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NACA 63-210 AIRFOIL (n63210-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
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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