NACA 0010-35 (naca001035-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 0010-35 (naca001035-il) Reynolds number: 50,000 Max Cl/Cd: 17.63 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca001035-il-50000.txt Download as CSV file: xf-naca001035-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0010-35
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
------ -------- --------- --------- -------- -------- --------
-7.250 -0.6162 0.07714 0.07075 0.0049 1.0000 0.4268
-7.000 -0.6696 0.07371 0.06755 0.0075 1.0000 0.4114
-6.750 -0.7344 0.06763 0.06140 0.0043 1.0000 0.3405
-6.500 -0.7634 0.06005 0.05274 0.0003 1.0000 0.2182
-6.250 -0.7469 0.05356 0.04543 0.0015 1.0000 0.1540
-6.000 -0.7345 0.04952 0.04072 0.0047 1.0000 0.1299
-5.750 -0.7212 0.04606 0.03665 0.0080 1.0000 0.1172
-5.500 -0.7079 0.04304 0.03294 0.0114 1.0000 0.1114
-5.250 -0.6923 0.04112 0.03015 0.0149 1.0000 0.1091
-5.000 -0.6704 0.03802 0.02673 0.0165 1.0000 0.1083
-4.750 -0.2200 0.02832 0.01864 -0.0404 1.0000 1.0000
-4.500 -0.2090 0.02760 0.01759 -0.0390 1.0000 1.0000
-4.250 -0.1978 0.02696 0.01667 -0.0374 1.0000 1.0000
-4.000 -0.1864 0.02640 0.01579 -0.0357 1.0000 1.0000
-3.750 -0.1747 0.02591 0.01507 -0.0339 1.0000 1.0000
-3.500 -0.1629 0.02547 0.01443 -0.0321 1.0000 1.0000
-3.250 -0.1510 0.02509 0.01386 -0.0302 1.0000 1.0000
-3.000 -0.1391 0.02475 0.01336 -0.0281 1.0000 1.0000
-2.750 -0.1272 0.02445 0.01291 -0.0261 1.0000 1.0000
-2.500 -0.1154 0.02418 0.01252 -0.0239 1.0000 1.0000
-2.250 -0.1036 0.02395 0.01212 -0.0217 1.0000 1.0000
-2.000 -0.0919 0.02375 0.01182 -0.0194 1.0000 1.0000
-1.750 -0.0802 0.02358 0.01156 -0.0171 1.0000 1.0000
-1.500 -0.0687 0.02344 0.01134 -0.0147 1.0000 1.0000
-1.250 -0.0571 0.02332 0.01116 -0.0123 1.0000 1.0000
-1.000 -0.0457 0.02322 0.01101 -0.0099 1.0000 1.0000
-0.750 -0.0342 0.02315 0.01088 -0.0074 1.0000 1.0000
-0.500 -0.0228 0.02309 0.01080 -0.0050 1.0000 1.0000
-0.250 -0.0114 0.02306 0.01075 -0.0025 1.0000 1.0000
0.000 0.0000 0.02305 0.01073 0.0000 1.0000 1.0000
0.250 0.0114 0.02306 0.01075 0.0025 1.0000 1.0000
0.500 0.0228 0.02309 0.01080 0.0050 1.0000 1.0000
0.750 0.0342 0.02314 0.01088 0.0074 1.0000 1.0000
1.000 0.0456 0.02322 0.01101 0.0099 1.0000 1.0000
1.250 0.0571 0.02331 0.01115 0.0123 1.0000 1.0000
1.500 0.0687 0.02343 0.01133 0.0147 1.0000 1.0000
1.750 0.0802 0.02358 0.01155 0.0171 1.0000 1.0000
2.000 0.0919 0.02375 0.01181 0.0194 1.0000 1.0000
2.250 0.1036 0.02395 0.01211 0.0217 1.0000 1.0000
2.500 0.1154 0.02418 0.01251 0.0239 1.0000 1.0000
2.750 0.1272 0.02444 0.01290 0.0261 1.0000 1.0000
3.000 0.1391 0.02474 0.01335 0.0281 1.0000 1.0000
3.250 0.1510 0.02508 0.01385 0.0302 1.0000 1.0000
3.500 0.1629 0.02546 0.01442 0.0321 1.0000 1.0000
3.750 0.1747 0.02589 0.01506 0.0339 1.0000 1.0000
4.000 0.1864 0.02639 0.01578 0.0357 1.0000 1.0000
4.250 0.1979 0.02695 0.01665 0.0374 1.0000 1.0000
4.500 0.2091 0.02758 0.01757 0.0390 1.0000 1.0000
4.750 0.2201 0.02830 0.01861 0.0404 1.0000 1.0000
5.000 0.6703 0.03801 0.02672 -0.0165 0.1083 1.0000
5.250 0.6923 0.04111 0.03015 -0.0149 0.1091 1.0000
5.500 0.7080 0.04309 0.03295 -0.0115 0.1109 1.0000
5.750 0.7212 0.04605 0.03663 -0.0080 0.1172 1.0000
6.000 0.7345 0.04952 0.04072 -0.0047 0.1299 1.0000
6.250 0.7470 0.05355 0.04542 -0.0015 0.1539 1.0000
6.500 0.7533 0.05890 0.05173 0.0009 0.2099 1.0000
6.750 0.7331 0.06688 0.06064 -0.0032 0.3301 1.0000
7.000 0.6675 0.07449 0.06832 -0.0089 0.4238 1.0000
7.250 0.6184 0.07691 0.07053 -0.0042 0.4204 1.0000
7.500 0.5504 0.08230 0.07559 -0.0077 0.4901 1.0000
8.750 0.5387 0.09946 0.09246 -0.0021 0.4424 1.0000
9.000 0.5608 0.10355 0.09657 0.0003 0.4094 1.0000
9.250 0.5595 0.10610 0.09907 0.0028 0.3801 1.0000
9.500 0.5685 0.10952 0.10247 0.0049 0.3534 1.0000
9.750 0.5678 0.11234 0.10525 0.0064 0.3312 1.0000
10.000 0.5785 0.11645 0.10935 0.0079 0.3127 1.0000
10.250 0.5701 0.11906 0.11188 0.0085 0.2958 1.0000
10.500 0.5708 0.12231 0.11515 0.0092 0.2796 1.0000
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Polar data table (+)
Polar graphs
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