NACA 0010 (naca0010-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 0010 (naca0010-il) Reynolds number: 500,000 Max Cl/Cd: 55.2 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca0010-il-500000.txt Download as CSV file: xf-naca0010-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0010
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -0.5410 0.15664 0.15441 0.0166 1.0000 0.0244
-15.250 -0.9687 0.10921 0.10680 0.0116 1.0000 0.0144
-15.000 -0.9414 0.11142 0.10906 0.0131 1.0000 0.0150
-14.750 -0.9092 0.11490 0.11260 0.0151 1.0000 0.0157
-14.500 -0.8712 0.11994 0.11766 0.0177 1.0000 0.0166
-13.750 -1.1591 0.04725 0.04339 -0.0277 1.0000 0.0135
-13.500 -1.1772 0.04217 0.03806 -0.0290 1.0000 0.0136
-13.250 -1.1889 0.03845 0.03414 -0.0288 1.0000 0.0139
-13.000 -1.1924 0.03596 0.03150 -0.0276 1.0000 0.0142
-12.750 -1.1898 0.03429 0.02972 -0.0261 1.0000 0.0145
-12.500 -1.1837 0.03304 0.02840 -0.0244 1.0000 0.0148
-12.250 -1.1760 0.03195 0.02721 -0.0224 1.0000 0.0153
-12.000 -1.1647 0.03087 0.02602 -0.0209 1.0000 0.0158
-11.750 -1.1519 0.02971 0.02471 -0.0195 1.0000 0.0165
-11.500 -1.1372 0.02863 0.02346 -0.0182 1.0000 0.0171
-11.250 -1.1201 0.02777 0.02243 -0.0171 1.0000 0.0177
-11.000 -1.1119 0.02534 0.01983 -0.0152 1.0000 0.0186
-10.750 -1.0929 0.02460 0.01905 -0.0143 1.0000 0.0194
-10.500 -1.0725 0.02400 0.01839 -0.0135 1.0000 0.0204
-10.250 -1.0520 0.02330 0.01760 -0.0126 1.0000 0.0215
-10.000 -1.0302 0.02277 0.01693 -0.0119 1.0000 0.0227
-9.750 -1.0116 0.02152 0.01553 -0.0108 1.0000 0.0240
-9.500 -0.9918 0.02057 0.01457 -0.0099 1.0000 0.0255
-9.250 -0.9692 0.02008 0.01404 -0.0093 1.0000 0.0270
-9.000 -0.9464 0.01954 0.01342 -0.0086 1.0000 0.0286
-8.750 -0.9222 0.01927 0.01306 -0.0080 1.0000 0.0299
-8.500 -0.9043 0.01773 0.01142 -0.0067 1.0000 0.0321
-8.250 -0.8817 0.01716 0.01085 -0.0060 1.0000 0.0339
-8.000 -0.8585 0.01668 0.01031 -0.0053 1.0000 0.0357
-7.750 -0.8348 0.01626 0.00983 -0.0046 1.0000 0.0374
-7.500 -0.8104 0.01600 0.00950 -0.0040 1.0000 0.0384
-7.250 -0.7922 0.01472 0.00816 -0.0025 1.0000 0.0409
-7.000 -0.7700 0.01420 0.00763 -0.0015 1.0000 0.0429
-6.750 -0.7472 0.01377 0.00717 -0.0006 1.0000 0.0448
-6.500 -0.7244 0.01338 0.00674 0.0003 1.0000 0.0466
-6.250 -0.7012 0.01304 0.00635 0.0013 1.0000 0.0479
-6.000 -0.6798 0.01246 0.00572 0.0024 1.0000 0.0498
-5.750 -0.6580 0.01195 0.00521 0.0036 1.0000 0.0530
-5.500 -0.6353 0.01159 0.00485 0.0046 1.0000 0.0560
-5.250 -0.6122 0.01130 0.00451 0.0055 1.0000 0.0591
-5.000 -0.5901 0.01084 0.00410 0.0066 1.0000 0.0677
-4.750 -0.5678 0.01039 0.00376 0.0076 1.0000 0.0877
-4.500 -0.5459 0.00989 0.00346 0.0086 1.0000 0.1251
-4.250 -0.5233 0.00948 0.00323 0.0094 1.0000 0.1629
-4.000 -0.5002 0.00914 0.00305 0.0101 1.0000 0.2012
-3.750 -0.4769 0.00881 0.00289 0.0108 1.0000 0.2422
-3.500 -0.4532 0.00851 0.00277 0.0114 1.0000 0.2842
-3.250 -0.4209 0.00820 0.00265 0.0102 0.9982 0.3324
-3.000 -0.3827 0.00789 0.00254 0.0077 0.9950 0.3835
-2.750 -0.3457 0.00757 0.00242 0.0056 0.9911 0.4361
-2.500 -0.3083 0.00724 0.00234 0.0034 0.9870 0.4958
-2.250 -0.2703 0.00695 0.00226 0.0011 0.9832 0.5508
-2.000 -0.2342 0.00667 0.00218 -0.0006 0.9775 0.6005
-1.750 -0.1959 0.00642 0.00210 -0.0028 0.9734 0.6461
-1.500 -0.1642 0.00620 0.00203 -0.0034 0.9644 0.6875
-1.250 -0.1334 0.00599 0.00198 -0.0037 0.9548 0.7284
-1.000 -0.1036 0.00583 0.00193 -0.0038 0.9437 0.7622
-0.750 -0.0762 0.00569 0.00189 -0.0032 0.9299 0.7927
-0.500 -0.0504 0.00559 0.00187 -0.0023 0.9129 0.8214
-0.250 -0.0251 0.00552 0.00185 -0.0012 0.8936 0.8479
0.000 0.0000 0.00550 0.00184 0.0000 0.8721 0.8722
0.250 0.0251 0.00552 0.00185 0.0012 0.8479 0.8935
0.500 0.0504 0.00559 0.00187 0.0023 0.8213 0.9129
0.750 0.0762 0.00569 0.00189 0.0032 0.7926 0.9298
1.000 0.1036 0.00583 0.00193 0.0038 0.7622 0.9437
1.250 0.1334 0.00599 0.00198 0.0037 0.7285 0.9548
1.500 0.1642 0.00620 0.00203 0.0034 0.6876 0.9644
1.750 0.1959 0.00642 0.00210 0.0028 0.6461 0.9734
2.000 0.2342 0.00667 0.00217 0.0006 0.6005 0.9775
2.250 0.2703 0.00695 0.00226 -0.0011 0.5507 0.9832
2.500 0.3083 0.00724 0.00234 -0.0034 0.4957 0.9870
2.750 0.3457 0.00757 0.00242 -0.0056 0.4362 0.9911
3.000 0.3827 0.00788 0.00253 -0.0077 0.3835 0.9950
3.250 0.4209 0.00820 0.00265 -0.0102 0.3325 0.9982
3.500 0.4532 0.00851 0.00277 -0.0114 0.2843 1.0000
3.750 0.4768 0.00881 0.00289 -0.0108 0.2422 1.0000
4.000 0.5002 0.00914 0.00305 -0.0101 0.2013 1.0000
4.250 0.5233 0.00948 0.00323 -0.0094 0.1629 1.0000
4.500 0.5458 0.00989 0.00346 -0.0086 0.1252 1.0000
4.750 0.5678 0.01039 0.00376 -0.0076 0.0877 1.0000
5.000 0.5901 0.01084 0.00410 -0.0066 0.0677 1.0000
5.250 0.6122 0.01130 0.00451 -0.0055 0.0591 1.0000
5.500 0.6353 0.01159 0.00484 -0.0046 0.0560 1.0000
5.750 0.6580 0.01195 0.00521 -0.0036 0.0530 1.0000
6.000 0.6798 0.01246 0.00572 -0.0024 0.0498 1.0000
6.250 0.7012 0.01304 0.00635 -0.0013 0.0479 1.0000
6.500 0.7244 0.01338 0.00674 -0.0003 0.0466 1.0000
6.750 0.7472 0.01377 0.00717 0.0006 0.0448 1.0000
7.000 0.7700 0.01420 0.00763 0.0015 0.0429 1.0000
7.250 0.7922 0.01472 0.00816 0.0025 0.0409 1.0000
7.500 0.8104 0.01600 0.00950 0.0040 0.0384 1.0000
7.750 0.8348 0.01627 0.00984 0.0046 0.0374 1.0000
8.000 0.8585 0.01667 0.01031 0.0053 0.0357 1.0000
8.250 0.8817 0.01716 0.01084 0.0060 0.0339 1.0000
8.500 0.9043 0.01772 0.01142 0.0067 0.0321 1.0000
8.750 0.9223 0.01926 0.01305 0.0080 0.0299 1.0000
9.000 0.9465 0.01954 0.01341 0.0085 0.0286 1.0000
9.250 0.9693 0.02008 0.01404 0.0092 0.0270 1.0000
9.500 0.9918 0.02058 0.01457 0.0099 0.0255 1.0000
9.750 1.0116 0.02152 0.01553 0.0108 0.0240 1.0000
10.000 1.0302 0.02277 0.01693 0.0119 0.0227 1.0000
10.250 1.0521 0.02330 0.01760 0.0126 0.0215 1.0000
10.500 1.0726 0.02400 0.01840 0.0135 0.0204 1.0000
10.750 1.0930 0.02460 0.01905 0.0143 0.0194 1.0000
11.000 1.1120 0.02534 0.01983 0.0152 0.0186 1.0000
11.250 1.1203 0.02776 0.02243 0.0170 0.0176 1.0000
11.500 1.1374 0.02861 0.02344 0.0182 0.0171 1.0000
11.750 1.1521 0.02971 0.02470 0.0195 0.0165 1.0000
12.000 1.1650 0.03086 0.02601 0.0208 0.0158 1.0000
12.250 1.1764 0.03193 0.02719 0.0223 0.0153 1.0000
12.500 1.1841 0.03303 0.02838 0.0243 0.0148 1.0000
12.750 1.1901 0.03430 0.02974 0.0261 0.0145 1.0000
13.000 1.1928 0.03597 0.03151 0.0276 0.0142 1.0000
13.250 1.1893 0.03846 0.03415 0.0287 0.0139 1.0000
13.500 1.1776 0.04220 0.03809 0.0289 0.0136 1.0000
13.750 1.1598 0.04726 0.04339 0.0276 0.0135 1.0000
14.000 1.1392 0.05348 0.04987 0.0244 0.0134 1.0000
14.250 1.1185 0.06054 0.05716 0.0198 0.0134 1.0000
14.500 1.0985 0.06815 0.06497 0.0145 0.0134 1.0000
14.750 1.0794 0.07607 0.07306 0.0090 0.0134 1.0000
15.000 1.0587 0.08458 0.08172 0.0034 0.0135 1.0000
15.250 1.0360 0.09378 0.09107 -0.0024 0.0136 1.0000
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