NACA M6 AIRFOIL (m6-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA M6 AIRFOIL (m6-il) Reynolds number: 1,000,000 Max Cl/Cd: 83.65 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-m6-il-1000000-n5.txt Download as CSV file: xf-m6-il-1000000-n5.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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -1.2580 0.04553 0.04266 -0.0404 1.0000 0.0171
-15.500 -1.2666 0.04221 0.03922 -0.0404 1.0000 0.0172
-15.250 -1.2710 0.03967 0.03657 -0.0394 1.0000 0.0173
-15.000 -1.2691 0.03790 0.03470 -0.0381 1.0000 0.0174
-14.750 -1.2629 0.03661 0.03334 -0.0366 1.0000 0.0175
-14.500 -1.2556 0.03547 0.03214 -0.0349 1.0000 0.0176
-14.250 -1.2479 0.03442 0.03102 -0.0330 1.0000 0.0177
-14.000 -1.2404 0.03339 0.02992 -0.0309 1.0000 0.0178
-13.750 -1.2320 0.03248 0.02893 -0.0286 1.0000 0.0179
-13.500 -1.2221 0.03162 0.02801 -0.0264 1.0000 0.0181
-13.250 -1.2074 0.03089 0.02721 -0.0249 1.0000 0.0182
-13.000 -1.1926 0.03005 0.02628 -0.0235 1.0000 0.0184
-12.750 -1.1772 0.02917 0.02531 -0.0220 1.0000 0.0186
-12.500 -1.1617 0.02819 0.02424 -0.0206 1.0000 0.0188
-12.250 -1.1453 0.02723 0.02317 -0.0193 1.0000 0.0190
-12.000 -1.1276 0.02634 0.02218 -0.0181 1.0000 0.0192
-11.750 -1.1091 0.02548 0.02120 -0.0170 1.0000 0.0195
-11.500 -1.0903 0.02456 0.02017 -0.0159 1.0000 0.0197
-11.250 -1.0710 0.02365 0.01914 -0.0149 1.0000 0.0199
-11.000 -1.0507 0.02280 0.01818 -0.0139 1.0000 0.0201
-10.750 -1.0293 0.02207 0.01735 -0.0131 1.0000 0.0202
-10.500 -1.0068 0.02146 0.01665 -0.0124 1.0000 0.0204
-10.250 -0.9791 0.02088 0.01597 -0.0128 0.9597 0.0205
-10.000 -0.9584 0.02036 0.01530 -0.0115 0.9289 0.0206
-9.750 -0.9389 0.01959 0.01437 -0.0101 0.9074 0.0208
-9.500 -0.9196 0.01853 0.01315 -0.0087 0.8900 0.0211
-9.250 -0.8975 0.01786 0.01237 -0.0078 0.8741 0.0213
-9.000 -0.8743 0.01732 0.01173 -0.0071 0.8589 0.0214
-8.750 -0.8503 0.01686 0.01117 -0.0064 0.8440 0.0216
-8.500 -0.8257 0.01646 0.01069 -0.0059 0.8288 0.0218
-8.250 -0.8007 0.01610 0.01024 -0.0054 0.8133 0.0220
-8.000 -0.7755 0.01571 0.00976 -0.0049 0.7979 0.0223
-7.500 -0.7248 0.01488 0.00874 -0.0041 0.7685 0.0226
-7.250 -0.6990 0.01449 0.00826 -0.0037 0.7552 0.0228
-7.000 -0.6732 0.01411 0.00779 -0.0034 0.7426 0.0230
-6.750 -0.6471 0.01374 0.00734 -0.0031 0.7309 0.0232
-6.500 -0.6209 0.01339 0.00691 -0.0028 0.7196 0.0234
-6.250 -0.5945 0.01305 0.00651 -0.0025 0.7096 0.0236
-5.750 -0.5413 0.01243 0.00575 -0.0020 0.6904 0.0241
-5.500 -0.5145 0.01215 0.00541 -0.0018 0.6817 0.0243
-5.250 -0.4875 0.01188 0.00509 -0.0016 0.6731 0.0245
-5.000 -0.4603 0.01166 0.00482 -0.0015 0.6650 0.0247
-4.750 -0.4329 0.01145 0.00457 -0.0014 0.6569 0.0250
-4.500 -0.4054 0.01127 0.00434 -0.0013 0.6492 0.0251
-4.250 -0.3784 0.01098 0.00401 -0.0011 0.6418 0.0254
-3.750 -0.3242 0.01043 0.00339 -0.0007 0.6273 0.0262
-3.500 -0.2966 0.01024 0.00316 -0.0007 0.6200 0.0266
-3.250 -0.2689 0.01007 0.00297 -0.0006 0.6134 0.0270
-3.000 -0.2410 0.00991 0.00279 -0.0006 0.6062 0.0274
-2.750 -0.2132 0.00977 0.00262 -0.0006 0.5997 0.0278
-2.500 -0.1851 0.00964 0.00247 -0.0006 0.5928 0.0283
-2.250 -0.1571 0.00953 0.00233 -0.0006 0.5859 0.0288
-2.000 -0.1289 0.00941 0.00220 -0.0006 0.5796 0.0293
-1.750 -0.1007 0.00931 0.00208 -0.0006 0.5724 0.0298
-1.500 -0.0724 0.00923 0.00198 -0.0007 0.5660 0.0303
-1.250 -0.0441 0.00914 0.00187 -0.0007 0.5591 0.0314
-1.000 -0.0160 0.00906 0.00178 -0.0008 0.5521 0.0334
-0.750 0.0124 0.00897 0.00170 -0.0009 0.5456 0.0355
-0.500 0.0406 0.00889 0.00163 -0.0009 0.5382 0.0414
-0.250 0.0682 0.00870 0.00156 -0.0009 0.5316 0.0754
0.000 0.0961 0.00859 0.00152 -0.0009 0.5241 0.0999
0.250 0.1238 0.00844 0.00148 -0.0009 0.5172 0.1386
0.500 0.1517 0.00832 0.00146 -0.0010 0.5096 0.1714
0.750 0.1792 0.00816 0.00143 -0.0010 0.5022 0.2240
1.000 0.2054 0.00784 0.00141 -0.0009 0.4944 0.3280
1.250 0.2163 0.00615 0.00128 0.0022 0.4877 0.7953
1.500 0.2405 0.00598 0.00137 0.0033 0.4797 0.8757
1.750 0.2673 0.00601 0.00145 0.0037 0.4707 0.9078
2.000 0.2948 0.00610 0.00153 0.0040 0.4595 0.9264
2.250 0.3224 0.00621 0.00162 0.0042 0.4471 0.9401
2.500 0.3499 0.00634 0.00173 0.0044 0.4371 0.9533
2.750 0.3779 0.00646 0.00183 0.0045 0.4286 0.9613
3.000 0.4079 0.00656 0.00190 0.0041 0.4209 0.9643
3.250 0.4370 0.00670 0.00198 0.0038 0.4090 0.9681
3.500 0.4639 0.00682 0.00206 0.0040 0.3953 0.9720
3.750 0.4949 0.00693 0.00213 0.0033 0.3858 0.9731
4.000 0.5257 0.00705 0.00222 0.0025 0.3764 0.9742
4.250 0.5565 0.00719 0.00232 0.0018 0.3642 0.9754
4.500 0.5867 0.00738 0.00243 0.0011 0.3456 0.9767
4.750 0.6162 0.00762 0.00257 0.0005 0.3202 0.9782
5.000 0.6453 0.00787 0.00272 0.0000 0.2988 0.9799
5.250 0.6736 0.00808 0.00287 -0.0003 0.2817 0.9818
5.500 0.7008 0.00839 0.00306 -0.0004 0.2556 0.9837
5.750 0.7311 0.00874 0.00328 -0.0013 0.2277 0.9843
6.000 0.7614 0.00911 0.00352 -0.0023 0.2018 0.9850
6.250 0.7914 0.00950 0.00379 -0.0031 0.1775 0.9857
6.500 0.8214 0.00982 0.00404 -0.0040 0.1589 0.9865
6.750 0.8504 0.01023 0.00433 -0.0047 0.1368 0.9875
7.000 0.8776 0.01084 0.00475 -0.0052 0.0991 0.9887
7.250 0.9053 0.01131 0.00512 -0.0057 0.0806 0.9899
7.500 0.9333 0.01169 0.00545 -0.0061 0.0699 0.9913
7.750 0.9605 0.01209 0.00579 -0.0064 0.0592 0.9928
8.000 0.9875 0.01250 0.00615 -0.0068 0.0487 0.9940
8.250 1.0161 0.01291 0.00651 -0.0074 0.0413 0.9946
8.500 1.0444 0.01331 0.00689 -0.0080 0.0366 0.9954
8.750 1.0728 0.01366 0.00724 -0.0087 0.0340 0.9963
9.000 1.1009 0.01405 0.00763 -0.0092 0.0316 0.9972
9.250 1.1285 0.01446 0.00804 -0.0098 0.0294 0.9983
9.500 1.1562 0.01482 0.00843 -0.0103 0.0281 0.9992
9.750 1.1831 0.01524 0.00886 -0.0107 0.0265 1.0000
10.000 1.2001 0.01564 0.00927 -0.0090 0.0250 1.0000
10.250 1.2169 0.01601 0.00966 -0.0072 0.0239 1.0000
10.500 1.2336 0.01637 0.01006 -0.0055 0.0230 1.0000
10.750 1.2494 0.01677 0.01048 -0.0036 0.0219 1.0000
11.000 1.2642 0.01722 0.01094 -0.0017 0.0207 1.0000
11.250 1.2784 0.01770 0.01143 0.0003 0.0196 1.0000
11.500 1.2928 0.01814 0.01192 0.0023 0.0187 1.0000
11.750 1.3062 0.01866 0.01246 0.0043 0.0177 1.0000
12.000 1.3153 0.01923 0.01306 0.0070 0.0168 1.0000
12.250 1.3241 0.01994 0.01379 0.0095 0.0160 1.0000
12.500 1.3357 0.02066 0.01456 0.0112 0.0155 1.0000
12.750 1.3474 0.02150 0.01545 0.0126 0.0149 1.0000
13.000 1.3588 0.02246 0.01646 0.0138 0.0142 1.0000
13.250 1.3695 0.02356 0.01760 0.0149 0.0136 1.0000
13.500 1.3793 0.02481 0.01889 0.0158 0.0130 1.0000
13.750 1.3892 0.02613 0.02027 0.0165 0.0125 1.0000
14.000 1.3995 0.02749 0.02169 0.0171 0.0121 1.0000
14.250 1.4086 0.02900 0.02326 0.0175 0.0118 1.0000
14.500 1.4167 0.03067 0.02500 0.0179 0.0114 1.0000
14.750 1.4236 0.03248 0.02688 0.0182 0.0110 1.0000
15.000 1.4292 0.03448 0.02893 0.0184 0.0107 1.0000
15.250 1.4335 0.03666 0.03117 0.0185 0.0104 1.0000
15.500 1.4359 0.03905 0.03364 0.0185 0.0101 1.0000
15.750 1.4383 0.04150 0.03616 0.0185 0.0099 1.0000
16.000 1.4408 0.04397 0.03871 0.0183 0.0097 1.0000
16.250 1.4418 0.04662 0.04145 0.0181 0.0096 1.0000
16.500 1.4418 0.04943 0.04435 0.0178 0.0094 1.0000
16.750 1.4410 0.05243 0.04744 0.0174 0.0092 1.0000
17.000 1.4393 0.05562 0.05071 0.0168 0.0091 1.0000
17.250 1.4365 0.05900 0.05418 0.0161 0.0089 1.0000
17.500 1.4330 0.06259 0.05786 0.0152 0.0088 1.0000
17.750 1.4284 0.06638 0.06173 0.0142 0.0086 1.0000
18.000 1.4227 0.07037 0.06580 0.0131 0.0085 1.0000
18.250 1.4162 0.07457 0.07009 0.0118 0.0083 1.0000
18.500 1.4086 0.07899 0.07460 0.0104 0.0082 1.0000
18.750 1.3997 0.08363 0.07934 0.0088 0.0081 1.0000
19.000 1.3897 0.08854 0.08433 0.0071 0.0080 1.0000
19.250 1.3784 0.09373 0.08962 0.0051 0.0078 1.0000
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