NACA M6 AIRFOIL (m6-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA M6 AIRFOIL (m6-il) Reynolds number: 500,000 Max Cl/Cd: 87.41 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-m6-il-500000.txt Download as CSV file: xf-m6-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.6036 0.09478 0.09252 -0.0095 1.0000 0.0368
-10.250 -0.6006 0.09163 0.08938 -0.0104 1.0000 0.0371
-10.000 -0.5987 0.08807 0.08584 -0.0121 1.0000 0.0374
-9.750 -0.6001 0.08358 0.08136 -0.0153 1.0000 0.0377
-9.500 -0.6133 0.07662 0.07440 -0.0222 1.0000 0.0380
-9.250 -0.6271 0.07147 0.06920 -0.0245 1.0000 0.0382
-9.000 -0.6371 0.06724 0.06491 -0.0249 1.0000 0.0387
-8.750 -0.6414 0.06286 0.06044 -0.0254 1.0000 0.0395
-8.500 -0.6975 0.04827 0.04495 -0.0237 1.0000 0.0438
-8.250 -0.6805 0.04619 0.04292 -0.0233 1.0000 0.0442
-8.000 -0.6636 0.04469 0.04144 -0.0228 1.0000 0.0447
-7.750 -0.6467 0.04330 0.04003 -0.0222 1.0000 0.0454
-7.500 -0.6704 0.02803 0.02292 -0.0162 0.9778 0.0368
-7.250 -0.6416 0.02695 0.02163 -0.0166 0.9589 0.0365
-7.000 -0.6212 0.02506 0.01946 -0.0153 0.9380 0.0365
-6.750 -0.6024 0.02345 0.01760 -0.0135 0.9179 0.0365
-6.500 -0.5816 0.02229 0.01623 -0.0120 0.9001 0.0364
-6.250 -0.5598 0.02071 0.01442 -0.0108 0.8839 0.0363
-6.000 -0.5365 0.01965 0.01316 -0.0098 0.8684 0.0364
-5.750 -0.5125 0.01826 0.01158 -0.0090 0.8538 0.0365
-5.500 -0.4877 0.01695 0.01011 -0.0083 0.8396 0.0367
-5.250 -0.4627 0.01582 0.00887 -0.0077 0.8259 0.0373
-5.000 -0.4371 0.01509 0.00809 -0.0073 0.8120 0.0380
-4.750 -0.4112 0.01451 0.00743 -0.0068 0.7987 0.0385
-4.500 -0.3852 0.01399 0.00683 -0.0064 0.7863 0.0390
-4.250 -0.3592 0.01353 0.00629 -0.0059 0.7747 0.0395
-4.000 -0.3330 0.01310 0.00580 -0.0055 0.7631 0.0401
-3.750 -0.3067 0.01271 0.00535 -0.0051 0.7523 0.0407
-3.500 -0.2805 0.01237 0.00493 -0.0047 0.7423 0.0414
-3.250 -0.2539 0.01205 0.00456 -0.0043 0.7321 0.0422
-3.000 -0.2271 0.01180 0.00425 -0.0040 0.7229 0.0430
-2.750 -0.2012 0.01140 0.00381 -0.0036 0.7137 0.0447
-2.500 -0.1743 0.01113 0.00353 -0.0033 0.7050 0.0466
-2.250 -0.1472 0.01094 0.00329 -0.0031 0.6964 0.0486
-1.750 -0.0927 0.01055 0.00287 -0.0027 0.6800 0.0585
-1.500 -0.0665 0.01017 0.00269 -0.0024 0.6721 0.1004
-1.250 -0.0408 0.00980 0.00257 -0.0020 0.6642 0.1723
-1.000 -0.0157 0.00936 0.00246 -0.0017 0.6568 0.2632
-0.750 0.0032 0.00830 0.00225 -0.0003 0.6492 0.5021
-0.500 0.0131 0.00704 0.00233 0.0040 0.6428 0.8593
-0.250 0.0417 0.00713 0.00249 0.0045 0.6349 0.9080
0.000 0.0720 0.00734 0.00265 0.0045 0.6278 0.9313
0.250 0.1047 0.00757 0.00286 0.0040 0.6197 0.9477
0.500 0.1387 0.00785 0.00303 0.0031 0.6124 0.9583
0.750 0.1920 0.00821 0.00336 -0.0020 0.6036 0.9657
1.000 0.2425 0.00857 0.00362 -0.0065 0.5954 0.9732
1.250 0.2940 0.00891 0.00393 -0.0112 0.5862 0.9829
1.500 0.3442 0.00902 0.00396 -0.0160 0.5776 0.9864
1.750 0.3832 0.00904 0.00395 -0.0185 0.5683 0.9895
2.000 0.4202 0.00910 0.00396 -0.0205 0.5594 0.9933
2.250 0.4558 0.00909 0.00390 -0.0223 0.5494 0.9948
2.500 0.4898 0.00906 0.00385 -0.0237 0.5391 0.9961
2.750 0.5234 0.00907 0.00381 -0.0251 0.5298 0.9975
3.000 0.5567 0.00907 0.00379 -0.0265 0.5200 0.9989
3.250 0.5888 0.00909 0.00379 -0.0275 0.5114 1.0000
3.500 0.6147 0.00911 0.00379 -0.0273 0.5023 1.0000
3.750 0.6406 0.00913 0.00381 -0.0271 0.4918 1.0000
4.000 0.6664 0.00919 0.00382 -0.0268 0.4815 1.0000
4.250 0.6922 0.00922 0.00386 -0.0266 0.4715 1.0000
4.500 0.7179 0.00928 0.00391 -0.0263 0.4603 1.0000
4.750 0.7435 0.00936 0.00395 -0.0260 0.4469 1.0000
5.000 0.7689 0.00945 0.00401 -0.0257 0.4330 1.0000
5.250 0.7942 0.00956 0.00409 -0.0254 0.4175 1.0000
5.500 0.8193 0.00969 0.00418 -0.0250 0.3998 1.0000
5.750 0.8442 0.00984 0.00429 -0.0247 0.3817 1.0000
6.000 0.8689 0.01002 0.00443 -0.0243 0.3630 1.0000
6.500 0.9169 0.01049 0.00478 -0.0233 0.3197 1.0000
6.750 0.9397 0.01082 0.00501 -0.0226 0.2949 1.0000
7.000 0.9617 0.01121 0.00529 -0.0218 0.2662 1.0000
7.250 0.9827 0.01168 0.00562 -0.0209 0.2358 1.0000
7.500 1.0028 0.01221 0.00601 -0.0199 0.2044 1.0000
7.750 1.0217 0.01283 0.00646 -0.0187 0.1702 1.0000
8.000 1.0380 0.01364 0.00703 -0.0171 0.1262 1.0000
8.250 1.0514 0.01465 0.00776 -0.0151 0.0860 1.0000
8.500 1.0665 0.01540 0.00842 -0.0132 0.0685 1.0000
8.750 1.0820 0.01605 0.00903 -0.0114 0.0580 1.0000
9.000 1.0966 0.01671 0.00965 -0.0093 0.0513 1.0000
9.250 1.1126 0.01722 0.01019 -0.0075 0.0474 1.0000
9.500 1.1256 0.01789 0.01085 -0.0052 0.0438 1.0000
9.750 1.1388 0.01851 0.01152 -0.0030 0.0414 1.0000
10.000 1.1520 0.01909 0.01215 -0.0008 0.0394 1.0000
10.250 1.1618 0.01983 0.01291 0.0019 0.0375 1.0000
10.500 1.1654 0.02084 0.01395 0.0053 0.0357 1.0000
10.750 1.1738 0.02145 0.01463 0.0082 0.0345 1.0000
11.000 1.1798 0.02223 0.01547 0.0111 0.0332 1.0000
11.250 1.1864 0.02322 0.01651 0.0134 0.0320 1.0000
11.500 1.1900 0.02461 0.01794 0.0155 0.0309 1.0000
11.750 1.1892 0.02655 0.01994 0.0174 0.0299 1.0000
12.000 1.1999 0.02777 0.02126 0.0183 0.0291 1.0000
12.250 1.2087 0.02923 0.02280 0.0191 0.0282 1.0000
12.500 1.2167 0.03082 0.02445 0.0198 0.0273 1.0000
12.750 1.2236 0.03257 0.02625 0.0203 0.0265 1.0000
13.000 1.2272 0.03468 0.02840 0.0208 0.0257 1.0000
13.250 1.2239 0.03744 0.03122 0.0217 0.0250 1.0000
13.500 1.2324 0.03921 0.03309 0.0219 0.0245 1.0000
13.750 1.2384 0.04123 0.03521 0.0221 0.0239 1.0000
14.000 1.2433 0.04338 0.03745 0.0222 0.0233 1.0000
14.250 1.2475 0.04563 0.03978 0.0223 0.0227 1.0000
14.500 1.2509 0.04797 0.04219 0.0223 0.0222 1.0000
14.750 1.2537 0.05041 0.04468 0.0222 0.0218 1.0000
15.000 1.2551 0.05298 0.04729 0.0222 0.0214 1.0000
15.250 1.2537 0.05571 0.05006 0.0226 0.0209 1.0000
15.500 1.2545 0.05848 0.05294 0.0225 0.0205 1.0000
15.750 1.2563 0.06135 0.05594 0.0219 0.0201 1.0000
16.000 1.2573 0.06434 0.05905 0.0212 0.0197 1.0000
16.250 1.2577 0.06744 0.06226 0.0205 0.0194 1.0000
16.500 1.2575 0.07070 0.06562 0.0197 0.0190 1.0000
16.750 1.2568 0.07404 0.06906 0.0188 0.0187 1.0000
17.000 1.2557 0.07750 0.07260 0.0178 0.0184 1.0000
17.250 1.2543 0.08104 0.07623 0.0166 0.0181 1.0000
17.500 1.2529 0.08463 0.07989 0.0155 0.0179 1.0000
17.750 1.2512 0.08823 0.08355 0.0143 0.0176 1.0000
18.000 1.2485 0.09190 0.08728 0.0133 0.0174 1.0000
18.250 1.2422 0.09585 0.09133 0.0126 0.0170 1.0000
18.500 1.2341 0.10084 0.09647 0.0105 0.0169 1.0000
18.750 1.2255 0.10607 0.10186 0.0080 0.0168 1.0000
19.000 1.2155 0.11159 0.10753 0.0054 0.0167 1.0000
19.250 1.2043 0.11747 0.11357 0.0024 0.0166 1.0000
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