NASA/AMES 63A108 MOD C AIRFOIL (a63a108c-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/AMES 63A108 MOD C AIRFOIL (a63a108c-il) Reynolds number: 1,000,000 Max Cl/Cd: 72.71 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-a63a108c-il-1000000-n5.txt Download as CSV file: xf-a63a108c-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA/AMES 63A108 MOD C 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
------ -------- --------- --------- -------- -------- --------
-13.500 -1.2464 0.05164 0.04936 -0.0050 1.0000 0.0056
-13.250 -1.2817 0.04420 0.04164 -0.0086 1.0000 0.0055
-13.000 -1.2970 0.04043 0.03765 -0.0069 1.0000 0.0056
-12.750 -1.2974 0.03733 0.03434 -0.0060 1.0000 0.0056
-12.500 -1.2910 0.03478 0.03158 -0.0050 1.0000 0.0056
-12.250 -1.2801 0.03263 0.02925 -0.0042 1.0000 0.0057
-12.000 -1.2662 0.03073 0.02717 -0.0035 1.0000 0.0058
-11.750 -1.2501 0.02905 0.02532 -0.0028 1.0000 0.0058
-11.500 -1.2321 0.02755 0.02367 -0.0022 1.0000 0.0059
-11.250 -1.2130 0.02613 0.02209 -0.0017 1.0000 0.0060
-11.000 -1.1926 0.02483 0.02064 -0.0012 1.0000 0.0061
-10.750 -1.1712 0.02365 0.01931 -0.0008 1.0000 0.0062
-10.500 -1.1489 0.02258 0.01811 -0.0004 1.0000 0.0064
-10.250 -1.1258 0.02160 0.01700 0.0000 1.0000 0.0065
-10.000 -1.1020 0.02070 0.01598 0.0003 1.0000 0.0067
-9.750 -1.0778 0.01984 0.01500 0.0005 1.0000 0.0068
-9.500 -1.0531 0.01905 0.01409 0.0008 1.0000 0.0070
-9.250 -1.0279 0.01831 0.01324 0.0010 1.0000 0.0071
-9.000 -1.0029 0.01745 0.01227 0.0012 1.0000 0.0072
-8.750 -0.9778 0.01657 0.01130 0.0014 1.0000 0.0074
-8.500 -0.9517 0.01593 0.01059 0.0015 1.0000 0.0076
-8.250 -0.9252 0.01539 0.01000 0.0016 1.0000 0.0077
-8.000 -0.8984 0.01487 0.00942 0.0016 1.0000 0.0079
-7.750 -0.8714 0.01437 0.00887 0.0016 1.0000 0.0081
-7.500 -0.8442 0.01388 0.00833 0.0017 1.0000 0.0084
-7.250 -0.8168 0.01341 0.00780 0.0017 1.0000 0.0086
-7.000 -0.7893 0.01296 0.00730 0.0017 1.0000 0.0089
-6.750 -0.7615 0.01253 0.00682 0.0016 1.0000 0.0091
-6.500 -0.7335 0.01216 0.00640 0.0016 1.0000 0.0093
-6.250 -0.7057 0.01166 0.00588 0.0015 1.0000 0.0097
-6.000 -0.6774 0.01130 0.00551 0.0013 1.0000 0.0100
-5.750 -0.6489 0.01100 0.00520 0.0012 1.0000 0.0105
-5.500 -0.6201 0.01071 0.00489 0.0010 0.9914 0.0110
-5.250 -0.5914 0.01049 0.00463 0.0009 0.9694 0.0115
-5.000 -0.5650 0.01022 0.00433 0.0013 0.9569 0.0120
-4.750 -0.5388 0.01000 0.00409 0.0018 0.9458 0.0126
-4.250 -0.4854 0.00961 0.00364 0.0026 0.9291 0.0140
-4.000 -0.4585 0.00941 0.00342 0.0029 0.9221 0.0148
-3.750 -0.4305 0.00922 0.00322 0.0030 0.9150 0.0160
-3.250 -0.3748 0.00889 0.00287 0.0033 0.9005 0.0192
-3.000 -0.3470 0.00872 0.00270 0.0034 0.8926 0.0214
-2.750 -0.3187 0.00857 0.00254 0.0035 0.8849 0.0241
-2.500 -0.2905 0.00842 0.00240 0.0036 0.8767 0.0277
-2.250 -0.2622 0.00828 0.00226 0.0036 0.8670 0.0330
-2.000 -0.2341 0.00814 0.00213 0.0037 0.8523 0.0416
-1.750 -0.2061 0.00800 0.00199 0.0039 0.8319 0.0533
-1.500 -0.1779 0.00785 0.00186 0.0039 0.8097 0.0749
-1.250 -0.1495 0.00765 0.00175 0.0039 0.7885 0.1108
-1.000 -0.1209 0.00741 0.00163 0.0037 0.7661 0.1655
-0.750 -0.0924 0.00716 0.00152 0.0035 0.7327 0.2377
-0.500 -0.0638 0.00686 0.00142 0.0032 0.6997 0.3306
-0.250 -0.0352 0.00647 0.00134 0.0029 0.6618 0.4586
0.000 -0.0065 0.00634 0.00130 0.0025 0.6046 0.5488
0.250 0.0223 0.00631 0.00131 0.0022 0.5400 0.6261
0.500 0.0512 0.00642 0.00134 0.0020 0.4700 0.6750
0.750 0.0799 0.00654 0.00139 0.0017 0.4046 0.7221
1.000 0.1083 0.00668 0.00145 0.0015 0.3381 0.7673
1.250 0.1368 0.00684 0.00151 0.0014 0.2826 0.7986
1.500 0.1653 0.00696 0.00156 0.0013 0.2430 0.8208
1.750 0.1934 0.00706 0.00162 0.0013 0.2098 0.8455
2.000 0.2206 0.00713 0.00169 0.0016 0.1812 0.8785
2.250 0.2459 0.00717 0.00175 0.0024 0.1569 0.9226
2.500 0.2743 0.00721 0.00177 0.0025 0.1366 0.9716
3.000 0.3358 0.00755 0.00194 0.0012 0.1024 1.0000
3.250 0.3647 0.00774 0.00205 0.0010 0.0893 1.0000
3.500 0.3935 0.00793 0.00217 0.0008 0.0782 1.0000
3.750 0.4224 0.00812 0.00230 0.0006 0.0691 1.0000
4.000 0.4512 0.00831 0.00244 0.0004 0.0606 1.0000
4.250 0.4799 0.00852 0.00260 0.0003 0.0530 1.0000
4.500 0.5086 0.00873 0.00276 0.0001 0.0473 1.0000
4.750 0.5372 0.00893 0.00293 -0.0001 0.0428 1.0000
5.000 0.5658 0.00914 0.00312 -0.0002 0.0385 1.0000
5.250 0.5943 0.00936 0.00331 -0.0004 0.0348 1.0000
5.500 0.6228 0.00958 0.00351 -0.0005 0.0318 1.0000
5.750 0.6512 0.00981 0.00374 -0.0007 0.0293 1.0000
6.000 0.6795 0.01007 0.00397 -0.0008 0.0269 1.0000
6.250 0.7078 0.01031 0.00421 -0.0009 0.0249 1.0000
6.500 0.7359 0.01058 0.00448 -0.0010 0.0230 1.0000
6.750 0.7640 0.01085 0.00475 -0.0011 0.0214 1.0000
7.000 0.7919 0.01114 0.00504 -0.0012 0.0201 1.0000
7.250 0.8198 0.01143 0.00535 -0.0013 0.0189 1.0000
7.500 0.8475 0.01178 0.00569 -0.0014 0.0179 1.0000
7.750 0.8752 0.01209 0.00603 -0.0015 0.0172 1.0000
8.000 0.9027 0.01242 0.00639 -0.0015 0.0164 1.0000
8.250 0.9300 0.01279 0.00677 -0.0016 0.0157 1.0000
8.500 0.9572 0.01319 0.00720 -0.0016 0.0151 1.0000
8.750 0.9843 0.01355 0.00760 -0.0016 0.0145 1.0000
9.000 1.0112 0.01395 0.00803 -0.0016 0.0140 1.0000
9.250 1.0379 0.01437 0.00850 -0.0016 0.0136 1.0000
9.500 1.0643 0.01485 0.00900 -0.0016 0.0132 1.0000
9.750 1.0903 0.01541 0.00960 -0.0015 0.0128 1.0000
10.000 1.1164 0.01587 0.01013 -0.0015 0.0125 1.0000
10.250 1.1422 0.01638 0.01071 -0.0014 0.0123 1.0000
10.500 1.1678 0.01691 0.01130 -0.0012 0.0120 1.0000
10.750 1.1930 0.01747 0.01192 -0.0011 0.0117 1.0000
11.000 1.2180 0.01805 0.01257 -0.0009 0.0114 1.0000
11.250 1.2425 0.01866 0.01323 -0.0008 0.0112 1.0000
11.500 1.2665 0.01933 0.01396 -0.0006 0.0108 1.0000
11.750 1.2897 0.02011 0.01481 -0.0003 0.0105 1.0000
12.000 1.3137 0.02070 0.01548 0.0000 0.0102 1.0000
12.250 1.3369 0.02135 0.01622 0.0003 0.0100 1.0000
12.500 1.3598 0.02202 0.01697 0.0006 0.0097 1.0000
12.750 1.3820 0.02277 0.01780 0.0010 0.0094 1.0000
13.000 1.4034 0.02357 0.01869 0.0014 0.0092 1.0000
13.250 1.4239 0.02444 0.01964 0.0019 0.0090 1.0000
13.500 1.4434 0.02539 0.02067 0.0025 0.0089 1.0000
13.750 1.4616 0.02644 0.02182 0.0032 0.0087 1.0000
14.000 1.4778 0.02766 0.02314 0.0040 0.0085 1.0000
14.250 1.4922 0.02898 0.02457 0.0049 0.0084 1.0000
14.500 1.5064 0.03019 0.02590 0.0058 0.0083 1.0000
14.750 1.5181 0.03153 0.02738 0.0069 0.0082 1.0000
15.000 1.5265 0.03300 0.02897 0.0083 0.0081 1.0000
15.250 1.5273 0.03467 0.03077 0.0104 0.0081 1.0000
15.500 1.5243 0.03684 0.03308 0.0119 0.0080 1.0000
15.750 1.5188 0.03968 0.03607 0.0124 0.0080 1.0000
16.000 1.5115 0.04322 0.03976 0.0117 0.0079 1.0000
16.250 1.4973 0.04844 0.04516 0.0090 0.0079 1.0000
16.500 1.4705 0.05726 0.05421 0.0024 0.0079 1.0000
16.750 1.2619 0.10517 0.10273 -0.0288 0.0084 1.0000
17.000 1.1794 0.12570 0.12345 -0.0402 0.0087 1.0000
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Polar data table (+)
Polar graphs
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