NACA 0010-34 (naca001034-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 0010-34 (naca001034-il) Reynolds number: 500,000 Max Cl/Cd: 43.86 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca001034-il-500000-n5.txt Download as CSV file: xf-naca001034-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.6635 0.07781 0.07566 -0.0268 1.0000 0.0035
-10.000 -0.6772 0.07025 0.06801 -0.0327 1.0000 0.0035
-9.750 -0.6915 0.06497 0.06263 -0.0352 1.0000 0.0034
-9.500 -0.7048 0.06089 0.05844 -0.0354 1.0000 0.0034
-9.250 -0.7167 0.05760 0.05503 -0.0337 1.0000 0.0033
-9.000 -0.7261 0.05474 0.05205 -0.0310 1.0000 0.0033
-8.750 -0.7294 0.05180 0.04898 -0.0286 1.0000 0.0033
-8.500 -0.7306 0.04903 0.04605 -0.0260 1.0000 0.0032
-8.250 -0.7304 0.04645 0.04333 -0.0231 1.0000 0.0032
-8.000 -0.7334 0.04362 0.04030 -0.0195 1.0000 0.0031
-7.750 -0.7440 0.03944 0.03584 -0.0144 1.0000 0.0030
-7.500 -0.7486 0.03583 0.03195 -0.0095 1.0000 0.0029
-7.250 -0.7458 0.03202 0.02778 -0.0058 0.9993 0.0029
-7.000 -0.7279 0.02760 0.02288 -0.0047 0.9966 0.0029
-6.750 -0.7060 0.02387 0.01868 -0.0041 0.9946 0.0028
-6.500 -0.6826 0.02092 0.01532 -0.0033 0.9920 0.0028
-6.250 -0.6568 0.01857 0.01263 -0.0031 0.9899 0.0029
-6.000 -0.6298 0.01673 0.01054 -0.0031 0.9880 0.0029
-5.750 -0.6020 0.01530 0.00884 -0.0034 0.9863 0.0030
-5.500 -0.5780 0.01389 0.00725 -0.0029 0.9829 0.0033
-5.250 -0.5525 0.01261 0.00579 -0.0027 0.9798 0.0048
-5.000 -0.5216 0.01212 0.00526 -0.0036 0.9778 0.0074
-4.750 -0.4899 0.01178 0.00491 -0.0049 0.9761 0.0105
-4.500 -0.4622 0.01158 0.00472 -0.0052 0.9718 0.0150
-4.250 -0.4324 0.01131 0.00439 -0.0059 0.9684 0.0173
-4.000 -0.4027 0.01079 0.00380 -0.0066 0.9656 0.0212
-3.750 -0.3752 0.01052 0.00347 -0.0067 0.9610 0.0235
-3.500 -0.3467 0.01028 0.00313 -0.0070 0.9564 0.0267
-3.250 -0.3178 0.00990 0.00284 -0.0075 0.9527 0.0510
-3.000 -0.2988 0.00881 0.00242 -0.0064 0.9455 0.2206
-2.750 -0.2779 0.00781 0.00210 -0.0056 0.9398 0.3917
-2.500 -0.2570 0.00717 0.00190 -0.0046 0.9325 0.5041
-2.250 -0.2343 0.00666 0.00175 -0.0037 0.9263 0.5988
-2.000 -0.2105 0.00640 0.00166 -0.0029 0.9186 0.6517
-1.750 -0.1847 0.00620 0.00157 -0.0024 0.9121 0.6936
-1.500 -0.1610 0.00599 0.00151 -0.0015 0.9032 0.7463
-1.250 -0.1358 0.00587 0.00150 -0.0008 0.8948 0.7844
-1.000 -0.1087 0.00581 0.00145 -0.0006 0.8860 0.8000
-0.750 -0.0817 0.00578 0.00142 -0.0004 0.8764 0.8134
-0.500 -0.0545 0.00575 0.00139 -0.0002 0.8673 0.8256
-0.250 -0.0272 0.00574 0.00137 -0.0001 0.8579 0.8368
0.000 0.0000 0.00573 0.00136 0.0000 0.8476 0.8476
0.250 0.0272 0.00574 0.00137 0.0001 0.8368 0.8579
0.500 0.0545 0.00575 0.00139 0.0002 0.8255 0.8673
0.750 0.0817 0.00578 0.00142 0.0004 0.8134 0.8765
1.000 0.1087 0.00581 0.00145 0.0006 0.8001 0.8860
1.250 0.1358 0.00587 0.00150 0.0008 0.7844 0.8948
1.500 0.1610 0.00599 0.00151 0.0015 0.7459 0.9033
1.750 0.1846 0.00620 0.00157 0.0024 0.6930 0.9121
2.000 0.2105 0.00640 0.00166 0.0029 0.6524 0.9186
2.250 0.2343 0.00666 0.00175 0.0037 0.5995 0.9263
2.500 0.2569 0.00718 0.00190 0.0046 0.5030 0.9325
2.750 0.2779 0.00780 0.00210 0.0056 0.3925 0.9398
3.000 0.2988 0.00880 0.00242 0.0064 0.2213 0.9456
3.250 0.3178 0.00990 0.00284 0.0075 0.0510 0.9528
3.500 0.3467 0.01028 0.00312 0.0070 0.0267 0.9564
3.750 0.3752 0.01052 0.00347 0.0067 0.0234 0.9610
4.000 0.4027 0.01079 0.00380 0.0066 0.0211 0.9656
4.250 0.4324 0.01131 0.00439 0.0059 0.0173 0.9685
4.500 0.4622 0.01158 0.00471 0.0052 0.0150 0.9718
4.750 0.4899 0.01178 0.00490 0.0049 0.0105 0.9761
5.000 0.5217 0.01212 0.00526 0.0036 0.0074 0.9778
5.250 0.5526 0.01260 0.00579 0.0026 0.0048 0.9798
5.500 0.5783 0.01385 0.00721 0.0028 0.0033 0.9830
5.750 0.6022 0.01530 0.00884 0.0033 0.0030 0.9864
6.000 0.6300 0.01673 0.01054 0.0030 0.0029 0.9880
6.250 0.6570 0.01859 0.01266 0.0030 0.0029 0.9899
6.500 0.6828 0.02093 0.01533 0.0033 0.0028 0.9921
6.750 0.7061 0.02388 0.01869 0.0041 0.0028 0.9946
7.000 0.7280 0.02761 0.02289 0.0047 0.0029 0.9966
7.250 0.7460 0.03204 0.02780 0.0057 0.0029 0.9993
7.500 0.7485 0.03583 0.03195 0.0096 0.0029 1.0000
7.750 0.7440 0.03944 0.03584 0.0144 0.0030 1.0000
8.000 0.7334 0.04363 0.04031 0.0195 0.0031 1.0000
8.250 0.7305 0.04646 0.04333 0.0231 0.0032 1.0000
8.500 0.7307 0.04904 0.04607 0.0260 0.0032 1.0000
8.750 0.7297 0.05181 0.04899 0.0286 0.0033 1.0000
9.000 0.7265 0.05475 0.05207 0.0309 0.0033 1.0000
9.250 0.7171 0.05764 0.05507 0.0336 0.0033 1.0000
9.500 0.7054 0.06093 0.05848 0.0353 0.0034 1.0000
9.750 0.6920 0.06504 0.06270 0.0351 0.0034 1.0000
10.000 0.6778 0.07032 0.06808 0.0326 0.0035 1.0000
10.250 0.6642 0.07797 0.07583 0.0265 0.0035 1.0000
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Polar data table (+)
Polar graphs
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