3963 0.01063 0.00440 -0.0276 0.6890 0.8519
2.250 0.4263 0.01073 0.00451 -0.0278 0.6754 0.8774
2.500 0.4570 0.01085 0.00462 -0.0281 0.6620 0.8998
2.750 0.4877 0.01097 0.00472 -0.0285 0.6486 0.9173
3.000 0.5186 0.01110 0.00480 -0.0290 0.6346 0.9306
3.250 0.5499 0.01123 0.00489 -0.0295 0.6197 0.9442
3.500 0.5790 0.01137 0.00500 -0.0296 0.6043 0.9544
3.750 0.6113 0.01151 0.00513 -0.0305 0.5891 0.9626
4.000 0.6424 0.01168 0.00529 -0.0312 0.5743 0.9713
4.250 0.6759 0.01186 0.00546 -0.0324 0.5593 0.9800
4.500 0.7127 0.01205 0.00563 -0.0344 0.5436 0.9871
4.750 0.7487 0.01226 0.00583 -0.0362 0.5276 0.9939
5.000 0.7873 0.01244 0.00598 -0.0386 0.5082 1.0000
5.250 0.8088 0.01262 0.00607 -0.0373 0.4877 1.0000
5.500 0.8298 0.01278 0.00623 -0.0360 0.4645 1.0000
5.750 0.8510 0.01299 0.00640 -0.0347 0.4439 1.0000
6.000 0.8720 0.01323 0.00659 -0.0334 0.4240 1.0000
6.250 0.8927 0.01349 0.00683 -0.0321 0.4031 1.0000
6.500 0.9131 0.01377 0.00708 -0.0307 0.3798 1.0000
6.750 0.9326 0.01412 0.00736 -0.0292 0.3553 1.0000
7.000 0.9513 0.01450 0.00767 -0.0277 0.3269 1.0000
7.250 0.9690 0.01498 0.00805 -0.0259 0.2948 1.0000
7.500 0.9853 0.01556 0.00849 -0.0241 0.2587 1.0000
7.750 0.9995 0.01633 0.00904 -0.0220 0.2162 1.0000
8.000 1.0104 0.01740 0.00980 -0.0195 0.1669 1.0000
8.250 1.0188 0.01870 0.01078 -0.0167 0.1232 1.0000
8.500 1.0296 0.01982 0.01176 -0.0142 0.1016 1.0000
8.750 1.0415 0.02084 0.01273 -0.0118 0.0905 1.0000
9.000 1.0513 0.02198 0.01379 -0.0093 0.0833 1.0000
9.250 1.0648 0.02284 0.01471 -0.0072 0.0778 1.0000
9.500 1.0726 0.02407 0.01586 -0.0045 0.0733 1.0000
9.750 1.0837 0.02503 0.01691 -0.0022 0.0699 1.0000
10.000 1.0949 0.02601 0.01793 0.0000 0.0665 1.0000
10.250 1.1049 0.02720 0.01911 0.0021 0.0635 1.0000
10.500 1.1170 0.02869 0.02059 0.0039 0.0607 1.0000
10.750 1.1302 0.02974 0.02176 0.0055 0.0582 1.0000
11.000 1.1436 0.03093 0.02300 0.0070 0.0558 1.0000
11.250 1.1576 0.03229 0.02433 0.0082 0.0534 1.0000
11.500 1.1750 0.03411 0.02620 0.0091 0.0511 1.0000
11.750 1.1862 0.03538 0.02764 0.0107 0.0493 1.0000
12.000 1.1985 0.03683 0.02922 0.0120 0.0475 1.0000
12.250 1.2108 0.03832 0.03077 0.0132 0.0459 1.0000
12.500 1.2305 0.04026 0.03265 0.0136 0.0440 1.0000
12.750 1.2381 0.04250 0.03511 0.0150 0.0428 1.0000
13.000 1.2400 0.04436 0.03722 0.0168 0.0417 1.0000
13.250 1.2428 0.04648 0.03955 0.0183 0.0406 1.0000
13.500 1.2456 0.04877 0.04203 0.0195 0.0397 1.0000
13.750 1.2486 0.05111 0.04452 0.0205 0.0389 1.0000
14.000 1.2494 0.05356 0.04711 0.0214 0.0381 1.0000
14.250 1.2522 0.05605 0.04967 0.0221 0.0373 1.0000
14.500 1.2568 0.05965 0.05335 0.0226 0.0364 1.0000
14.750 1.2417 0.06374 0.05770 0.0231 0.0361 1.0000
15.000 1.2243 0.06780 0.06202 0.0229 0.0359 1.0000
15.250 1.2055 0.07245 0.06694 0.0220 0.0357 1.0000
15.500 1.1849 0.07771 0.07244 0.0205 0.0356 1.0000
15.750 1.1627 0.08363 0.07860 0.0183 0.0355 1.0000
16.000 1.1388 0.09024 0.08543 0.0153 0.0356 1.0000
16.250 1.1135 0.09765 0.09306 0.0114 0.0356 1.0000
16.500 1.0868 0.10593 0.10153 0.0068 0.0358 1.0000
16.750 1.0593 0.11503 0.11080 0.0015 0.0360 1.0000
17.000 1.0315 0.12494 0.12086 -0.0042 0.0362 1.0000
17.250 0.6156 0.17190 0.16843 -0.0147 0.0724 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA M12 (nacam12-il)