NACA 65-210 (naca65210-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 65-210 (naca65210-il) Reynolds number: 50,000 Max Cl/Cd: 24.62 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca65210-il-50000.txt Download as CSV file: xf-naca65210-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65-210
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 -0.4673 0.09959 0.09260 -0.0036 1.0000 0.3775
-8.500 -0.4592 0.09661 0.08965 -0.0022 1.0000 0.4049
-8.250 -0.4635 0.09488 0.08801 -0.0007 1.0000 0.4302
-8.000 -0.4363 0.09014 0.08322 -0.0002 1.0000 0.4506
-6.750 -0.5234 0.07059 0.06441 -0.0111 1.0000 0.3606
-6.500 -0.5888 0.05524 0.04837 -0.0329 1.0000 0.1916
-6.250 -0.5831 0.05009 0.04245 -0.0332 1.0000 0.1559
-6.000 -0.5732 0.04636 0.03814 -0.0318 1.0000 0.1425
-5.750 -0.5605 0.04301 0.03447 -0.0303 1.0000 0.1383
-5.500 -0.5459 0.04043 0.03097 -0.0284 1.0000 0.1302
-5.250 -0.5282 0.03732 0.02768 -0.0270 1.0000 0.1270
-5.000 -0.5090 0.03470 0.02467 -0.0255 1.0000 0.1238
-4.750 -0.4880 0.03242 0.02196 -0.0240 1.0000 0.1220
-4.500 -0.4669 0.03056 0.01979 -0.0226 1.0000 0.1246
-4.250 -0.4452 0.02908 0.01792 -0.0211 1.0000 0.1294
-4.000 -0.4220 0.02733 0.01607 -0.0197 1.0000 0.1333
-3.750 -0.3991 0.02599 0.01471 -0.0180 1.0000 0.1390
-3.500 -0.3781 0.02483 0.01355 -0.0162 1.0000 0.1494
-3.250 -0.3590 0.02373 0.01250 -0.0146 1.0000 0.1677
-3.000 -0.0611 0.02214 0.01259 -0.0395 1.0000 1.0000
-2.750 -0.0592 0.02197 0.01234 -0.0367 1.0000 1.0000
-2.500 -0.0603 0.02186 0.01217 -0.0335 1.0000 1.0000
-2.250 -0.0636 0.02179 0.01205 -0.0300 1.0000 1.0000
-2.000 -0.0682 0.02173 0.01194 -0.0262 1.0000 1.0000
-1.750 -0.0734 0.02166 0.01181 -0.0225 1.0000 1.0000
-1.500 -0.0790 0.02156 0.01166 -0.0186 1.0000 1.0000
-1.250 -0.0848 0.02143 0.01149 -0.0148 1.0000 1.0000
-1.000 -0.0908 0.02127 0.01127 -0.0109 1.0000 1.0000
-0.750 -0.0966 0.02107 0.01099 -0.0071 1.0000 1.0000
-0.500 -0.1013 0.02085 0.01071 -0.0033 1.0000 1.0000
-0.250 -0.1030 0.02066 0.01044 0.0000 1.0000 1.0000
0.000 -0.0978 0.02059 0.01026 0.0022 1.0000 1.0000
0.250 -0.0859 0.02066 0.01021 0.0034 1.0000 1.0000
0.500 -0.0700 0.02084 0.01027 0.0039 1.0000 1.0000
0.750 -0.0522 0.02110 0.01042 0.0041 1.0000 1.0000
1.000 -0.0333 0.02143 0.01064 0.0042 1.0000 1.0000
1.250 -0.0139 0.02180 0.01093 0.0042 1.0000 1.0000
1.500 0.0059 0.02222 0.01129 0.0042 1.0000 1.0000
1.750 0.0257 0.02269 0.01171 0.0041 1.0000 1.0000
2.000 0.0456 0.02319 0.01219 0.0040 1.0000 1.0000
2.250 0.0655 0.02374 0.01273 0.0038 1.0000 1.0000
2.500 0.0852 0.02433 0.01332 0.0037 1.0000 1.0000
2.750 0.1048 0.02497 0.01398 0.0035 1.0000 1.0000
3.000 0.1241 0.02565 0.01469 0.0033 1.0000 1.0000
3.250 0.1432 0.02637 0.01549 0.0031 1.0000 1.0000
3.500 0.1685 0.02734 0.01654 0.0016 0.9967 1.0000
3.750 0.2162 0.02909 0.01846 -0.0041 0.9831 1.0000
4.000 0.2584 0.03056 0.02016 -0.0087 0.9679 1.0000
4.250 0.2982 0.03194 0.02177 -0.0127 0.9511 1.0000
4.500 0.3404 0.03335 0.02347 -0.0169 0.9321 1.0000
4.750 0.3861 0.03475 0.02525 -0.0213 0.9097 1.0000
5.000 0.4365 0.03592 0.02686 -0.0257 0.8815 1.0000
5.250 0.6160 0.02502 0.01381 -0.0140 0.1775 1.0000
5.500 0.6368 0.02684 0.01546 -0.0124 0.1532 1.0000
5.750 0.6730 0.02882 0.01729 -0.0126 0.1354 1.0000
6.000 0.7128 0.03098 0.01950 -0.0134 0.1229 1.0000
6.250 0.7514 0.03386 0.02247 -0.0141 0.1185 1.0000
6.500 0.7804 0.03637 0.02543 -0.0135 0.1159 1.0000
6.750 0.8050 0.03896 0.02842 -0.0126 0.1118 1.0000
7.000 0.8279 0.04205 0.03197 -0.0116 0.1114 1.0000
7.250 0.8476 0.04563 0.03612 -0.0102 0.1144 1.0000
7.500 0.8656 0.04966 0.04053 -0.0091 0.1179 1.0000
7.750 0.8748 0.05351 0.04520 -0.0070 0.1255 1.0000
8.000 0.8889 0.05855 0.05050 -0.0062 0.1324 1.0000
8.250 0.8873 0.06340 0.05604 -0.0046 0.1450 1.0000
8.500 0.8798 0.06904 0.06226 -0.0040 0.1640 1.0000
8.750 0.8663 0.07790 0.07155 -0.0065 0.2037 1.0000
9.000 0.8103 0.08264 0.07636 -0.0080 0.2072 1.0000
9.250 0.7611 0.09164 0.08525 -0.0159 0.2240 1.0000
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Polar data table (+)
Polar graphs
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