NACA 0015 (naca0015-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 0015 (naca0015-il) Reynolds number: 100,000 Max Cl/Cd: 37.5 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca0015-il-100000.txt Download as CSV file: xf-naca0015-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0015
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
------ -------- --------- --------- -------- -------- --------
-13.750 -0.9918 0.07386 0.06732 -0.0434 1.0000 0.0931
-13.500 -1.0244 0.06821 0.06144 -0.0442 1.0000 0.0930
-13.250 -1.0543 0.06363 0.05660 -0.0433 1.0000 0.0930
-13.000 -1.0815 0.05992 0.05262 -0.0408 1.0000 0.0931
-12.750 -1.1060 0.05692 0.04933 -0.0370 1.0000 0.0933
-12.500 -1.0961 0.05378 0.04619 -0.0363 1.0000 0.0949
-12.250 -1.0894 0.05164 0.04399 -0.0348 1.0000 0.0965
-12.000 -1.0861 0.04938 0.04158 -0.0328 1.0000 0.0979
-11.750 -1.0855 0.04699 0.03895 -0.0304 1.0000 0.0994
-11.500 -1.0844 0.04470 0.03639 -0.0277 1.0000 0.1012
-11.250 -1.0839 0.04255 0.03387 -0.0248 1.0000 0.1032
-11.000 -1.0765 0.04031 0.03136 -0.0226 1.0000 0.1055
-10.750 -1.0559 0.03869 0.02982 -0.0220 1.0000 0.1087
-10.500 -1.0416 0.03713 0.02812 -0.0204 1.0000 0.1121
-10.250 -1.0304 0.03553 0.02621 -0.0181 1.0000 0.1157
-10.000 -1.0105 0.03385 0.02459 -0.0173 1.0000 0.1202
-9.750 -0.9937 0.03268 0.02338 -0.0158 1.0000 0.1255
-9.500 -0.9786 0.03123 0.02173 -0.0139 1.0000 0.1312
-9.250 -0.9588 0.03010 0.02075 -0.0129 1.0000 0.1379
-9.000 -0.9434 0.02889 0.01942 -0.0109 1.0000 0.1458
-8.750 -0.9265 0.02794 0.01855 -0.0093 1.0000 0.1546
-8.500 -0.9100 0.02689 0.01755 -0.0075 1.0000 0.1642
-8.250 -0.8950 0.02597 0.01658 -0.0055 1.0000 0.1755
-8.000 -0.8797 0.02519 0.01582 -0.0034 1.0000 0.1877
-7.750 -0.8638 0.02437 0.01512 -0.0015 1.0000 0.2008
-7.500 -0.8484 0.02362 0.01445 0.0006 1.0000 0.2150
-7.250 -0.8331 0.02292 0.01383 0.0027 1.0000 0.2306
-7.000 -0.8179 0.02228 0.01327 0.0048 1.0000 0.2475
-6.750 -0.8025 0.02169 0.01274 0.0069 1.0000 0.2658
-6.500 -0.7870 0.02114 0.01225 0.0090 1.0000 0.2854
-6.250 -0.7712 0.02062 0.01179 0.0110 1.0000 0.3061
-6.000 -0.7545 0.02012 0.01145 0.0130 1.0000 0.3266
-5.750 -0.7377 0.01969 0.01113 0.0149 1.0000 0.3481
-5.500 -0.7206 0.01930 0.01083 0.0167 1.0000 0.3708
-5.250 -0.7032 0.01895 0.01053 0.0185 1.0000 0.3942
-5.000 -0.6848 0.01863 0.01034 0.0201 1.0000 0.4163
-4.750 -0.6664 0.01836 0.01018 0.0217 1.0000 0.4396
-4.500 -0.6478 0.01813 0.00999 0.0233 1.0000 0.4642
-4.250 -0.6283 0.01792 0.00992 0.0247 1.0000 0.4871
-4.000 -0.6087 0.01777 0.00989 0.0261 1.0000 0.5110
-3.750 -0.5892 0.01765 0.00983 0.0274 1.0000 0.5363
-3.500 -0.5693 0.01756 0.00987 0.0287 1.0000 0.5598
-3.250 -0.5497 0.01751 0.00994 0.0300 1.0000 0.5841
-3.000 -0.5304 0.01749 0.00999 0.0312 1.0000 0.6100
-2.750 -0.5110 0.01752 0.01017 0.0325 1.0000 0.6335
-2.500 -0.4865 0.01761 0.01037 0.0328 0.9982 0.6598
-2.250 -0.4391 0.01785 0.01072 0.0289 0.9882 0.6899
-2.000 -0.3925 0.01807 0.01101 0.0253 0.9775 0.7205
-1.750 -0.3443 0.01834 0.01141 0.0219 0.9674 0.7471
-1.500 -0.3021 0.01848 0.01160 0.0195 0.9547 0.7742
-1.250 -0.2605 0.01867 0.01187 0.0176 0.9418 0.7975
-1.000 -0.2161 0.01890 0.01215 0.0153 0.9299 0.8195
-0.750 -0.1605 0.01912 0.01239 0.0111 0.9210 0.8397
-0.500 -0.1125 0.01931 0.01260 0.0084 0.9083 0.8575
-0.250 -0.0557 0.01942 0.01272 0.0041 0.8982 0.8727
0.000 0.0000 0.01941 0.01270 0.0000 0.8869 0.8869
0.250 0.0556 0.01942 0.01272 -0.0041 0.8727 0.8983
0.500 0.1126 0.01931 0.01260 -0.0084 0.8575 0.9083
0.750 0.1605 0.01912 0.01239 -0.0111 0.8397 0.9210
1.000 0.2160 0.01890 0.01215 -0.0153 0.8195 0.9299
1.250 0.2605 0.01867 0.01187 -0.0176 0.7975 0.9418
1.500 0.3021 0.01848 0.01160 -0.0195 0.7743 0.9547
1.750 0.3442 0.01834 0.01140 -0.0218 0.7471 0.9675
2.000 0.3925 0.01807 0.01101 -0.0253 0.7205 0.9775
2.250 0.4391 0.01785 0.01072 -0.0289 0.6899 0.9882
2.500 0.4865 0.01761 0.01037 -0.0328 0.6598 0.9982
2.750 0.5109 0.01752 0.01016 -0.0325 0.6336 1.0000
3.000 0.5303 0.01749 0.00998 -0.0312 0.6101 1.0000
3.250 0.5496 0.01751 0.00994 -0.0300 0.5842 1.0000
3.500 0.5692 0.01755 0.00987 -0.0286 0.5598 1.0000
3.750 0.5890 0.01765 0.00982 -0.0273 0.5363 1.0000
4.000 0.6085 0.01777 0.00988 -0.0260 0.5110 1.0000
4.250 0.6281 0.01792 0.00992 -0.0247 0.4872 1.0000
4.500 0.6477 0.01813 0.00999 -0.0233 0.4642 1.0000
4.750 0.6663 0.01835 0.01018 -0.0217 0.4396 1.0000
5.000 0.6847 0.01862 0.01034 -0.0201 0.4164 1.0000
5.250 0.7030 0.01895 0.01052 -0.0185 0.3942 1.0000
5.500 0.7205 0.01930 0.01082 -0.0167 0.3709 1.0000
5.750 0.7376 0.01969 0.01113 -0.0148 0.3481 1.0000
6.000 0.7544 0.02012 0.01145 -0.0129 0.3266 1.0000
6.250 0.7711 0.02062 0.01179 -0.0110 0.3062 1.0000
6.500 0.7869 0.02113 0.01225 -0.0090 0.2855 1.0000
6.750 0.8024 0.02169 0.01274 -0.0069 0.2658 1.0000
7.000 0.8178 0.02228 0.01327 -0.0048 0.2475 1.0000
7.250 0.8330 0.02292 0.01383 -0.0026 0.2306 1.0000
7.500 0.8483 0.02361 0.01445 -0.0005 0.2150 1.0000
7.750 0.8637 0.02437 0.01512 0.0015 0.2008 1.0000
8.000 0.8796 0.02519 0.01581 0.0034 0.1877 1.0000
8.250 0.8949 0.02597 0.01657 0.0055 0.1755 1.0000
8.500 0.9100 0.02689 0.01754 0.0075 0.1642 1.0000
8.750 0.9265 0.02794 0.01855 0.0093 0.1546 1.0000
9.000 0.9434 0.02889 0.01941 0.0109 0.1458 1.0000
9.250 0.9588 0.03010 0.02075 0.0128 0.1379 1.0000
9.500 0.9786 0.03123 0.02173 0.0139 0.1312 1.0000
9.750 0.9938 0.03268 0.02338 0.0158 0.1255 1.0000
10.000 1.0106 0.03385 0.02459 0.0173 0.1202 1.0000
10.250 1.0305 0.03553 0.02621 0.0181 0.1157 1.0000
10.500 1.0417 0.03713 0.02812 0.0203 0.1120 1.0000
10.750 1.0561 0.03869 0.02982 0.0220 0.1087 1.0000
11.000 1.0768 0.04032 0.03136 0.0225 0.1055 1.0000
11.250 1.0841 0.04256 0.03387 0.0247 0.1032 1.0000
11.500 1.0847 0.04471 0.03639 0.0277 0.1012 1.0000
11.750 1.0858 0.04699 0.03896 0.0303 0.0993 1.0000
12.000 1.0865 0.04938 0.04159 0.0327 0.0979 1.0000
12.250 1.0902 0.05164 0.04399 0.0346 0.0964 1.0000
12.500 1.0972 0.05379 0.04620 0.0362 0.0949 1.0000
12.750 1.1063 0.05695 0.04936 0.0369 0.0933 1.0000
13.000 1.0817 0.05995 0.05265 0.0407 0.0931 1.0000
13.250 1.0546 0.06367 0.05665 0.0431 0.0929 1.0000
13.500 1.0247 0.06828 0.06152 0.0440 0.0930 1.0000
13.750 0.9920 0.07396 0.06743 0.0432 0.0931 1.0000
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