NASA/AMES 63A108 MOD C AIRFOIL (a63a108c-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA/AMES 63A108 MOD C AIRFOIL (a63a108c-il) Reynolds number: 100,000 Max Cl/Cd: 31.69 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-a63a108c-il-100000.txt Download as CSV file: xf-a63a108c-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.6796 0.09554 0.09079 0.0206 1.0000 0.1151
-7.750 -0.7040 0.08853 0.08376 0.0066 1.0000 0.1196
-7.500 -0.6948 0.08383 0.07912 0.0076 1.0000 0.1227
-7.250 -0.6828 0.08062 0.07590 0.0083 1.0000 0.1279
-7.000 -0.6902 0.07401 0.06912 0.0003 1.0000 0.1357
-6.750 -0.6730 0.07107 0.06625 0.0023 1.0000 0.1410
-6.500 -0.6686 0.06592 0.06093 -0.0017 1.0000 0.1516
-6.250 -0.6594 0.06196 0.05674 -0.0043 1.0000 0.1656
-6.000 -0.6402 0.05873 0.05365 -0.0027 1.0000 0.1722
-5.750 -0.6257 0.05506 0.04987 -0.0035 1.0000 0.1873
-5.500 -0.5924 0.03785 0.03013 -0.0104 1.0000 0.0790
-5.250 -0.5670 0.03440 0.02637 -0.0103 1.0000 0.0763
-5.000 -0.5393 0.03052 0.02146 -0.0095 1.0000 0.0703
-4.750 -0.5119 0.02774 0.01839 -0.0092 1.0000 0.0697
-4.500 -0.4835 0.02559 0.01579 -0.0088 1.0000 0.0704
-4.250 -0.4564 0.02373 0.01404 -0.0088 1.0000 0.0747
-4.000 -0.4275 0.02209 0.01210 -0.0083 1.0000 0.0777
-3.750 -0.3998 0.02046 0.01054 -0.0081 1.0000 0.0827
-3.500 -0.3723 0.01912 0.00923 -0.0078 1.0000 0.0904
-3.250 -0.3454 0.01785 0.00808 -0.0073 1.0000 0.1005
-3.000 -0.3190 0.01669 0.00706 -0.0069 1.0000 0.1173
-2.750 -0.2935 0.01536 0.00602 -0.0064 1.0000 0.1521
-2.500 -0.2811 0.01196 0.00529 -0.0036 1.0000 0.6284
-2.250 -0.2668 0.01155 0.00539 0.0014 1.0000 0.7969
-2.000 -0.2466 0.01144 0.00542 0.0053 1.0000 0.8845
-1.750 -0.1922 0.01165 0.00548 0.0023 1.0000 0.9627
-1.500 -0.1091 0.01184 0.00536 -0.0080 1.0000 1.0000
-1.250 -0.0887 0.01151 0.00493 -0.0079 1.0000 1.0000
-1.000 -0.0693 0.01126 0.00460 -0.0073 1.0000 1.0000
-0.750 -0.0513 0.01110 0.00437 -0.0063 1.0000 1.0000
-0.500 -0.0347 0.01104 0.00423 -0.0049 1.0000 1.0000
-0.250 -0.0184 0.01106 0.00418 -0.0033 1.0000 1.0000
0.000 -0.0007 0.01114 0.00420 -0.0020 1.0000 1.0000
0.250 0.0187 0.01126 0.00427 -0.0009 1.0000 1.0000
0.500 0.0393 0.01142 0.00440 -0.0001 1.0000 1.0000
0.750 0.0606 0.01162 0.00458 0.0006 1.0000 1.0000
1.000 0.0825 0.01186 0.00481 0.0010 1.0000 1.0000
1.250 0.1046 0.01213 0.00509 0.0014 1.0000 1.0000
1.500 0.1301 0.01243 0.00543 0.0009 0.9986 1.0000
1.750 0.2065 0.01243 0.00556 -0.0087 0.9765 1.0000
2.000 0.2759 0.01228 0.00559 -0.0161 0.9495 1.0000
2.250 0.3134 0.01223 0.00565 -0.0166 0.9126 1.0000
2.500 0.3352 0.01221 0.00566 -0.0136 0.8725 1.0000
2.750 0.3524 0.01214 0.00559 -0.0097 0.8235 1.0000
3.000 0.3697 0.01206 0.00545 -0.0057 0.7574 1.0000
3.250 0.3863 0.01219 0.00521 -0.0015 0.6399 1.0000
3.500 0.4038 0.01332 0.00520 0.0016 0.4297 1.0000
3.750 0.4270 0.01477 0.00576 0.0022 0.3005 1.0000
4.000 0.4522 0.01597 0.00646 0.0025 0.2402 1.0000
4.250 0.4784 0.01700 0.00727 0.0027 0.2015 1.0000
4.500 0.5046 0.01803 0.00808 0.0030 0.1747 1.0000
4.750 0.5312 0.01912 0.00906 0.0032 0.1544 1.0000
5.000 0.5580 0.02021 0.01010 0.0035 0.1382 1.0000
5.250 0.5849 0.02140 0.01127 0.0037 0.1254 1.0000
5.500 0.6116 0.02270 0.01254 0.0039 0.1149 1.0000
5.750 0.6383 0.02403 0.01383 0.0041 0.1061 1.0000
6.000 0.6655 0.02552 0.01560 0.0044 0.0987 1.0000
6.250 0.6918 0.02728 0.01756 0.0046 0.0925 1.0000
6.500 0.7180 0.02899 0.01939 0.0048 0.0877 1.0000
6.750 0.7428 0.03143 0.02227 0.0051 0.0834 1.0000
7.000 0.7668 0.03423 0.02557 0.0054 0.0809 1.0000
7.250 0.7904 0.03660 0.02803 0.0056 0.0786 1.0000
7.500 0.8096 0.04050 0.03251 0.0058 0.0770 1.0000
7.750 0.8255 0.04518 0.03779 0.0060 0.0769 1.0000
8.000 0.8420 0.04965 0.04256 0.0061 0.0781 1.0000
8.250 0.7801 0.08251 0.07744 -0.0101 0.1594 1.0000
8.500 0.7593 0.09004 0.08500 -0.0181 0.1547 1.0000
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Polar data table (+)
Polar graphs
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