NACA 63(2)A-015 (naca632a015-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 63(2)A-015 (naca632a015-il) Reynolds number: 50,000 Max Cl/Cd: 23.29 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca632a015-il-50000.txt Download as CSV file: xf-naca632a015-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63(2)A-015
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5020 0.07862 0.07218 -0.0332 1.0000 0.2383
-8.500 -0.5658 0.07307 0.06680 -0.0334 1.0000 0.2330
-8.250 -0.6215 0.06968 0.06346 -0.0297 1.0000 0.2310
-8.000 -0.6425 0.06454 0.05817 -0.0281 1.0000 0.2071
-7.750 -0.6885 0.06199 0.05530 -0.0224 1.0000 0.1996
-7.500 -0.6935 0.05829 0.05129 -0.0193 1.0000 0.1788
-7.000 -0.7178 0.05358 0.04558 -0.0097 1.0000 0.1524
-6.750 -0.7085 0.05065 0.04252 -0.0072 1.0000 0.1450
-6.500 -0.7105 0.04869 0.04001 -0.0029 1.0000 0.1373
-6.250 -0.7060 0.04742 0.03825 0.0008 1.0000 0.1335
-6.000 -0.6955 0.04489 0.03553 0.0031 1.0000 0.1317
-5.750 -0.6837 0.04270 0.03310 0.0055 1.0000 0.1297
-5.500 -0.6692 0.04072 0.03083 0.0077 1.0000 0.1270
-5.250 -0.6531 0.03895 0.02873 0.0098 1.0000 0.1251
-5.000 -0.6356 0.03739 0.02692 0.0115 1.0000 0.1261
-4.750 -0.6170 0.03604 0.02535 0.0131 1.0000 0.1288
-4.500 -0.5960 0.03482 0.02390 0.0145 1.0000 0.1314
-4.250 -0.5746 0.03389 0.02272 0.0159 1.0000 0.1346
-4.000 -0.5454 0.03219 0.02132 0.0160 1.0000 0.1428
-3.750 -0.5246 0.03146 0.02050 0.0174 1.0000 0.1513
-3.500 -0.5087 0.03037 0.01958 0.0193 1.0000 0.1615
-3.250 -0.4975 0.02953 0.01876 0.0216 1.0000 0.1720
-3.000 -0.4874 0.02868 0.01793 0.0240 1.0000 0.1854
-2.750 -0.4770 0.02765 0.01709 0.0260 1.0000 0.2077
-2.500 -0.4763 0.02540 0.01646 0.0292 1.0000 0.3925
-2.250 -0.4780 0.02532 0.01755 0.0367 1.0000 0.6574
-2.000 -0.1398 0.03821 0.02964 0.0083 1.0000 0.9613
-1.750 -0.1160 0.03813 0.02942 0.0059 1.0000 0.9719
-1.500 -0.0536 0.03799 0.02905 -0.0036 0.9906 0.9803
-1.250 0.0128 0.03783 0.02868 -0.0138 0.9802 0.9892
-1.000 0.0817 0.03766 0.02833 -0.0244 0.9706 0.9984
-0.750 0.1190 0.03753 0.02812 -0.0291 0.9586 1.0000
-0.500 0.1484 0.03751 0.02802 -0.0322 0.9461 1.0000
-0.250 0.1760 0.03755 0.02800 -0.0349 0.9339 1.0000
0.000 0.2084 0.03764 0.02802 -0.0381 0.9222 1.0000
0.250 0.2417 0.03771 0.02804 -0.0413 0.9097 1.0000
0.500 0.2589 0.03789 0.02820 -0.0416 0.8958 1.0000
0.750 0.2787 0.03810 0.02838 -0.0422 0.8820 1.0000
1.000 0.3029 0.03829 0.02855 -0.0433 0.8679 1.0000
1.250 0.3326 0.03842 0.02867 -0.0450 0.8535 1.0000
1.500 0.3685 0.03845 0.02868 -0.0473 0.8384 1.0000
1.750 0.4114 0.03829 0.02853 -0.0504 0.8225 1.0000
2.000 0.4626 0.03789 0.02816 -0.0543 0.8064 1.0000
2.250 0.4939 0.03771 0.02801 -0.0549 0.7900 1.0000
2.500 0.5106 0.03785 0.02816 -0.0533 0.7736 1.0000
2.750 0.5293 0.03790 0.02825 -0.0518 0.7569 1.0000
3.000 0.5474 0.03791 0.02828 -0.0501 0.7401 1.0000
3.250 0.5642 0.03793 0.02832 -0.0480 0.7233 1.0000
3.500 0.5826 0.03783 0.02825 -0.0459 0.7063 1.0000
3.750 0.6048 0.03752 0.02799 -0.0440 0.6890 1.0000
4.000 0.6287 0.03711 0.02760 -0.0421 0.6717 1.0000
4.250 0.6473 0.03685 0.02736 -0.0396 0.6540 1.0000
4.500 0.6461 0.03735 0.02787 -0.0349 0.6346 1.0000
4.750 0.6562 0.03747 0.02802 -0.0314 0.6157 1.0000
5.000 0.6720 0.03742 0.02798 -0.0285 0.5972 1.0000
5.250 0.6936 0.03714 0.02771 -0.0262 0.5788 1.0000
5.500 0.7178 0.03681 0.02738 -0.0242 0.5610 1.0000
5.750 0.7418 0.03656 0.02715 -0.0223 0.5437 1.0000
6.000 0.7656 0.03639 0.02697 -0.0205 0.5266 1.0000
6.250 0.7844 0.03659 0.02717 -0.0183 0.5103 1.0000
6.500 0.7992 0.03713 0.02774 -0.0159 0.4949 1.0000
6.750 0.8126 0.03781 0.02844 -0.0134 0.4801 1.0000
7.000 0.8274 0.03850 0.02914 -0.0112 0.4659 1.0000
7.250 0.8480 0.03893 0.02959 -0.0095 0.4525 1.0000
7.500 0.8751 0.03900 0.02966 -0.0084 0.4387 1.0000
7.750 0.9062 0.03891 0.02954 -0.0078 0.4247 1.0000
8.000 0.8972 0.04103 0.03180 -0.0036 0.4130 1.0000
8.250 0.8963 0.04288 0.03374 -0.0004 0.4018 1.0000
8.500 0.9209 0.04330 0.03418 0.0008 0.3893 1.0000
8.750 0.9533 0.04336 0.03424 0.0012 0.3758 1.0000
9.000 0.9128 0.04766 0.03872 0.0071 0.3689 1.0000
9.250 0.9328 0.04841 0.03953 0.0086 0.3565 1.0000
9.500 0.8910 0.05310 0.04428 0.0136 0.3508 1.0000
9.750 0.8220 0.06102 0.05213 0.0173 0.3478 1.0000
10.000 0.7181 0.07734 0.06822 0.0135 0.3459 1.0000
10.250 0.6633 0.08797 0.07873 0.0102 0.3441 1.0000
10.500 0.6319 0.09550 0.08619 0.0080 0.3425 1.0000
10.750 0.6132 0.10153 0.09221 0.0062 0.3409 1.0000
11.000 0.6020 0.10696 0.09766 0.0047 0.3407 1.0000
11.250 0.5983 0.11217 0.10291 0.0031 0.3428 1.0000
11.500 0.6009 0.11713 0.10793 0.0018 0.3445 1.0000
11.750 0.6200 0.11928 0.11017 0.0026 0.3296 1.0000
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Polar data table (+)
Polar graphs
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