NACA M6 (nacam6-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA M6 (nacam6-il) Reynolds number: 50,000 Max Cl/Cd: 32.17 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nacam6-il-50000-n5.txt Download as CSV file: xf-nacam6-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA M6
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 -0.4808 0.09659 0.08902 -0.0345 1.0000 0.0784
-9.750 -0.4777 0.09280 0.08526 -0.0352 1.0000 0.0775
-9.500 -0.4809 0.08836 0.08086 -0.0372 1.0000 0.0766
-9.250 -0.4894 0.08370 0.07623 -0.0392 1.0000 0.0756
-9.000 -0.5021 0.07933 0.07188 -0.0402 1.0000 0.0746
-8.750 -0.5191 0.07530 0.06788 -0.0397 1.0000 0.0738
-8.500 -0.5372 0.07176 0.06432 -0.0377 1.0000 0.0730
-8.250 -0.5528 0.06816 0.06066 -0.0355 1.0000 0.0723
-8.000 -0.5667 0.06467 0.05707 -0.0327 1.0000 0.0717
-7.750 -0.5788 0.06135 0.05360 -0.0295 1.0000 0.0711
-7.500 -0.5880 0.05840 0.05049 -0.0260 1.0000 0.0711
-7.250 -0.5944 0.05581 0.04773 -0.0223 1.0000 0.0713
-7.000 -0.5996 0.05347 0.04523 -0.0184 1.0000 0.0718
-6.750 -0.6045 0.05138 0.04297 -0.0142 1.0000 0.0724
-6.500 -0.6098 0.04946 0.04087 -0.0098 1.0000 0.0731
-6.250 -0.6147 0.04763 0.03882 -0.0052 1.0000 0.0735
-6.000 -0.6184 0.04587 0.03683 -0.0008 1.0000 0.0738
-5.750 -0.6031 0.04329 0.03386 0.0001 0.9925 0.0742
-5.500 -0.5750 0.04050 0.03058 -0.0010 0.9807 0.0747
-5.250 -0.5443 0.03802 0.02760 -0.0022 0.9698 0.0755
-5.000 -0.5111 0.03583 0.02495 -0.0037 0.9594 0.0766
-4.750 -0.4772 0.03403 0.02265 -0.0049 0.9488 0.0788
-4.500 -0.4391 0.03247 0.02105 -0.0075 0.9401 0.0821
-4.250 -0.3997 0.03110 0.01950 -0.0099 0.9309 0.0856
-4.000 -0.3542 0.02964 0.01780 -0.0132 0.9234 0.0890
-3.750 -0.3041 0.02826 0.01623 -0.0172 0.9160 0.0935
-3.500 -0.2519 0.02711 0.01507 -0.0219 0.9097 0.1020
-3.250 -0.2094 0.02620 0.01415 -0.0248 0.8998 0.1149
-3.000 -0.1677 0.02522 0.01316 -0.0275 0.8908 0.1354
-2.750 -0.1314 0.02415 0.01236 -0.0293 0.8810 0.1760
-2.500 -0.0163 0.02150 0.01290 -0.0432 0.8852 0.8477
-2.250 0.0715 0.02262 0.01352 -0.0518 0.8808 0.9483
-2.000 0.1863 0.02203 0.01244 -0.0686 0.8775 1.0000
-1.750 0.2145 0.02192 0.01209 -0.0690 0.8618 1.0000
-1.500 0.2403 0.02186 0.01183 -0.0689 0.8469 1.0000
-1.250 0.2634 0.02185 0.01165 -0.0683 0.8319 1.0000
-1.000 0.2854 0.02188 0.01152 -0.0674 0.8176 1.0000
-0.750 0.3067 0.02193 0.01143 -0.0664 0.8039 1.0000
-0.500 0.3282 0.02199 0.01137 -0.0653 0.7913 1.0000
-0.250 0.3502 0.02204 0.01128 -0.0643 0.7799 1.0000
0.000 0.3707 0.02215 0.01130 -0.0630 0.7675 1.0000
0.250 0.3910 0.02229 0.01136 -0.0618 0.7556 1.0000
0.500 0.4123 0.02240 0.01138 -0.0606 0.7450 1.0000
0.750 0.4330 0.02254 0.01145 -0.0593 0.7340 1.0000
1.000 0.4530 0.02274 0.01161 -0.0580 0.7227 1.0000
1.250 0.4754 0.02286 0.01166 -0.0569 0.7131 1.0000
1.500 0.4959 0.02308 0.01187 -0.0558 0.7020 1.0000
1.750 0.5167 0.02331 0.01209 -0.0546 0.6915 1.0000
2.000 0.5390 0.02344 0.01218 -0.0534 0.6824 1.0000
2.250 0.5581 0.02377 0.01254 -0.0521 0.6711 1.0000
2.500 0.5792 0.02398 0.01274 -0.0508 0.6616 1.0000
2.750 0.5997 0.02423 0.01300 -0.0494 0.6515 1.0000
3.000 0.6189 0.02456 0.01338 -0.0480 0.6409 1.0000
3.250 0.6414 0.02469 0.01349 -0.0467 0.6324 1.0000
3.500 0.6591 0.02512 0.01400 -0.0452 0.6208 1.0000
3.750 0.6789 0.02542 0.01435 -0.0437 0.6106 1.0000
4.000 0.7001 0.02561 0.01456 -0.0422 0.6008 1.0000
4.250 0.7176 0.02603 0.01506 -0.0405 0.5889 1.0000
4.500 0.7372 0.02630 0.01540 -0.0389 0.5781 1.0000
4.750 0.7585 0.02645 0.01558 -0.0374 0.5678 1.0000
5.000 0.7753 0.02689 0.01613 -0.0355 0.5554 1.0000
5.250 0.7938 0.02723 0.01655 -0.0338 0.5439 1.0000
5.500 0.8157 0.02734 0.01671 -0.0323 0.5337 1.0000
5.750 0.8323 0.02778 0.01728 -0.0304 0.5213 1.0000
6.000 0.8492 0.02822 0.01783 -0.0285 0.5090 1.0000
6.250 0.8679 0.02853 0.01826 -0.0267 0.4974 1.0000
6.500 0.8896 0.02865 0.01844 -0.0251 0.4865 1.0000
6.750 0.9046 0.02918 0.01912 -0.0230 0.4731 1.0000
7.000 0.9206 0.02958 0.01964 -0.0208 0.4591 1.0000
7.250 0.9369 0.02980 0.01996 -0.0185 0.4433 1.0000
7.500 0.9529 0.02984 0.02004 -0.0160 0.4250 1.0000
7.750 0.9658 0.03002 0.02025 -0.0132 0.4048 1.0000
8.000 0.9755 0.03043 0.02075 -0.0102 0.3837 1.0000
8.250 0.9862 0.03082 0.02116 -0.0072 0.3633 1.0000
8.500 0.9939 0.03133 0.02170 -0.0040 0.3409 1.0000
8.750 0.9984 0.03203 0.02240 -0.0005 0.3170 1.0000
9.000 1.0004 0.03287 0.02319 0.0032 0.2920 1.0000
9.250 0.9997 0.03386 0.02410 0.0071 0.2674 1.0000
9.500 0.9950 0.03507 0.02524 0.0113 0.2440 1.0000
9.750 0.9874 0.03641 0.02646 0.0156 0.2233 1.0000
10.000 0.9801 0.03806 0.02800 0.0192 0.2033 1.0000
10.250 0.9730 0.04002 0.02991 0.0221 0.1835 1.0000
10.500 0.9666 0.04220 0.03199 0.0245 0.1662 1.0000
10.750 0.9618 0.04449 0.03420 0.0265 0.1516 1.0000
11.000 0.9580 0.04689 0.03653 0.0281 0.1388 1.0000
11.250 0.9552 0.04932 0.03889 0.0295 0.1282 1.0000
11.500 0.9542 0.05167 0.04118 0.0308 0.1200 1.0000
11.750 0.9555 0.05399 0.04354 0.0319 0.1119 1.0000
12.250 0.9596 0.05862 0.04820 0.0339 0.0992 1.0000
12.500 0.9641 0.06072 0.05028 0.0349 0.0943 1.0000
12.750 0.9695 0.06298 0.05267 0.0359 0.0898 1.0000
13.000 0.9730 0.06545 0.05527 0.0365 0.0853 1.0000
13.250 0.9816 0.06731 0.05706 0.0375 0.0814 1.0000
13.500 0.9861 0.07001 0.05996 0.0382 0.0784 1.0000
13.750 0.9846 0.07341 0.06363 0.0383 0.0758 1.0000
14.000 0.9820 0.07688 0.06729 0.0381 0.0732 1.0000
14.250 0.9828 0.07984 0.07031 0.0382 0.0706 1.0000
14.500 0.9896 0.08232 0.07281 0.0387 0.0682 1.0000
14.750 0.9745 0.08774 0.07853 0.0372 0.0675 1.0000
15.000 0.9543 0.09416 0.08522 0.0348 0.0669 1.0000
15.250 0.9295 0.10178 0.09309 0.0315 0.0666 1.0000
15.500 0.9009 0.11084 0.10234 0.0271 0.0668 1.0000
15.750 0.8649 0.12244 0.11411 0.0211 0.0672 1.0000
16.000 0.8243 0.13676 0.12850 0.0136 0.0675 1.0000
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