NACA-M1 AIRFOIL (m1-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA-M1 AIRFOIL (m1-il) Reynolds number: 500,000 Max Cl/Cd: 38.22 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-m1-il-500000.txt Download as CSV file: xf-m1-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NACA-M1 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.7270 0.09127 0.08911 0.0135 1.0000 0.0174
-9.000 -0.7362 0.08327 0.08114 0.0067 1.0000 0.0175
-8.750 -0.7420 0.07567 0.07349 -0.0012 1.0000 0.0175
-8.500 -0.7527 0.06820 0.06589 -0.0052 1.0000 0.0177
-8.250 -0.7582 0.06189 0.05944 -0.0074 1.0000 0.0179
-8.000 -0.7551 0.05764 0.05508 -0.0082 1.0000 0.0183
-7.750 -0.7470 0.05431 0.05164 -0.0086 1.0000 0.0187
-7.500 -0.7365 0.05091 0.04810 -0.0090 1.0000 0.0193
-7.250 -0.7332 0.04063 0.03724 -0.0086 1.0000 0.0160
-7.000 -0.7243 0.03406 0.03018 -0.0077 1.0000 0.0153
-6.750 -0.7080 0.02921 0.02481 -0.0065 1.0000 0.0160
-6.500 -0.6889 0.02522 0.02030 -0.0054 1.0000 0.0164
-6.250 -0.6657 0.02304 0.01773 -0.0045 1.0000 0.0170
-6.000 -0.6454 0.01879 0.01294 -0.0036 1.0000 0.0181
-5.750 -0.6207 0.01756 0.01160 -0.0033 1.0000 0.0193
-5.500 -0.5947 0.01696 0.01094 -0.0031 1.0000 0.0209
-5.250 -0.5683 0.01638 0.01025 -0.0028 1.0000 0.0231
-5.000 -0.5416 0.01578 0.00952 -0.0025 1.0000 0.0246
-4.750 -0.5171 0.01372 0.00728 -0.0018 1.0000 0.0268
-4.500 -0.4915 0.01286 0.00640 -0.0015 1.0000 0.0297
-4.250 -0.4652 0.01234 0.00585 -0.0013 1.0000 0.0326
-4.000 -0.4389 0.01178 0.00523 -0.0009 1.0000 0.0348
-3.750 -0.4121 0.01147 0.00487 -0.0007 1.0000 0.0361
-3.500 -0.3874 0.01037 0.00371 -0.0002 1.0000 0.0395
-3.250 -0.3611 0.00989 0.00321 0.0001 1.0000 0.0418
-3.000 -0.3347 0.00953 0.00282 0.0004 1.0000 0.0445
-2.750 -0.3082 0.00924 0.00251 0.0007 1.0000 0.0474
-2.500 -0.2819 0.00894 0.00218 0.0011 1.0000 0.0501
-2.250 -0.2557 0.00866 0.00192 0.0014 1.0000 0.0568
-2.000 -0.2303 0.00812 0.00167 0.0018 1.0000 0.1226
-1.750 -0.2076 0.00681 0.00143 0.0020 1.0000 0.4012
-1.500 -0.1851 0.00586 0.00135 0.0026 1.0000 0.6206
-1.250 -0.1626 0.00533 0.00136 0.0039 1.0000 0.7594
-1.000 -0.1407 0.00506 0.00143 0.0056 1.0000 0.8502
-0.750 -0.1188 0.00497 0.00152 0.0074 1.0000 0.9143
-0.500 -0.0846 0.00501 0.00163 0.0064 1.0000 0.9700
-0.250 -0.0360 0.00507 0.00168 0.0019 1.0000 0.9945
0.000 0.0000 0.00509 0.00170 0.0000 1.0000 1.0000
0.250 0.0358 0.00507 0.00168 -0.0019 0.9946 1.0000
0.500 0.0847 0.00501 0.00163 -0.0065 0.9699 1.0000
0.750 0.1189 0.00497 0.00152 -0.0074 0.9149 1.0000
1.000 0.1408 0.00506 0.00143 -0.0056 0.8504 1.0000
1.250 0.1627 0.00533 0.00136 -0.0039 0.7597 1.0000
1.500 0.1851 0.00586 0.00135 -0.0027 0.6212 1.0000
1.750 0.2076 0.00681 0.00143 -0.0020 0.4007 1.0000
2.000 0.2304 0.00811 0.00167 -0.0018 0.1256 1.0000
2.250 0.2557 0.00866 0.00192 -0.0014 0.0568 1.0000
2.500 0.2819 0.00894 0.00218 -0.0011 0.0501 1.0000
2.750 0.3082 0.00924 0.00251 -0.0007 0.0474 1.0000
3.000 0.3347 0.00953 0.00282 -0.0004 0.0445 1.0000
3.250 0.3612 0.00990 0.00321 -0.0001 0.0418 1.0000
3.500 0.3874 0.01037 0.00371 0.0002 0.0395 1.0000
3.750 0.4121 0.01146 0.00487 0.0007 0.0361 1.0000
4.000 0.4389 0.01177 0.00522 0.0009 0.0348 1.0000
4.250 0.4652 0.01235 0.00585 0.0013 0.0327 1.0000
4.500 0.4915 0.01286 0.00640 0.0015 0.0297 1.0000
4.750 0.5172 0.01370 0.00726 0.0018 0.0269 1.0000
5.000 0.5416 0.01578 0.00952 0.0024 0.0246 1.0000
5.250 0.5683 0.01639 0.01026 0.0028 0.0231 1.0000
5.500 0.5948 0.01694 0.01091 0.0031 0.0209 1.0000
5.750 0.6207 0.01755 0.01159 0.0033 0.0193 1.0000
6.000 0.6454 0.01880 0.01294 0.0036 0.0180 1.0000
6.250 0.6658 0.02301 0.01769 0.0045 0.0170 1.0000
6.500 0.6889 0.02524 0.02031 0.0054 0.0164 1.0000
6.750 0.7080 0.02926 0.02486 0.0065 0.0160 1.0000
7.000 0.7244 0.03405 0.03016 0.0077 0.0153 1.0000
7.250 0.7332 0.04064 0.03726 0.0085 0.0160 1.0000
9.000 0.7372 0.08322 0.08109 -0.0068 0.0176 1.0000
12.250 0.5778 0.13904 0.13685 -0.0223 0.0171 1.0000
12.500 0.5782 0.14262 0.14042 -0.0236 0.0171 1.0000
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Polar data table (+)
Polar graphs
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