NACA 63-210 AIRFOIL (n63210-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 63-210 AIRFOIL (n63210-il) Reynolds number: 50,000 Max Cl/Cd: 33.53 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n63210-il-50000.txt Download as CSV file: xf-n63210-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63-210 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4701 0.09748 0.09045 0.0051 1.0000 0.3846
-8.250 -0.4664 0.09438 0.08739 0.0052 1.0000 0.3973
-8.000 -0.4659 0.09154 0.08461 0.0053 1.0000 0.4100
-7.750 -0.4551 0.08759 0.08067 0.0047 1.0000 0.4141
-7.500 -0.4557 0.08413 0.07727 0.0038 1.0000 0.4136
-7.250 -0.6138 0.05895 0.05172 -0.0379 1.0000 0.1621
-7.000 -0.6030 0.05312 0.04552 -0.0386 1.0000 0.1462
-6.750 -0.5904 0.04890 0.04110 -0.0383 1.0000 0.1427
-6.500 -0.5789 0.04482 0.03656 -0.0380 1.0000 0.1388
-6.250 -0.5645 0.04133 0.03217 -0.0373 1.0000 0.1327
-6.000 -0.5456 0.03805 0.02863 -0.0364 1.0000 0.1304
-5.750 -0.5254 0.03522 0.02543 -0.0353 1.0000 0.1288
-5.500 -0.5040 0.03275 0.02258 -0.0342 1.0000 0.1283
-5.250 -0.4819 0.03063 0.02011 -0.0330 1.0000 0.1290
-5.000 -0.4595 0.02896 0.01802 -0.0317 1.0000 0.1326
-4.750 -0.4380 0.02719 0.01632 -0.0304 1.0000 0.1390
-4.500 -0.4157 0.02582 0.01483 -0.0288 1.0000 0.1456
-4.250 -0.3948 0.02444 0.01353 -0.0270 1.0000 0.1530
-4.000 -0.3755 0.02322 0.01235 -0.0250 1.0000 0.1655
-3.750 -0.3576 0.02186 0.01110 -0.0233 1.0000 0.1907
-3.500 -0.3512 0.01839 0.01012 -0.0204 1.0000 0.4826
-3.250 -0.3605 0.01918 0.01156 -0.0085 1.0000 0.7099
-3.000 -0.3652 0.01999 0.01243 0.0015 1.0000 0.7777
-2.750 -0.1838 0.02306 0.01441 -0.0081 1.0000 0.9482
-2.500 -0.1089 0.02203 0.01291 -0.0183 1.0000 0.9726
-2.250 -0.0414 0.02096 0.01152 -0.0277 1.0000 0.9926
-2.000 -0.0165 0.02043 0.01089 -0.0298 1.0000 1.0000
-1.750 -0.0247 0.02034 0.01082 -0.0261 1.0000 1.0000
-1.500 -0.0371 0.02028 0.01077 -0.0218 1.0000 1.0000
-1.250 -0.0517 0.02018 0.01067 -0.0173 1.0000 1.0000
-1.000 -0.0676 0.01999 0.01048 -0.0128 1.0000 1.0000
-0.750 -0.0841 0.01972 0.01020 -0.0081 1.0000 1.0000
-0.500 -0.0975 0.01940 0.00983 -0.0040 1.0000 1.0000
-0.250 -0.0972 0.01926 0.00958 -0.0018 1.0000 1.0000
0.000 -0.0843 0.01934 0.00954 -0.0015 1.0000 1.0000
0.250 -0.0664 0.01958 0.00964 -0.0018 1.0000 1.0000
0.500 -0.0469 0.01991 0.00984 -0.0023 1.0000 1.0000
0.750 -0.0268 0.02031 0.01013 -0.0029 1.0000 1.0000
1.000 -0.0064 0.02077 0.01050 -0.0034 1.0000 1.0000
1.250 0.0138 0.02129 0.01095 -0.0040 1.0000 1.0000
1.500 0.0362 0.02191 0.01151 -0.0049 0.9988 1.0000
1.750 0.0811 0.02305 0.01264 -0.0100 0.9868 1.0000
2.000 0.1239 0.02415 0.01375 -0.0146 0.9746 1.0000
2.250 0.1645 0.02521 0.01485 -0.0187 0.9621 1.0000
2.500 0.2042 0.02626 0.01597 -0.0225 0.9491 1.0000
2.750 0.2424 0.02728 0.01708 -0.0259 0.9358 1.0000
3.000 0.2801 0.02829 0.01819 -0.0291 0.9218 1.0000
3.250 0.3172 0.02928 0.01934 -0.0320 0.9070 1.0000
3.500 0.3544 0.03025 0.02046 -0.0348 0.8913 1.0000
3.750 0.3945 0.03120 0.02161 -0.0378 0.8744 1.0000
4.000 0.4421 0.03210 0.02282 -0.0416 0.8565 1.0000
4.250 0.4708 0.03292 0.02386 -0.0423 0.8357 1.0000
4.500 0.5236 0.03334 0.02467 -0.0456 0.8120 1.0000
4.750 0.5772 0.03295 0.02478 -0.0473 0.7795 1.0000
5.000 0.6805 0.02243 0.01486 -0.0355 0.6538 1.0000
5.250 0.6853 0.02044 0.01240 -0.0248 0.4549 1.0000
5.500 0.6752 0.02437 0.01375 -0.0190 0.1948 1.0000
5.750 0.6915 0.02659 0.01556 -0.0172 0.1573 1.0000
6.000 0.7183 0.02844 0.01730 -0.0163 0.1405 1.0000
6.250 0.7524 0.03046 0.01926 -0.0161 0.1312 1.0000
6.500 0.7863 0.03262 0.02155 -0.0161 0.1252 1.0000
6.750 0.8188 0.03548 0.02438 -0.0163 0.1214 1.0000
7.000 0.8440 0.03781 0.02722 -0.0155 0.1183 1.0000
7.250 0.8670 0.04047 0.03034 -0.0147 0.1153 1.0000
7.500 0.8884 0.04369 0.03403 -0.0138 0.1152 1.0000
7.750 0.9068 0.04733 0.03814 -0.0128 0.1167 1.0000
8.000 0.9222 0.05134 0.04259 -0.0118 0.1188 1.0000
8.250 0.9398 0.05604 0.04753 -0.0114 0.1210 1.0000
8.500 0.9294 0.06054 0.05311 -0.0095 0.1283 1.0000
8.750 0.9361 0.06590 0.05871 -0.0091 0.1336 1.0000
9.000 0.9094 0.07169 0.06510 -0.0091 0.1420 1.0000
9.250 0.9018 0.07775 0.07135 -0.0099 0.1513 1.0000
9.500 0.8494 0.08420 0.07788 -0.0126 0.1556 1.0000
9.750 0.8109 0.09392 0.08756 -0.0204 0.1677 1.0000
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Polar data table (+)
Polar graphs
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