NACA M5 AIRFOIL (m5-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA M5 AIRFOIL (m5-il) Reynolds number: 1,000,000 Max Cl/Cd: 86.25 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-m5-il-1000000.txt Download as CSV file: xf-m5-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NACA M5 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.5072 0.13035 0.12890 0.0245 1.0000 0.0147
-11.250 -1.1100 0.03179 0.02902 -0.0032 1.0000 0.0092
-11.000 -1.1098 0.02584 0.02244 -0.0013 1.0000 0.0097
-10.750 -1.0926 0.02371 0.02010 -0.0004 1.0000 0.0102
-10.500 -1.0705 0.02258 0.01885 0.0001 1.0000 0.0106
-10.250 -1.0473 0.02165 0.01779 0.0005 1.0000 0.0111
-10.000 -1.0239 0.02067 0.01668 0.0010 1.0000 0.0116
-9.750 -1.0002 0.01972 0.01557 0.0014 1.0000 0.0121
-9.500 -0.9755 0.01893 0.01464 0.0017 1.0000 0.0124
-9.250 -0.9529 0.01758 0.01314 0.0023 1.0000 0.0135
-9.000 -0.9257 0.01747 0.01306 0.0023 1.0000 0.0143
-8.750 -0.8984 0.01737 0.01293 0.0023 1.0000 0.0151
-8.500 -0.8716 0.01703 0.01253 0.0024 1.0000 0.0158
-8.250 -0.8444 0.01677 0.01220 0.0025 1.0000 0.0163
-8.000 -0.8196 0.01580 0.01113 0.0028 1.0000 0.0176
-7.750 -0.7914 0.01591 0.01129 0.0027 1.0000 0.0183
-7.500 -0.7634 0.01591 0.01129 0.0026 1.0000 0.0192
-7.250 -0.7356 0.01581 0.01115 0.0026 1.0000 0.0201
-7.000 -0.7074 0.01584 0.01115 0.0025 1.0000 0.0209
-6.750 -0.6819 0.01467 0.00981 0.0027 1.0000 0.0221
-6.500 -0.6543 0.01442 0.00956 0.0026 1.0000 0.0230
-6.250 -0.6262 0.01435 0.00950 0.0024 1.0000 0.0238
-6.000 -0.5970 0.01426 0.00939 0.0021 0.9869 0.0248
-5.750 -0.5700 0.01420 0.00925 0.0023 0.9500 0.0258
-5.500 -0.5471 0.01406 0.00901 0.0036 0.9229 0.0266
-5.000 -0.4983 0.01294 0.00754 0.0053 0.8763 0.0282
-4.750 -0.4733 0.01215 0.00661 0.0059 0.8553 0.0295
-4.500 -0.4466 0.01185 0.00623 0.0062 0.8361 0.0303
-4.250 -0.4194 0.01165 0.00595 0.0063 0.8178 0.0313
-4.000 -0.3921 0.01135 0.00555 0.0065 0.8012 0.0323
-3.750 -0.3647 0.01102 0.00513 0.0067 0.7852 0.0332
-3.500 -0.3371 0.01072 0.00474 0.0068 0.7704 0.0340
-3.250 -0.3093 0.01052 0.00446 0.0069 0.7562 0.0348
-3.000 -0.2814 0.01031 0.00418 0.0069 0.7427 0.0353
-2.750 -0.2536 0.01009 0.00389 0.0070 0.7297 0.0356
-2.500 -0.2268 0.00947 0.00316 0.0072 0.7175 0.0367
-2.250 -0.1994 0.00909 0.00270 0.0073 0.7055 0.0384
-2.000 -0.1713 0.00889 0.00247 0.0073 0.6936 0.0401
-1.750 -0.1430 0.00875 0.00230 0.0073 0.6824 0.0419
-1.500 -0.1147 0.00864 0.00215 0.0072 0.6719 0.0439
-1.250 -0.0863 0.00855 0.00201 0.0071 0.6616 0.0453
-1.000 -0.0580 0.00838 0.00180 0.0071 0.6514 0.0482
-0.750 -0.0296 0.00823 0.00165 0.0070 0.6418 0.0544
-0.500 -0.0012 0.00815 0.00153 0.0069 0.6324 0.0617
-0.250 0.0272 0.00800 0.00145 0.0068 0.6230 0.0803
0.000 0.0553 0.00780 0.00140 0.0067 0.6140 0.1312
0.250 0.0830 0.00748 0.00136 0.0065 0.6048 0.2281
0.500 0.0985 0.00530 0.00124 0.0085 0.5969 0.8567
1.000 0.1464 0.00525 0.00137 0.0112 0.5796 0.9681
1.250 0.1785 0.00534 0.00142 0.0104 0.5705 0.9802
1.500 0.2243 0.00552 0.00154 0.0065 0.5603 0.9879
1.750 0.2703 0.00573 0.00171 0.0025 0.5498 0.9936
2.000 0.3323 0.00604 0.00197 -0.0050 0.5379 0.9995
2.250 0.3629 0.00609 0.00197 -0.0057 0.5274 1.0000
2.500 0.3904 0.00612 0.00196 -0.0057 0.5134 1.0000
2.750 0.4178 0.00616 0.00194 -0.0057 0.4969 1.0000
3.000 0.4453 0.00621 0.00194 -0.0057 0.4800 1.0000
3.250 0.4727 0.00628 0.00196 -0.0057 0.4609 1.0000
3.500 0.4999 0.00637 0.00198 -0.0057 0.4421 1.0000
3.750 0.5268 0.00647 0.00202 -0.0056 0.4204 1.0000
4.000 0.5536 0.00660 0.00208 -0.0055 0.3994 1.0000
4.250 0.5801 0.00680 0.00216 -0.0054 0.3655 1.0000
4.500 0.6064 0.00705 0.00227 -0.0053 0.3289 1.0000
4.750 0.6322 0.00733 0.00241 -0.0051 0.2912 1.0000
5.000 0.6576 0.00779 0.00263 -0.0050 0.2337 1.0000
5.250 0.6822 0.00851 0.00298 -0.0049 0.1548 1.0000
5.500 0.7062 0.00927 0.00340 -0.0047 0.0834 1.0000
5.750 0.7303 0.00983 0.00378 -0.0043 0.0479 1.0000
6.000 0.7547 0.01018 0.00409 -0.0039 0.0366 1.0000
6.250 0.7791 0.01053 0.00441 -0.0033 0.0285 1.0000
6.500 0.8033 0.01096 0.00482 -0.0028 0.0227 1.0000
6.750 0.8278 0.01124 0.00512 -0.0023 0.0205 1.0000
7.000 0.8519 0.01176 0.00565 -0.0018 0.0175 1.0000
7.250 0.8765 0.01210 0.00603 -0.0014 0.0164 1.0000
7.500 0.9010 0.01248 0.00644 -0.0010 0.0153 1.0000
7.750 0.9254 0.01290 0.00688 -0.0006 0.0143 1.0000
8.000 0.9482 0.01372 0.00777 0.0000 0.0130 1.0000
8.250 0.9716 0.01438 0.00851 0.0004 0.0125 1.0000
8.500 0.9959 0.01484 0.00903 0.0008 0.0120 1.0000
8.750 1.0201 0.01533 0.00955 0.0011 0.0113 1.0000
9.000 1.0439 0.01585 0.01011 0.0014 0.0107 1.0000
9.250 1.0670 0.01648 0.01079 0.0018 0.0102 1.0000
9.500 1.0860 0.01772 0.01212 0.0026 0.0096 1.0000
9.750 1.1037 0.01910 0.01362 0.0036 0.0092 1.0000
10.000 1.1255 0.01980 0.01440 0.0041 0.0090 1.0000
10.250 1.1459 0.02067 0.01536 0.0048 0.0087 1.0000
10.500 1.1652 0.02163 0.01641 0.0056 0.0085 1.0000
10.750 1.1835 0.02266 0.01755 0.0064 0.0082 1.0000
11.000 1.2009 0.02373 0.01872 0.0073 0.0080 1.0000
11.250 1.2175 0.02479 0.01988 0.0082 0.0077 1.0000
11.500 1.2330 0.02589 0.02106 0.0092 0.0075 1.0000
11.750 1.2475 0.02692 0.02218 0.0103 0.0073 1.0000
12.000 1.2587 0.02813 0.02346 0.0116 0.0071 1.0000
12.250 1.2599 0.02990 0.02535 0.0139 0.0069 1.0000
12.500 1.2444 0.03381 0.02952 0.0165 0.0067 1.0000
12.750 1.2409 0.03667 0.03260 0.0174 0.0066 1.0000
13.000 1.2439 0.03892 0.03499 0.0174 0.0065 1.0000
13.250 1.2438 0.04174 0.03796 0.0171 0.0064 1.0000
13.500 1.2412 0.04502 0.04140 0.0164 0.0064 1.0000
13.750 1.2350 0.04896 0.04551 0.0152 0.0063 1.0000
14.000 1.2262 0.05340 0.05012 0.0136 0.0063 1.0000
14.250 1.2143 0.05850 0.05539 0.0115 0.0063 1.0000
14.500 1.1996 0.06422 0.06129 0.0088 0.0062 1.0000
14.750 1.1824 0.07062 0.06785 0.0056 0.0062 1.0000
15.000 1.1627 0.07774 0.07514 0.0019 0.0062 1.0000
15.250 1.1404 0.08587 0.08343 -0.0026 0.0063 1.0000
15.500 1.1166 0.09489 0.09260 -0.0077 0.0063 1.0000
15.750 1.0895 0.10515 0.10301 -0.0135 0.0063 1.0000
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