NACA M2 (nacam2-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA M2 (nacam2-il) Reynolds number: 1,000,000 Max Cl/Cd: 70.46 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nacam2-il-1000000-n5.txt Download as CSV file: xf-nacam2-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA M2
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
------ -------- --------- --------- -------- -------- --------
-15.000 -1.2791 0.05164 0.04918 -0.0184 1.0000 0.0034
-14.750 -1.3007 0.04505 0.04237 -0.0224 1.0000 0.0034
-14.500 -1.3149 0.04075 0.03789 -0.0234 1.0000 0.0034
-14.250 -1.3243 0.03765 0.03463 -0.0225 1.0000 0.0034
-14.000 -1.3300 0.03529 0.03211 -0.0204 1.0000 0.0035
-13.750 -1.3328 0.03336 0.03002 -0.0177 1.0000 0.0035
-13.500 -1.3275 0.03156 0.02807 -0.0159 1.0000 0.0036
-13.250 -1.3187 0.02990 0.02624 -0.0144 1.0000 0.0037
-13.000 -1.3071 0.02840 0.02458 -0.0130 1.0000 0.0038
-12.750 -1.2935 0.02700 0.02303 -0.0118 1.0000 0.0039
-12.500 -1.2782 0.02570 0.02158 -0.0106 1.0000 0.0040
-12.250 -1.2615 0.02451 0.02024 -0.0096 1.0000 0.0041
-12.000 -1.2435 0.02340 0.01900 -0.0087 1.0000 0.0042
-11.750 -1.2244 0.02239 0.01785 -0.0079 1.0000 0.0043
-11.500 -1.2043 0.02146 0.01679 -0.0071 1.0000 0.0044
-11.250 -1.1838 0.02054 0.01575 -0.0064 1.0000 0.0045
-11.000 -1.1639 0.01944 0.01452 -0.0056 1.0000 0.0048
-10.750 -1.1424 0.01859 0.01355 -0.0049 1.0000 0.0050
-10.500 -1.1198 0.01785 0.01274 -0.0044 1.0000 0.0053
-10.250 -1.0968 0.01718 0.01199 -0.0039 1.0000 0.0055
-10.000 -1.0732 0.01656 0.01129 -0.0035 1.0000 0.0058
-9.750 -1.0493 0.01598 0.01064 -0.0031 1.0000 0.0061
-9.500 -1.0250 0.01545 0.01002 -0.0027 1.0000 0.0064
-9.250 -1.0010 0.01483 0.00933 -0.0022 1.0000 0.0069
-9.000 -0.9767 0.01425 0.00869 -0.0018 1.0000 0.0075
-8.750 -0.9519 0.01375 0.00813 -0.0015 1.0000 0.0081
-8.500 -0.9268 0.01329 0.00762 -0.0012 1.0000 0.0087
-8.250 -0.9014 0.01288 0.00715 -0.0009 1.0000 0.0092
-8.000 -0.8761 0.01244 0.00668 -0.0006 1.0000 0.0104
-7.750 -0.8504 0.01207 0.00632 -0.0003 1.0000 0.0119
-7.500 -0.8245 0.01174 0.00597 -0.0001 1.0000 0.0133
-7.250 -0.7984 0.01146 0.00571 0.0001 1.0000 0.0155
-7.000 -0.7719 0.01125 0.00551 0.0002 1.0000 0.0175
-6.750 -0.7455 0.01105 0.00530 0.0004 1.0000 0.0187
-6.500 -0.7189 0.01089 0.00512 0.0006 1.0000 0.0194
-6.250 -0.6931 0.01058 0.00478 0.0009 1.0000 0.0207
-6.000 -0.6673 0.01029 0.00447 0.0012 1.0000 0.0221
-5.750 -0.6413 0.01006 0.00425 0.0015 1.0000 0.0233
-5.500 -0.6156 0.00986 0.00404 0.0019 1.0000 0.0245
-5.250 -0.5901 0.00966 0.00382 0.0023 1.0000 0.0256
-5.000 -0.5649 0.00946 0.00361 0.0028 1.0000 0.0266
-4.750 -0.5399 0.00929 0.00342 0.0034 1.0000 0.0275
-4.500 -0.5089 0.00911 0.00323 0.0026 0.9982 0.0280
-4.250 -0.4760 0.00893 0.00305 0.0013 0.9959 0.0284
-4.000 -0.4436 0.00867 0.00275 0.0002 0.9932 0.0294
-3.750 -0.4121 0.00843 0.00248 -0.0006 0.9889 0.0307
-3.500 -0.3797 0.00823 0.00227 -0.0017 0.9849 0.0319
-3.250 -0.3490 0.00806 0.00210 -0.0023 0.9788 0.0330
-3.000 -0.3181 0.00791 0.00194 -0.0030 0.9724 0.0342
-2.750 -0.2881 0.00777 0.00181 -0.0035 0.9642 0.0355
-2.500 -0.2596 0.00764 0.00169 -0.0036 0.9538 0.0371
-2.250 -0.2319 0.00754 0.00158 -0.0035 0.9418 0.0403
-2.000 -0.2057 0.00734 0.00146 -0.0030 0.9251 0.0650
-1.750 -0.1804 0.00713 0.00133 -0.0024 0.9016 0.1023
-1.500 -0.1551 0.00687 0.00120 -0.0018 0.8761 0.1602
-1.250 -0.1294 0.00649 0.00108 -0.0015 0.8546 0.2495
-1.000 -0.1030 0.00632 0.00100 -0.0012 0.8277 0.3015
-0.750 -0.0776 0.00623 0.00092 -0.0008 0.7748 0.3573
-0.500 -0.0517 0.00607 0.00085 -0.0005 0.7248 0.4384
-0.250 -0.0255 0.00587 0.00081 -0.0003 0.6828 0.5256
0.000 0.0000 0.00577 0.00080 0.0000 0.6160 0.6157
0.250 0.0256 0.00585 0.00081 0.0003 0.5286 0.6832
0.500 0.0517 0.00607 0.00085 0.0005 0.4377 0.7248
0.750 0.0773 0.00623 0.00092 0.0008 0.3549 0.7781
1.000 0.1030 0.00630 0.00100 0.0013 0.3043 0.8290
1.250 0.1293 0.00649 0.00108 0.0015 0.2487 0.8544
1.500 0.1551 0.00686 0.00120 0.0018 0.1614 0.8761
1.750 0.1803 0.00713 0.00133 0.0024 0.1017 0.9018
2.000 0.2056 0.00735 0.00146 0.0030 0.0633 0.9251
2.250 0.2319 0.00754 0.00158 0.0035 0.0400 0.9418
2.500 0.2596 0.00764 0.00169 0.0036 0.0371 0.9538
2.750 0.2881 0.00777 0.00181 0.0035 0.0355 0.9642
3.000 0.3181 0.00791 0.00194 0.0030 0.0342 0.9725
3.250 0.3490 0.00806 0.00210 0.0023 0.0330 0.9788
3.500 0.3797 0.00823 0.00227 0.0017 0.0319 0.9849
3.750 0.4121 0.00843 0.00248 0.0006 0.0307 0.9889
4.000 0.4436 0.00867 0.00275 -0.0002 0.0294 0.9932
4.250 0.4760 0.00893 0.00305 -0.0013 0.0284 0.9959
4.500 0.5089 0.00911 0.00323 -0.0026 0.0281 0.9982
4.750 0.5399 0.00929 0.00342 -0.0034 0.0275 1.0000
5.000 0.5649 0.00947 0.00361 -0.0028 0.0267 1.0000
5.250 0.5901 0.00965 0.00382 -0.0023 0.0256 1.0000
5.500 0.6155 0.00986 0.00404 -0.0019 0.0245 1.0000
5.750 0.6413 0.01006 0.00425 -0.0015 0.0233 1.0000
6.000 0.6672 0.01029 0.00447 -0.0012 0.0221 1.0000
6.250 0.6931 0.01058 0.00478 -0.0009 0.0207 1.0000
6.500 0.7189 0.01089 0.00512 -0.0006 0.0194 1.0000
6.750 0.7455 0.01105 0.00530 -0.0004 0.0187 1.0000
7.000 0.7719 0.01125 0.00551 -0.0002 0.0175 1.0000
7.250 0.7984 0.01146 0.00571 -0.0001 0.0155 1.0000
7.500 0.8245 0.01174 0.00597 0.0001 0.0132 1.0000
7.750 0.8504 0.01207 0.00631 0.0003 0.0119 1.0000
8.000 0.8761 0.01244 0.00668 0.0006 0.0104 1.0000
8.250 0.9014 0.01288 0.00714 0.0009 0.0092 1.0000
8.500 0.9268 0.01329 0.00762 0.0012 0.0087 1.0000
8.750 0.9519 0.01375 0.00812 0.0015 0.0080 1.0000
9.000 0.9768 0.01424 0.00867 0.0018 0.0075 1.0000
9.250 1.0010 0.01483 0.00933 0.0022 0.0069 1.0000
9.500 1.0251 0.01545 0.01002 0.0027 0.0064 1.0000
9.750 1.0494 0.01598 0.01063 0.0030 0.0061 1.0000
10.000 1.0733 0.01656 0.01129 0.0035 0.0058 1.0000
10.250 1.0968 0.01718 0.01199 0.0039 0.0055 1.0000
10.500 1.1199 0.01785 0.01273 0.0044 0.0053 1.0000
10.750 1.1424 0.01858 0.01355 0.0049 0.0050 1.0000
11.000 1.1639 0.01945 0.01453 0.0056 0.0048 1.0000
11.250 1.1838 0.02055 0.01577 0.0064 0.0045 1.0000
11.500 1.2044 0.02145 0.01679 0.0071 0.0044 1.0000
11.750 1.2245 0.02239 0.01785 0.0079 0.0043 1.0000
12.000 1.2436 0.02340 0.01899 0.0087 0.0042 1.0000
12.250 1.2616 0.02451 0.02024 0.0096 0.0041 1.0000
12.500 1.2784 0.02570 0.02158 0.0106 0.0040 1.0000
12.750 1.2937 0.02699 0.02302 0.0117 0.0039 1.0000
13.000 1.3073 0.02840 0.02457 0.0130 0.0038 1.0000
13.250 1.3189 0.02991 0.02626 0.0143 0.0037 1.0000
13.500 1.3278 0.03156 0.02806 0.0158 0.0036 1.0000
13.750 1.3331 0.03336 0.03002 0.0176 0.0035 1.0000
14.000 1.3307 0.03528 0.03210 0.0203 0.0035 1.0000
14.250 1.3250 0.03766 0.03463 0.0224 0.0034 1.0000
14.500 1.3155 0.04076 0.03791 0.0232 0.0034 1.0000
14.750 1.3017 0.04502 0.04235 0.0223 0.0034 1.0000
15.000 1.2798 0.05169 0.04923 0.0182 0.0034 1.0000
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Polar data table (+)
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