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NACA 65(2)-415 (naca652415-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NACA 65(2)-415 (naca652415-il)
Reynolds number: 50,000
Max Cl/Cd: 23.93 at α=9°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca652415-il-50000.txt
Download as CSV file: xf-naca652415-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 65(2)-415                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3317   0.10869   0.10173  -0.0320   1.0000   0.3772
  -9.500  -0.3335   0.10628   0.09940  -0.0305   1.0000   0.3860
  -9.250  -0.3507   0.10545   0.09871  -0.0279   1.0000   0.3982
  -9.000  -0.3396   0.10216   0.09546  -0.0265   1.0000   0.4032
  -8.750  -0.3652   0.10191   0.09537  -0.0226   1.0000   0.4138
  -8.500  -0.5266   0.08761   0.08158  -0.0355   1.0000   0.2271
  -8.250  -0.6128   0.08490   0.07912  -0.0329   1.0000   0.2243
  -8.000  -0.6601   0.07741   0.07152  -0.0341   1.0000   0.1873
  -7.750  -0.7010   0.07224   0.06611  -0.0330   1.0000   0.1728
  -7.500  -0.7280   0.06705   0.06045  -0.0319   1.0000   0.1589
  -7.250  -0.7267   0.06293   0.05619  -0.0306   1.0000   0.1526
  -7.000  -0.7341   0.05857   0.05107  -0.0295   1.0000   0.1435
  -6.750  -0.7263   0.05517   0.04743  -0.0284   1.0000   0.1415
  -6.500  -0.7169   0.05191   0.04380  -0.0274   1.0000   0.1394
  -6.250  -0.7045   0.04873   0.04013  -0.0266   1.0000   0.1365
  -6.000  -0.6887   0.04580   0.03657  -0.0258   1.0000   0.1333
  -5.750  -0.6704   0.04346   0.03362  -0.0249   1.0000   0.1317
  -5.500  -0.6515   0.04139   0.03137  -0.0241   1.0000   0.1336
  -5.250  -0.6323   0.03971   0.02950  -0.0232   1.0000   0.1369
  -5.000  -0.6119   0.03817   0.02768  -0.0223   1.0000   0.1398
  -4.750  -0.5906   0.03680   0.02602  -0.0212   1.0000   0.1421
  -4.500  -0.5693   0.03571   0.02464  -0.0200   1.0000   0.1455
  -4.250  -0.5499   0.03454   0.02366  -0.0187   1.0000   0.1533
  -4.000  -0.5297   0.03379   0.02280  -0.0171   1.0000   0.1614
  -3.750  -0.5115   0.03296   0.02210  -0.0153   1.0000   0.1717
  -3.500  -0.4938   0.03212   0.02134  -0.0137   1.0000   0.1878
  -3.250  -0.4759   0.03095   0.02044  -0.0128   1.0000   0.2178
  -3.000  -0.4699   0.02812   0.02048  -0.0088   1.0000   0.5708
  -2.750  -0.4848   0.03039   0.02296   0.0054   1.0000   0.7326
  -2.500  -0.2426   0.04137   0.03280  -0.0067   1.0000   0.9691
  -2.250  -0.1940   0.04128   0.03240  -0.0133   1.0000   0.9841
  -2.000  -0.1475   0.04119   0.03203  -0.0197   1.0000   0.9960
  -1.750  -0.1300   0.04109   0.03178  -0.0207   1.0000   1.0000
  -1.500  -0.1280   0.04087   0.03147  -0.0187   1.0000   1.0000
  -1.250  -0.1261   0.04065   0.03116  -0.0167   1.0000   1.0000
  -1.000  -0.1243   0.04043   0.03086  -0.0146   1.0000   1.0000
  -0.750  -0.1226   0.04020   0.03055  -0.0125   1.0000   1.0000
  -0.500  -0.1211   0.03995   0.03023  -0.0103   1.0000   1.0000
  -0.250  -0.1198   0.03970   0.02991  -0.0081   1.0000   1.0000
   0.000  -0.1189   0.03942   0.02956  -0.0058   1.0000   1.0000
   0.250  -0.1184   0.03911   0.02919  -0.0035   1.0000   1.0000
   0.500  -0.1182   0.03876   0.02879  -0.0011   1.0000   1.0000
   0.750  -0.1185   0.03836   0.02835   0.0014   1.0000   1.0000
   1.000  -0.1190   0.03793   0.02786   0.0040   1.0000   1.0000
   1.250  -0.1197   0.03747   0.02735   0.0065   1.0000   1.0000
   1.500  -0.1196   0.03699   0.02683   0.0089   1.0000   1.0000
   1.750  -0.1175   0.03660   0.02640   0.0110   1.0000   1.0000
   2.000  -0.1094   0.03651   0.02624   0.0119   1.0000   1.0000
   2.250  -0.0956   0.03673   0.02640   0.0118   1.0000   1.0000
   2.500  -0.0782   0.03720   0.02680   0.0111   1.0000   1.0000
   2.750  -0.0588   0.03784   0.02739   0.0101   1.0000   1.0000
   3.000  -0.0383   0.03861   0.02811   0.0088   1.0000   1.0000
   3.250  -0.0173   0.03950   0.02894   0.0075   1.0000   1.0000
   3.500   0.0037   0.04047   0.02987   0.0061   1.0000   1.0000
   3.750   0.0246   0.04151   0.03089   0.0048   1.0000   1.0000
   4.000   0.0451   0.04262   0.03198   0.0035   1.0000   1.0000
   4.250   0.0653   0.04380   0.03314   0.0023   1.0000   1.0000
   4.500   0.0849   0.04504   0.03438   0.0011   1.0000   1.0000
   4.750   0.1041   0.04635   0.03570   0.0000   1.0000   1.0000
   5.000   0.1327   0.04842   0.03781  -0.0030   0.9955   1.0000
   5.250   0.1727   0.05150   0.04092  -0.0082   0.9840   1.0000
   5.500   0.2103   0.05446   0.04395  -0.0130   0.9706   1.0000
   5.750   0.2415   0.05685   0.04643  -0.0165   0.9554   1.0000
   6.000   0.2677   0.05873   0.04841  -0.0191   0.9376   1.0000
   6.250   0.2950   0.06082   0.05060  -0.0217   0.9187   1.0000
   6.500   0.3255   0.06325   0.05315  -0.0247   0.8986   1.0000
   6.750   0.3626   0.06636   0.05640  -0.0287   0.8785   1.0000
   7.000   0.3817   0.06810   0.05826  -0.0298   0.8576   1.0000
   7.250   0.4239   0.07116   0.06149  -0.0337   0.8289   1.0000
   7.500   0.5330   0.06869   0.05938  -0.0370   0.7063   1.0000
   7.750   0.5656   0.06937   0.06028  -0.0375   0.6780   1.0000
   8.000   0.6049   0.06969   0.06085  -0.0381   0.6506   1.0000
   8.250   0.6521   0.06906   0.06054  -0.0384   0.6215   1.0000
   8.500   0.7006   0.06687   0.05869  -0.0373   0.5873   1.0000
   8.750   0.8753   0.04357   0.03660  -0.0283   0.5160   1.0000
   9.000   0.8887   0.03713   0.02834  -0.0155   0.2687   1.0000
   9.250   0.8797   0.04035   0.03059  -0.0121   0.2100   1.0000
   9.500   0.8949   0.04241   0.03219  -0.0101   0.1724   1.0000
   9.750   0.9582   0.04339   0.03285  -0.0109   0.1419   1.0000
  10.000   1.0660   0.04653   0.03592  -0.0179   0.1218   1.0000
  10.250   1.1040   0.04954   0.03925  -0.0193   0.1147   1.0000
  10.500   1.1573   0.05447   0.04423  -0.0231   0.1101   1.0000
  10.750   1.1695   0.05773   0.04797  -0.0215   0.1094   1.0000
  11.000   1.1737   0.06100   0.05167  -0.0193   0.1088   1.0000
  11.250   1.1713   0.06424   0.05533  -0.0167   0.1082   1.0000
  11.500   1.1640   0.06751   0.05895  -0.0138   0.1079   1.0000
  11.750   1.1530   0.07093   0.06268  -0.0110   0.1079   1.0000
  12.000   1.1405   0.07463   0.06664  -0.0085   0.1082   1.0000
  12.250   1.1255   0.07864   0.07090  -0.0066   0.1086   1.0000
  12.500   1.1122   0.08309   0.07556  -0.0053   0.1093   1.0000
  12.750   1.1085   0.08829   0.08094  -0.0049   0.1102   1.0000
  13.000   0.9827   0.09633   0.08957  -0.0058   0.1168   1.0000
  13.250   0.9409   0.10537   0.09874  -0.0097   0.1205   1.0000
  13.500   0.9209   0.11334   0.10675  -0.0130   0.1226   1.0000
  13.750   0.9192   0.11986   0.11333  -0.0150   0.1242   1.0000
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