NACA 0010-34 (naca001034-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 0010-34 (naca001034-il) Reynolds number: 50,000 Max Cl/Cd: 20.77 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca001034-il-50000.txt Download as CSV file: xf-naca001034-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0010-34
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 -0.5067 0.08470 0.07836 -0.0132 1.0000 0.2617
-8.500 -0.5732 0.07264 0.06647 -0.0246 1.0000 0.2009
-8.250 -0.6192 0.06536 0.05919 -0.0269 1.0000 0.1747
-8.000 -0.7109 0.07464 0.06814 -0.0180 1.0000 0.2096
-7.750 -0.7261 0.06616 0.05928 -0.0206 1.0000 0.1626
-7.500 -0.7341 0.06039 0.05299 -0.0196 1.0000 0.1385
-7.250 -0.7331 0.05552 0.04761 -0.0174 1.0000 0.1233
-7.000 -0.7284 0.05137 0.04287 -0.0146 1.0000 0.1124
-6.750 -0.7210 0.04752 0.03847 -0.0117 1.0000 0.1062
-6.500 -0.7115 0.04506 0.03516 -0.0081 1.0000 0.1025
-6.250 -0.6960 0.04196 0.03163 -0.0059 1.0000 0.1024
-6.000 -0.6766 0.03880 0.02812 -0.0040 1.0000 0.1018
-5.750 -0.6537 0.03577 0.02475 -0.0024 1.0000 0.1008
-5.500 -0.6281 0.03316 0.02175 -0.0011 1.0000 0.1010
-5.250 -0.5991 0.03085 0.01909 -0.0001 1.0000 0.1032
-5.000 -0.5687 0.02859 0.01680 0.0002 1.0000 0.1147
-4.750 -0.5367 0.02656 0.01481 0.0006 1.0000 0.1276
-4.500 -0.5139 0.02474 0.01307 0.0022 1.0000 0.1459
-4.250 -0.3028 0.02841 0.01900 -0.0059 1.0000 0.9411
-4.000 -0.2270 0.02704 0.01700 -0.0166 1.0000 0.9717
-3.750 -0.1509 0.02530 0.01468 -0.0283 1.0000 0.9988
-3.500 -0.1347 0.02442 0.01364 -0.0285 1.0000 1.0000
-3.250 -0.1213 0.02367 0.01276 -0.0279 1.0000 1.0000
-3.000 -0.1080 0.02301 0.01198 -0.0272 1.0000 1.0000
-2.750 -0.0949 0.02243 0.01130 -0.0262 1.0000 1.0000
-2.500 -0.0822 0.02193 0.01067 -0.0250 1.0000 1.0000
-2.250 -0.0702 0.02149 0.01016 -0.0235 1.0000 1.0000
-2.000 -0.0589 0.02112 0.00973 -0.0218 1.0000 1.0000
-1.750 -0.0486 0.02080 0.00937 -0.0198 1.0000 1.0000
-1.500 -0.0393 0.02054 0.00907 -0.0176 1.0000 1.0000
-1.250 -0.0308 0.02033 0.00883 -0.0151 1.0000 1.0000
-1.000 -0.0232 0.02015 0.00865 -0.0124 1.0000 1.0000
-0.750 -0.0164 0.02003 0.00849 -0.0095 1.0000 1.0000
-0.500 -0.0105 0.01994 0.00839 -0.0065 1.0000 1.0000
-0.250 -0.0051 0.01988 0.00834 -0.0033 1.0000 1.0000
0.000 0.0000 0.01987 0.00832 0.0000 1.0000 1.0000
0.250 0.0051 0.01988 0.00834 0.0033 1.0000 1.0000
0.500 0.0105 0.01994 0.00839 0.0065 1.0000 1.0000
0.750 0.0164 0.02002 0.00849 0.0095 1.0000 1.0000
1.000 0.0232 0.02015 0.00864 0.0124 1.0000 1.0000
1.250 0.0308 0.02032 0.00883 0.0151 1.0000 1.0000
1.500 0.0394 0.02054 0.00907 0.0176 1.0000 1.0000
1.750 0.0486 0.02080 0.00936 0.0198 1.0000 1.0000
2.000 0.0589 0.02111 0.00972 0.0218 1.0000 1.0000
2.250 0.0702 0.02149 0.01015 0.0235 1.0000 1.0000
2.500 0.0823 0.02192 0.01066 0.0250 1.0000 1.0000
2.750 0.0950 0.02242 0.01129 0.0262 1.0000 1.0000
3.000 0.1082 0.02300 0.01197 0.0271 1.0000 1.0000
3.250 0.1215 0.02366 0.01275 0.0279 1.0000 1.0000
3.500 0.1349 0.02440 0.01362 0.0285 1.0000 1.0000
3.750 0.1509 0.02528 0.01466 0.0283 0.9989 1.0000
4.000 0.2270 0.02702 0.01698 0.0166 0.9717 1.0000
4.250 0.3031 0.02840 0.01899 0.0058 0.9412 1.0000
4.500 0.5139 0.02474 0.01307 -0.0022 0.1460 1.0000
4.750 0.5367 0.02656 0.01480 -0.0006 0.1276 1.0000
5.000 0.5687 0.02859 0.01680 -0.0002 0.1147 1.0000
5.250 0.5991 0.03085 0.01909 0.0001 0.1032 1.0000
5.500 0.6281 0.03316 0.02174 0.0011 0.1010 1.0000
5.750 0.6537 0.03577 0.02475 0.0024 0.1008 1.0000
6.000 0.6766 0.03880 0.02812 0.0040 0.1018 1.0000
6.250 0.6960 0.04196 0.03164 0.0059 0.1024 1.0000
6.500 0.7115 0.04507 0.03516 0.0081 0.1025 1.0000
6.750 0.7209 0.04752 0.03847 0.0117 0.1063 1.0000
7.000 0.7284 0.05137 0.04287 0.0146 0.1124 1.0000
7.250 0.7331 0.05551 0.04761 0.0174 0.1233 1.0000
7.500 0.7342 0.06039 0.05299 0.0196 0.1385 1.0000
7.750 0.7261 0.06618 0.05930 0.0206 0.1627 1.0000
8.000 0.6661 0.06047 0.05411 0.0254 0.1699 1.0000
8.250 0.6185 0.06526 0.05909 0.0269 0.1748 1.0000
8.500 0.5738 0.07250 0.06634 0.0247 0.2007 1.0000
8.750 0.5065 0.08459 0.07825 0.0132 0.2618 1.0000
9.000 0.5755 0.10446 0.09763 -0.0113 0.3786 1.0000
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Polar data table (+)
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