NACA M6 AIRFOIL (m6-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA M6 AIRFOIL (m6-il) Reynolds number: 200,000 Max Cl/Cd: 66.49 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-m6-il-200000.txt Download as CSV file: xf-m6-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA M6 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5560 0.09329 0.08981 -0.0142 1.0000 0.0726
-9.250 -0.5465 0.09065 0.08719 -0.0135 1.0000 0.0737
-9.000 -0.5443 0.08689 0.08345 -0.0153 1.0000 0.0750
-8.750 -0.5501 0.08199 0.07856 -0.0193 1.0000 0.0763
-8.500 -0.5611 0.07738 0.07394 -0.0218 1.0000 0.0779
-8.250 -0.6086 0.07135 0.06738 -0.0260 1.0000 0.0829
-8.000 -0.6102 0.06484 0.06082 -0.0260 1.0000 0.0840
-7.750 -0.5936 0.06159 0.05768 -0.0257 1.0000 0.0851
-7.500 -0.5799 0.05908 0.05519 -0.0251 1.0000 0.0864
-7.250 -0.5681 0.05659 0.05267 -0.0244 1.0000 0.0883
-7.000 -0.5768 0.05648 0.05179 -0.0212 1.0000 0.0965
-6.750 -0.5756 0.05030 0.04584 -0.0198 1.0000 0.0981
-6.500 -0.5563 0.04784 0.04348 -0.0201 0.9957 0.0998
-6.250 -0.5228 0.04498 0.04053 -0.0230 0.9874 0.1034
-6.000 -0.5107 0.03016 0.02333 -0.0201 0.9733 0.0603
-5.750 -0.4767 0.02788 0.02074 -0.0216 0.9622 0.0602
-5.500 -0.4446 0.02541 0.01798 -0.0226 0.9500 0.0600
-5.250 -0.4152 0.02339 0.01571 -0.0229 0.9363 0.0597
-5.000 -0.3891 0.02199 0.01408 -0.0221 0.9213 0.0598
-4.750 -0.3649 0.02093 0.01281 -0.0209 0.9062 0.0600
-4.500 -0.3411 0.01995 0.01166 -0.0197 0.8920 0.0603
-4.250 -0.3168 0.01865 0.01029 -0.0187 0.8778 0.0615
-4.000 -0.2925 0.01791 0.00954 -0.0178 0.8642 0.0634
-3.750 -0.2678 0.01732 0.00891 -0.0169 0.8515 0.0652
-3.500 -0.2432 0.01672 0.00825 -0.0159 0.8400 0.0668
-3.250 -0.2184 0.01618 0.00763 -0.0150 0.8284 0.0687
-3.000 -0.1931 0.01574 0.00711 -0.0142 0.8166 0.0708
-2.750 -0.1698 0.01505 0.00646 -0.0131 0.8064 0.0747
-2.500 -0.1451 0.01467 0.00605 -0.0123 0.7959 0.0807
-2.250 -0.1207 0.01419 0.00562 -0.0115 0.7854 0.0924
-2.000 -0.0989 0.01340 0.00514 -0.0101 0.7768 0.1581
-1.750 -0.0788 0.01249 0.00487 -0.0089 0.7662 0.2993
-1.500 -0.0711 0.01047 0.00490 -0.0043 0.7583 0.7837
-1.250 -0.0179 0.01117 0.00572 -0.0073 0.7487 0.9168
-1.000 0.0448 0.01209 0.00645 -0.0127 0.7397 0.9535
-0.750 0.1235 0.01274 0.00690 -0.0222 0.7299 0.9797
-0.500 0.2095 0.01279 0.00678 -0.0340 0.7191 1.0000
0.000 0.2599 0.01267 0.00645 -0.0334 0.7005 1.0000
0.250 0.2851 0.01264 0.00631 -0.0331 0.6922 1.0000
0.500 0.3107 0.01260 0.00621 -0.0328 0.6826 1.0000
0.750 0.3361 0.01259 0.00612 -0.0325 0.6740 1.0000
1.000 0.3616 0.01257 0.00604 -0.0322 0.6650 1.0000
1.250 0.3872 0.01258 0.00599 -0.0320 0.6562 1.0000
1.500 0.4127 0.01258 0.00592 -0.0316 0.6475 1.0000
1.750 0.4384 0.01260 0.00591 -0.0314 0.6384 1.0000
2.000 0.4638 0.01262 0.00586 -0.0309 0.6301 1.0000
2.250 0.4895 0.01264 0.00589 -0.0307 0.6205 1.0000
2.500 0.5149 0.01268 0.00583 -0.0302 0.6125 1.0000
2.750 0.5405 0.01270 0.00588 -0.0300 0.6021 1.0000
3.000 0.5659 0.01274 0.00588 -0.0295 0.5931 1.0000
3.250 0.5913 0.01277 0.00589 -0.0291 0.5829 1.0000
3.500 0.6166 0.01282 0.00594 -0.0287 0.5729 1.0000
3.750 0.6419 0.01287 0.00594 -0.0282 0.5641 1.0000
4.000 0.6670 0.01294 0.00606 -0.0278 0.5535 1.0000
4.250 0.6920 0.01302 0.00612 -0.0273 0.5445 1.0000
4.500 0.7168 0.01310 0.00622 -0.0268 0.5345 1.0000
4.750 0.7413 0.01320 0.00635 -0.0262 0.5240 1.0000
5.000 0.7657 0.01328 0.00640 -0.0256 0.5132 1.0000
5.250 0.7898 0.01335 0.00649 -0.0249 0.5009 1.0000
5.500 0.8136 0.01345 0.00663 -0.0242 0.4880 1.0000
5.750 0.8373 0.01355 0.00675 -0.0234 0.4744 1.0000
6.000 0.8603 0.01364 0.00685 -0.0225 0.4584 1.0000
6.250 0.8828 0.01374 0.00692 -0.0215 0.4394 1.0000
6.500 0.9050 0.01390 0.00703 -0.0205 0.4203 1.0000
6.750 0.9272 0.01409 0.00725 -0.0196 0.4016 1.0000
7.000 0.9490 0.01431 0.00750 -0.0186 0.3819 1.0000
7.250 0.9701 0.01459 0.00776 -0.0175 0.3608 1.0000
7.500 0.9906 0.01492 0.00807 -0.0163 0.3374 1.0000
7.750 1.0096 0.01535 0.00843 -0.0150 0.3106 1.0000
8.000 1.0275 0.01586 0.00887 -0.0135 0.2790 1.0000
8.250 1.0432 0.01655 0.00941 -0.0118 0.2404 1.0000
8.500 1.0540 0.01760 0.01018 -0.0094 0.1907 1.0000
8.750 1.0588 0.01910 0.01128 -0.0064 0.1294 1.0000
9.000 1.0623 0.02059 0.01250 -0.0030 0.0985 1.0000
9.250 1.0669 0.02186 0.01369 0.0002 0.0859 1.0000
9.500 1.0707 0.02308 0.01489 0.0036 0.0784 1.0000
9.750 1.0747 0.02421 0.01603 0.0068 0.0730 1.0000
10.000 1.0734 0.02551 0.01732 0.0107 0.0693 1.0000
10.250 1.0785 0.02653 0.01842 0.0136 0.0655 1.0000
10.500 1.0827 0.02780 0.01971 0.0160 0.0623 1.0000
10.750 1.0852 0.02953 0.02138 0.0183 0.0596 1.0000
11.000 1.0951 0.03074 0.02273 0.0199 0.0571 1.0000
11.250 1.1043 0.03209 0.02413 0.0212 0.0546 1.0000
11.500 1.1129 0.03356 0.02558 0.0225 0.0523 1.0000
11.750 1.1239 0.03520 0.02721 0.0239 0.0501 1.0000
12.000 1.1352 0.03661 0.02877 0.0250 0.0484 1.0000
12.250 1.1464 0.03810 0.03034 0.0261 0.0466 1.0000
12.500 1.1574 0.03960 0.03187 0.0270 0.0450 1.0000
12.750 1.1751 0.04125 0.03344 0.0280 0.0430 1.0000
13.000 1.1831 0.04310 0.03549 0.0290 0.0419 1.0000
13.250 1.1906 0.04502 0.03759 0.0299 0.0408 1.0000
13.500 1.1987 0.04704 0.03978 0.0308 0.0397 1.0000
13.750 1.2062 0.04912 0.04199 0.0315 0.0388 1.0000
14.000 1.2119 0.05128 0.04427 0.0321 0.0379 1.0000
14.250 1.2206 0.05335 0.04637 0.0326 0.0369 1.0000
14.500 1.2318 0.05646 0.04956 0.0335 0.0358 1.0000
14.750 1.2220 0.05964 0.05301 0.0337 0.0355 1.0000
15.000 1.2116 0.06324 0.05687 0.0335 0.0351 1.0000
15.250 1.1999 0.06725 0.06113 0.0330 0.0348 1.0000
15.500 1.1864 0.07171 0.06584 0.0321 0.0346 1.0000
15.750 1.1705 0.07665 0.07102 0.0308 0.0345 1.0000
16.000 1.1520 0.08214 0.07675 0.0290 0.0344 1.0000
16.250 1.1314 0.08826 0.08309 0.0265 0.0344 1.0000
16.500 1.1087 0.09512 0.09018 0.0233 0.0345 1.0000
16.750 1.0839 0.10283 0.09810 0.0193 0.0347 1.0000
17.000 1.0568 0.11148 0.10695 0.0144 0.0349 1.0000
17.250 1.0279 0.12116 0.11680 0.0087 0.0352 1.0000
17.500 0.9986 0.13171 0.12750 0.0023 0.0356 1.0000
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