NACA-M1 AIRFOIL (m1-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA-M1 AIRFOIL (m1-il) Reynolds number: 1,000,000 Max Cl/Cd: 56.01 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-m1-il-1000000.txt Download as CSV file: xf-m1-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.8721 0.02331 0.01955 -0.0049 1.0000 0.0076
-8.000 -0.8510 0.02137 0.01733 -0.0043 1.0000 0.0078
-7.750 -0.8348 0.01730 0.01264 -0.0030 1.0000 0.0082
-7.500 -0.8128 0.01537 0.01044 -0.0023 1.0000 0.0088
-7.250 -0.7871 0.01479 0.00979 -0.0021 1.0000 0.0094
-7.000 -0.7610 0.01432 0.00925 -0.0019 1.0000 0.0100
-6.750 -0.7347 0.01390 0.00876 -0.0018 1.0000 0.0108
-6.500 -0.7079 0.01361 0.00842 -0.0016 1.0000 0.0115
-6.250 -0.6835 0.01235 0.00698 -0.0011 1.0000 0.0124
-6.000 -0.6574 0.01175 0.00636 -0.0009 1.0000 0.0136
-5.750 -0.6302 0.01159 0.00618 -0.0009 1.0000 0.0147
-5.500 -0.6031 0.01133 0.00590 -0.0008 1.0000 0.0160
-5.250 -0.5756 0.01125 0.00579 -0.0007 1.0000 0.0170
-5.000 -0.5502 0.01035 0.00483 -0.0004 1.0000 0.0193
-4.750 -0.5229 0.01018 0.00468 -0.0004 1.0000 0.0210
-4.500 -0.4957 0.00995 0.00443 -0.0003 1.0000 0.0229
-4.250 -0.4684 0.00978 0.00424 -0.0002 1.0000 0.0243
-4.000 -0.4405 0.00989 0.00437 -0.0002 1.0000 0.0251
-3.750 -0.4155 0.00878 0.00316 0.0002 1.0000 0.0285
-3.500 -0.3886 0.00846 0.00280 0.0004 1.0000 0.0301
-3.250 -0.3617 0.00820 0.00253 0.0005 1.0000 0.0319
-3.000 -0.3348 0.00795 0.00227 0.0007 1.0000 0.0336
-2.750 -0.3081 0.00774 0.00204 0.0010 1.0000 0.0351
-2.500 -0.2816 0.00759 0.00189 0.0013 1.0000 0.0361
-2.250 -0.2554 0.00737 0.00163 0.0017 1.0000 0.0382
-2.000 -0.2296 0.00720 0.00146 0.0021 1.0000 0.0408
-1.750 -0.2041 0.00705 0.00135 0.0026 1.0000 0.0454
-1.500 -0.1792 0.00665 0.00122 0.0031 1.0000 0.1157
-1.250 -0.1548 0.00584 0.00109 0.0033 1.0000 0.3045
-1.000 -0.1239 0.00506 0.00100 0.0020 0.9981 0.4986
-0.750 -0.0840 0.00434 0.00092 -0.0010 0.9908 0.6799
-0.500 -0.0492 0.00393 0.00091 -0.0025 0.9762 0.7892
-0.250 -0.0212 0.00377 0.00093 -0.0020 0.9381 0.8530
0.000 0.0001 0.00375 0.00093 0.0000 0.8953 0.8944
0.250 0.0213 0.00376 0.00093 0.0020 0.8542 0.9384
0.500 0.0492 0.00393 0.00092 0.0025 0.7892 0.9761
0.750 0.0842 0.00434 0.00092 0.0009 0.6798 0.9911
1.000 0.1244 0.00507 0.00100 -0.0021 0.4974 0.9983
1.250 0.1548 0.00584 0.00109 -0.0033 0.3057 1.0000
1.500 0.1792 0.00662 0.00122 -0.0031 0.1203 1.0000
1.750 0.2041 0.00705 0.00135 -0.0026 0.0454 1.0000
2.000 0.2296 0.00720 0.00146 -0.0021 0.0409 1.0000
2.250 0.2554 0.00737 0.00163 -0.0017 0.0381 1.0000
2.500 0.2816 0.00759 0.00189 -0.0013 0.0361 1.0000
2.750 0.3081 0.00774 0.00204 -0.0010 0.0351 1.0000
3.000 0.3348 0.00795 0.00227 -0.0007 0.0336 1.0000
3.250 0.3617 0.00820 0.00254 -0.0005 0.0319 1.0000
3.500 0.3886 0.00845 0.00280 -0.0004 0.0301 1.0000
3.750 0.4155 0.00878 0.00316 -0.0002 0.0285 1.0000
4.000 0.4405 0.00989 0.00437 0.0002 0.0251 1.0000
4.250 0.4684 0.00978 0.00425 0.0002 0.0243 1.0000
4.500 0.4957 0.00995 0.00443 0.0003 0.0229 1.0000
4.750 0.5229 0.01019 0.00469 0.0004 0.0210 1.0000
5.000 0.5502 0.01035 0.00484 0.0004 0.0193 1.0000
5.250 0.5755 0.01126 0.00581 0.0007 0.0170 1.0000
5.500 0.6031 0.01133 0.00590 0.0008 0.0160 1.0000
5.750 0.6302 0.01158 0.00618 0.0009 0.0147 1.0000
6.000 0.6575 0.01174 0.00635 0.0009 0.0136 1.0000
6.250 0.6835 0.01235 0.00699 0.0011 0.0124 1.0000
6.500 0.7079 0.01363 0.00844 0.0016 0.0115 1.0000
6.750 0.7347 0.01391 0.00877 0.0018 0.0108 1.0000
7.000 0.7610 0.01432 0.00925 0.0019 0.0100 1.0000
7.250 0.7872 0.01477 0.00977 0.0021 0.0093 1.0000
7.500 0.8128 0.01536 0.01043 0.0023 0.0088 1.0000
7.750 0.8347 0.01735 0.01269 0.0030 0.0082 1.0000
8.000 0.8510 0.02139 0.01734 0.0043 0.0078 1.0000
8.250 0.8722 0.02329 0.01953 0.0049 0.0076 1.0000
8.500 0.8831 0.02848 0.02533 0.0063 0.0073 1.0000
10.500 0.7262 0.11837 0.11676 -0.0325 0.0116 1.0000
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Polar data table (+)
Polar graphs
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