NACA M12 (nacam12-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA M12 (nacam12-il) Reynolds number: 50,000 Max Cl/Cd: 33.61 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nacam12-il-50000-n5.txt Download as CSV file: xf-nacam12-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5106 0.10070 0.09311 -0.0256 1.0000 0.0787
-9.750 -0.5138 0.09573 0.08818 -0.0282 1.0000 0.0775
-9.500 -0.5212 0.09001 0.08251 -0.0320 1.0000 0.0763
-9.250 -0.5371 0.08341 0.07594 -0.0369 1.0000 0.0749
-9.000 -0.5598 0.07779 0.07030 -0.0389 1.0000 0.0737
-8.750 -0.5791 0.07258 0.06498 -0.0396 1.0000 0.0728
-8.500 -0.5941 0.06782 0.06003 -0.0392 1.0000 0.0721
-8.250 -0.6021 0.06367 0.05566 -0.0380 1.0000 0.0717
-8.000 -0.6034 0.06025 0.05204 -0.0365 1.0000 0.0719
-7.750 -0.5994 0.05758 0.04924 -0.0349 1.0000 0.0729
-7.500 -0.5950 0.05504 0.04654 -0.0330 1.0000 0.0741
-7.250 -0.5904 0.05246 0.04372 -0.0309 1.0000 0.0754
-7.000 -0.5852 0.04981 0.04081 -0.0287 1.0000 0.0763
-6.750 -0.5786 0.04720 0.03791 -0.0264 1.0000 0.0769
-6.500 -0.5702 0.04473 0.03512 -0.0242 1.0000 0.0773
-6.250 -0.5601 0.04241 0.03249 -0.0219 1.0000 0.0780
-6.000 -0.5485 0.04023 0.02998 -0.0198 1.0000 0.0788
-5.750 -0.5352 0.03815 0.02755 -0.0178 1.0000 0.0799
-5.500 -0.5206 0.03636 0.02543 -0.0159 1.0000 0.0820
-5.250 -0.5051 0.03556 0.02460 -0.0143 1.0000 0.0843
-5.000 -0.4888 0.03453 0.02343 -0.0128 1.0000 0.0869
-4.750 -0.4713 0.03328 0.02195 -0.0113 1.0000 0.0895
-4.250 -0.4341 0.03124 0.01960 -0.0088 1.0000 0.0942
-4.000 -0.3997 0.03030 0.01849 -0.0104 0.9944 0.0992
-3.750 -0.3608 0.02962 0.01762 -0.0129 0.9862 0.1081
-3.500 -0.3221 0.02896 0.01670 -0.0152 0.9777 0.1199
-3.250 -0.2811 0.02810 0.01557 -0.0177 0.9704 0.1363
-3.000 -0.2437 0.02671 0.01408 -0.0197 0.9623 0.1591
-2.750 -0.2044 0.02472 0.01233 -0.0226 0.9568 0.1875
-2.500 -0.1750 0.02344 0.01168 -0.0240 0.9465 0.2188
-2.250 -0.1389 0.02290 0.01146 -0.0261 0.9372 0.3030
-2.000 -0.1067 0.02199 0.01117 -0.0275 0.9275 0.4029
-1.750 -0.0781 0.02103 0.01130 -0.0270 0.9182 0.6182
-1.500 -0.0236 0.02097 0.01162 -0.0306 0.9117 0.7858
-1.250 0.0257 0.02109 0.01165 -0.0341 0.9030 0.8543
-1.000 0.0703 0.02118 0.01160 -0.0370 0.8931 0.8920
-0.750 0.1119 0.02129 0.01158 -0.0395 0.8818 0.9199
-0.500 0.1556 0.02130 0.01145 -0.0424 0.8720 0.9377
-0.250 0.1948 0.02134 0.01140 -0.0446 0.8595 0.9522
0.000 0.2347 0.02138 0.01135 -0.0469 0.8469 0.9661
0.250 0.2773 0.02137 0.01125 -0.0497 0.8353 0.9792
0.500 0.3209 0.02131 0.01113 -0.0527 0.8235 0.9915
0.750 0.3571 0.02134 0.01111 -0.0545 0.8094 1.0000
1.000 0.3800 0.02144 0.01115 -0.0534 0.7951 1.0000
1.250 0.4031 0.02153 0.01120 -0.0524 0.7813 1.0000
1.500 0.4271 0.02161 0.01122 -0.0514 0.7683 1.0000
1.750 0.4510 0.02169 0.01126 -0.0505 0.7553 1.0000
2.000 0.4726 0.02188 0.01143 -0.0492 0.7409 1.0000
2.250 0.4947 0.02207 0.01160 -0.0480 0.7270 1.0000
2.500 0.5175 0.02223 0.01175 -0.0469 0.7138 1.0000
2.750 0.5416 0.02235 0.01185 -0.0458 0.7014 1.0000
3.000 0.5639 0.02254 0.01205 -0.0446 0.6878 1.0000
3.250 0.5851 0.02281 0.01233 -0.0433 0.6736 1.0000
3.500 0.6069 0.02305 0.01261 -0.0420 0.6598 1.0000
3.750 0.6294 0.02327 0.01283 -0.0408 0.6464 1.0000
4.000 0.6527 0.02344 0.01301 -0.0396 0.6332 1.0000
4.250 0.6753 0.02364 0.01324 -0.0383 0.6193 1.0000
4.500 0.6963 0.02392 0.01356 -0.0369 0.6041 1.0000
4.750 0.7174 0.02418 0.01387 -0.0354 0.5888 1.0000
5.000 0.7388 0.02444 0.01416 -0.0340 0.5731 1.0000
5.250 0.7601 0.02470 0.01448 -0.0325 0.5572 1.0000
5.500 0.7814 0.02497 0.01480 -0.0310 0.5412 1.0000
5.750 0.8025 0.02527 0.01515 -0.0296 0.5248 1.0000
6.000 0.8234 0.02559 0.01554 -0.0281 0.5081 1.0000
6.250 0.8440 0.02592 0.01593 -0.0266 0.4907 1.0000
6.500 0.8642 0.02626 0.01633 -0.0250 0.4724 1.0000
6.750 0.8841 0.02658 0.01668 -0.0233 0.4530 1.0000
7.000 0.9015 0.02693 0.01709 -0.0213 0.4302 1.0000
7.250 0.9168 0.02728 0.01743 -0.0190 0.4034 1.0000
7.500 0.9299 0.02772 0.01786 -0.0165 0.3739 1.0000
7.750 0.9423 0.02827 0.01835 -0.0140 0.3439 1.0000
8.000 0.9539 0.02895 0.01896 -0.0115 0.3144 1.0000
8.250 0.9638 0.02978 0.01973 -0.0090 0.2847 1.0000
8.500 0.9721 0.03080 0.02066 -0.0065 0.2551 1.0000
8.750 0.9783 0.03201 0.02177 -0.0039 0.2261 1.0000
9.000 0.9830 0.03342 0.02304 -0.0012 0.2006 1.0000
9.250 0.9853 0.03495 0.02446 0.0016 0.1792 1.0000
9.500 0.9870 0.03662 0.02603 0.0042 0.1619 1.0000
10.000 0.9952 0.04020 0.02957 0.0084 0.1355 1.0000
10.250 1.0002 0.04206 0.03138 0.0101 0.1261 1.0000
10.500 1.0071 0.04390 0.03327 0.0115 0.1174 1.0000
10.750 1.0167 0.04572 0.03513 0.0129 0.1110 1.0000
11.000 1.0270 0.04755 0.03706 0.0141 0.1047 1.0000
11.250 1.0372 0.04935 0.03880 0.0152 0.0995 1.0000
11.500 1.0466 0.05144 0.04120 0.0163 0.0943 1.0000
11.750 1.0573 0.05342 0.04326 0.0172 0.0901 1.0000
12.000 1.0712 0.05529 0.04508 0.0182 0.0864 1.0000
12.250 1.0736 0.05812 0.04827 0.0190 0.0830 1.0000
12.500 1.0755 0.06093 0.05132 0.0196 0.0799 1.0000
12.750 1.0793 0.06361 0.05412 0.0202 0.0773 1.0000
13.000 1.0925 0.06569 0.05616 0.0209 0.0744 1.0000
13.250 1.0815 0.06989 0.06069 0.0208 0.0730 1.0000
13.500 1.0671 0.07467 0.06581 0.0201 0.0718 1.0000
13.750 1.0496 0.08008 0.07152 0.0186 0.0708 1.0000
14.000 1.0280 0.08643 0.07814 0.0162 0.0702 1.0000
14.250 1.0003 0.09425 0.08619 0.0125 0.0701 1.0000
14.500 0.9640 0.10446 0.09663 0.0069 0.0707 1.0000
14.750 0.9186 0.11819 0.11054 -0.0012 0.0717 1.0000
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Polar data table (+)
Polar graphs
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