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NACA 64(2)-415 (naca642415-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NACA 64(2)-415 (naca642415-il)
Reynolds number: 50,000
Max Cl/Cd: 27.25 at α=9.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca642415-il-50000.txt
Download as CSV file: xf-naca642415-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64(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  -0.3371   0.10783   0.10061  -0.0284   1.0000   0.3655
  -9.500  -0.4969   0.08164   0.07492  -0.0560   1.0000   0.1729
  -9.250  -0.5063   0.07719   0.07054  -0.0559   1.0000   0.1661
  -9.000  -0.6108   0.07306   0.06659  -0.0527   1.0000   0.1572
  -8.750  -0.6327   0.07026   0.06376  -0.0498   1.0000   0.1532
  -8.500  -0.6495   0.06728   0.06077  -0.0470   1.0000   0.1503
  -8.250  -0.6745   0.06399   0.05736  -0.0442   1.0000   0.1470
  -8.000  -0.7193   0.06009   0.05261  -0.0415   1.0000   0.1400
  -7.750  -0.7161   0.05673   0.04914  -0.0399   1.0000   0.1390
  -7.500  -0.7148   0.05362   0.04575  -0.0384   1.0000   0.1385
  -7.250  -0.7108   0.05067   0.04243  -0.0371   1.0000   0.1386
  -7.000  -0.7025   0.04785   0.03922  -0.0360   1.0000   0.1387
  -6.750  -0.6906   0.04519   0.03616  -0.0350   1.0000   0.1389
  -6.500  -0.6756   0.04277   0.03332  -0.0342   1.0000   0.1392
  -6.250  -0.6589   0.04044   0.03071  -0.0335   1.0000   0.1415
  -6.000  -0.6414   0.03868   0.02894  -0.0326   1.0000   0.1462
  -5.750  -0.6228   0.03710   0.02711  -0.0318   1.0000   0.1504
  -5.500  -0.6030   0.03567   0.02530  -0.0308   1.0000   0.1546
  -5.250  -0.5845   0.03427   0.02397  -0.0297   1.0000   0.1617
  -5.000  -0.5651   0.03328   0.02278  -0.0286   1.0000   0.1708
  -4.750  -0.5473   0.03218   0.02188  -0.0270   1.0000   0.1810
  -4.500  -0.5298   0.03125   0.02106  -0.0255   1.0000   0.1961
  -4.250  -0.5124   0.03024   0.02014  -0.0241   1.0000   0.2194
  -4.000  -0.4951   0.02856   0.01905  -0.0235   1.0000   0.2687
  -3.750  -0.4942   0.02783   0.02069  -0.0166   1.0000   0.5819
  -3.500  -0.4959   0.02991   0.02276  -0.0076   1.0000   0.6581
  -3.250  -0.4968   0.03136   0.02419   0.0006   1.0000   0.6962
  -3.000  -0.4912   0.03277   0.02550   0.0074   0.9970   0.7318
  -2.750  -0.4812   0.03408   0.02669   0.0134   0.9919   0.7661
  -2.500  -0.4715   0.03506   0.02754   0.0191   0.9868   0.7991
  -2.250  -0.4592   0.03614   0.02851   0.0249   0.9817   0.8393
  -2.000  -0.3803   0.03877   0.03078   0.0219   0.9741   0.8981
  -1.750  -0.3181   0.03943   0.03110   0.0146   0.9680   0.9189
  -1.500  -0.2576   0.03972   0.03111   0.0066   0.9619   0.9303
  -1.250  -0.1950   0.04019   0.03131  -0.0021   0.9557   0.9404
  -1.000  -0.1618   0.04015   0.03113  -0.0056   0.9504   0.9501
  -0.750  -0.1258   0.04031   0.03114  -0.0097   0.9455   0.9599
  -0.500  -0.0663   0.04088   0.03153  -0.0181   0.9401   0.9682
  -0.250  -0.0348   0.04100   0.03156  -0.0216   0.9356   0.9766
   0.000   0.0031   0.04132   0.03179  -0.0263   0.9307   0.9852
   0.250   0.0494   0.04188   0.03226  -0.0326   0.9261   0.9937
   0.500   0.0810   0.04238   0.03269  -0.0363   0.9221   1.0000
   0.750   0.0722   0.04241   0.03270  -0.0329   0.9204   1.0000
   1.000   0.0630   0.04241   0.03268  -0.0295   0.9200   1.0000
   1.250   0.0525   0.04236   0.03262  -0.0260   0.9211   1.0000
   1.500  -0.1326   0.03630   0.02678   0.0071   1.0000   1.0000
   1.750  -0.1243   0.03611   0.02651   0.0074   1.0000   1.0000
   2.000  -0.1079   0.03637   0.02670   0.0062   1.0000   1.0000
   2.250  -0.0870   0.03694   0.02719   0.0043   1.0000   1.0000
   2.500  -0.0638   0.03772   0.02789   0.0021   1.0000   1.0000
   2.750  -0.0400   0.03865   0.02874  -0.0002   1.0000   1.0000
   3.000  -0.0160   0.03968   0.02971  -0.0024   1.0000   1.0000
   3.250   0.0075   0.04080   0.03076  -0.0045   1.0000   1.0000
   3.500   0.0304   0.04198   0.03190  -0.0065   1.0000   1.0000
   3.750   0.0526   0.04323   0.03310  -0.0083   1.0000   1.0000
   4.000   0.0739   0.04453   0.03437  -0.0099   1.0000   1.0000
   4.250   0.0947   0.04590   0.03572  -0.0115   0.9999   1.0000
   4.500   0.1327   0.04852   0.03833  -0.0164   0.9898   1.0000
   4.750   0.1698   0.05113   0.04096  -0.0211   0.9767   1.0000
   5.000   0.2043   0.05360   0.04346  -0.0252   0.9618   1.0000
   5.250   0.2368   0.05600   0.04589  -0.0288   0.9461   1.0000
   5.500   0.2684   0.05839   0.04835  -0.0322   0.9293   1.0000
   5.750   0.2990   0.06079   0.05081  -0.0353   0.9118   1.0000
   6.000   0.3300   0.06329   0.05339  -0.0383   0.8938   1.0000
   6.250   0.3653   0.06631   0.05651  -0.0419   0.8748   1.0000
   6.500   0.3892   0.06849   0.05878  -0.0436   0.8563   1.0000
   6.750   0.4063   0.06993   0.06032  -0.0441   0.8331   1.0000
   7.000   0.4502   0.07328   0.06382  -0.0481   0.8065   1.0000
   7.250   0.5727   0.06964   0.06047  -0.0497   0.6724   1.0000
   7.500   0.6009   0.07044   0.06143  -0.0497   0.6475   1.0000
   7.750   0.6359   0.07087   0.06204  -0.0497   0.6217   1.0000
   8.000   0.7001   0.06936   0.06085  -0.0501   0.5943   1.0000
   8.250   0.7146   0.06983   0.06148  -0.0485   0.5673   1.0000
   8.500   0.7613   0.06762   0.05957  -0.0468   0.5379   1.0000
   8.750   0.8447   0.05984   0.05230  -0.0432   0.5042   1.0000
   9.000   0.9879   0.03842   0.03168  -0.0329   0.4313   1.0000
   9.250   0.9959   0.03655   0.02823  -0.0253   0.2875   1.0000
   9.500   0.9925   0.03940   0.03018  -0.0221   0.2332   1.0000
   9.750   1.0067   0.04176   0.03211  -0.0203   0.1945   1.0000
  10.000   1.0494   0.04363   0.03368  -0.0203   0.1636   1.0000
  10.250   1.1150   0.04632   0.03619  -0.0232   0.1415   1.0000
  10.500   1.1684   0.04991   0.03978  -0.0263   0.1291   1.0000
  10.750   1.1785   0.05261   0.04295  -0.0246   0.1241   1.0000
  11.000   1.2061   0.05596   0.04645  -0.0250   0.1188   1.0000
  11.250   1.2289   0.06025   0.05090  -0.0253   0.1154   1.0000
  11.500   1.2232   0.06343   0.05453  -0.0226   0.1143   1.0000
  11.750   1.2118   0.06663   0.05810  -0.0196   0.1135   1.0000
  12.000   1.1969   0.07010   0.06190  -0.0170   0.1129   1.0000
  12.250   1.1790   0.07395   0.06605  -0.0149   0.1128   1.0000
  12.500   1.1581   0.07823   0.07061  -0.0135   0.1130   1.0000
  12.750   1.1352   0.08303   0.07566  -0.0129   0.1135   1.0000
  13.000   1.1106   0.08846   0.08130  -0.0131   0.1141   1.0000
  13.250   1.0867   0.09448   0.08750  -0.0142   0.1149   1.0000
  13.500   1.0651   0.10105   0.09420  -0.0159   0.1156   1.0000
  13.750   0.9209   0.12570   0.11915  -0.0327   0.1313   1.0000
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