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NACA 64(2)-215 (naca642215-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NACA 64(2)-215 (naca642215-il)
Reynolds number: 50,000
Max Cl/Cd: 28.31 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca642215-il-50000.txt
Download as CSV file: xf-naca642215-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64(2)-215                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.5536   0.09246   0.08529  -0.0400   1.0000   0.1611
 -10.500  -0.5741   0.08368   0.07654  -0.0451   1.0000   0.1519
 -10.250  -0.6891   0.07305   0.06586  -0.0522   1.0000   0.1428
 -10.000  -0.6946   0.06866   0.06145  -0.0517   1.0000   0.1407
  -9.750  -0.7114   0.06453   0.05721  -0.0507   1.0000   0.1385
  -9.500  -0.7303   0.06066   0.05315  -0.0489   1.0000   0.1362
  -9.250  -0.7478   0.05708   0.04930  -0.0463   1.0000   0.1340
  -9.000  -0.7625   0.05394   0.04583  -0.0430   1.0000   0.1322
  -8.750  -0.7737   0.05127   0.04278  -0.0393   1.0000   0.1310
  -8.500  -0.7747   0.04885   0.04016  -0.0362   1.0000   0.1316
  -8.250  -0.7719   0.04670   0.03785  -0.0334   1.0000   0.1335
  -8.000  -0.7689   0.04466   0.03560  -0.0306   1.0000   0.1355
  -7.750  -0.7642   0.04263   0.03330  -0.0279   1.0000   0.1376
  -7.500  -0.7564   0.04061   0.03097  -0.0254   1.0000   0.1395
  -7.250  -0.7465   0.03877   0.02875  -0.0231   1.0000   0.1420
  -7.000  -0.7324   0.03687   0.02676  -0.0214   1.0000   0.1468
  -6.750  -0.7166   0.03537   0.02521  -0.0197   1.0000   0.1534
  -6.500  -0.6997   0.03395   0.02354  -0.0179   1.0000   0.1596
  -6.250  -0.6808   0.03259   0.02235  -0.0164   1.0000   0.1702
  -6.000  -0.6626   0.03139   0.02127  -0.0147   1.0000   0.1830
  -5.750  -0.6470   0.03024   0.02023  -0.0126   1.0000   0.2001
  -5.500  -0.6360   0.02892   0.01916  -0.0103   1.0000   0.2259
  -5.250  -0.6306   0.02702   0.01786  -0.0076   1.0000   0.2734
  -5.000  -0.6394   0.02566   0.01868  -0.0004   1.0000   0.5093
  -4.750  -0.6383   0.02863   0.02173   0.0092   1.0000   0.6117
  -4.500  -0.6320   0.03080   0.02379   0.0166   1.0000   0.6550
  -4.250  -0.6242   0.03268   0.02556   0.0237   1.0000   0.6878
  -4.000  -0.6137   0.03452   0.02730   0.0305   1.0000   0.7173
  -3.750  -0.5980   0.03640   0.02905   0.0369   1.0000   0.7476
  -3.500  -0.5736   0.03829   0.03076   0.0420   1.0000   0.7831
  -3.250  -0.4868   0.04122   0.03330   0.0384   1.0000   0.8297
  -3.000  -0.4621   0.04111   0.03298   0.0383   1.0000   0.8510
  -2.750  -0.4303   0.04090   0.03257   0.0364   1.0000   0.8677
  -2.500  -0.3866   0.04070   0.03215   0.0320   0.9991   0.8813
  -2.250  -0.3268   0.04065   0.03184   0.0241   0.9922   0.8927
  -2.000  -0.2908   0.04044   0.03146   0.0201   0.9851   0.9027
  -1.750  -0.2503   0.04028   0.03114   0.0154   0.9789   0.9119
  -1.500  -0.2092   0.04016   0.03087   0.0105   0.9725   0.9202
  -1.250  -0.1808   0.04003   0.03064   0.0079   0.9662   0.9288
  -1.000  -0.1359   0.03999   0.03047   0.0023   0.9596   0.9363
  -0.750  -0.1105   0.04002   0.03042   0.0001   0.9543   0.9445
  -0.500  -0.0729   0.03995   0.03029  -0.0042   0.9487   0.9513
  -0.250  -0.0393   0.04012   0.03039  -0.0079   0.9430   0.9590
   0.000  -0.0019   0.04021   0.03043  -0.0123   0.9375   0.9660
   0.250   0.0258   0.04035   0.03055  -0.0150   0.9326   0.9733
   0.500   0.0728   0.04072   0.03088  -0.0212   0.9271   0.9807
   0.750   0.1059   0.04096   0.03113  -0.0250   0.9218   0.9884
   1.000   0.1413   0.04131   0.03148  -0.0293   0.9165   0.9963
   1.250   0.1736   0.04181   0.03198  -0.0329   0.9110   1.0000
   1.500   0.1672   0.04205   0.03223  -0.0298   0.9069   1.0000
   1.750   0.1596   0.04222   0.03240  -0.0265   0.9031   1.0000
   2.000   0.1563   0.04244   0.03261  -0.0239   0.8995   1.0000
   2.250   0.1564   0.04273   0.03290  -0.0220   0.8962   1.0000
   2.500   0.1542   0.04302   0.03319  -0.0196   0.8932   1.0000
   2.750   0.1366   0.04292   0.03307  -0.0149   0.8928   1.0000
   3.000   0.0984   0.04214   0.03226  -0.0072   0.8994   1.0000
   3.250   0.0880   0.04215   0.03223  -0.0040   0.9044   1.0000
   3.500   0.0983   0.04292   0.03297  -0.0041   0.9074   1.0000
   3.750   0.1165   0.04413   0.03415  -0.0054   0.9097   1.0000
   5.250   0.2813   0.05235   0.04260  -0.0171   0.8246   1.0000
   5.500   0.3283   0.05380   0.04418  -0.0201   0.7930   1.0000
   5.750   0.3511   0.05487   0.04533  -0.0205   0.7712   1.0000
   6.000   0.4003   0.05610   0.04674  -0.0232   0.7434   1.0000
   6.250   0.4199   0.05710   0.04784  -0.0230   0.7213   1.0000
   6.500   0.4730   0.05781   0.04876  -0.0251   0.6947   1.0000
   6.750   0.4896   0.05863   0.04970  -0.0242   0.6702   1.0000
   7.000   0.5339   0.05861   0.04993  -0.0246   0.6419   1.0000
   7.250   0.5869   0.05735   0.04896  -0.0243   0.6110   1.0000
   7.500   0.6427   0.05454   0.04651  -0.0227   0.5769   1.0000
   8.000   0.8426   0.02976   0.02255  -0.0073   0.3893   1.0000
   8.250   0.8329   0.03136   0.02245  -0.0009   0.2730   1.0000
   8.500   0.8360   0.03390   0.02421   0.0019   0.2231   1.0000
   8.750   0.8647   0.03608   0.02600   0.0025   0.1862   1.0000
   9.000   0.9231   0.03864   0.02826  -0.0003   0.1585   1.0000
   9.250   0.9691   0.04141   0.03098  -0.0022   0.1443   1.0000
   9.500   0.9938   0.04380   0.03365  -0.0019   0.1358   1.0000
   9.750   1.0250   0.04708   0.03701  -0.0026   0.1297   1.0000
  10.000   1.0372   0.04997   0.04037  -0.0011   0.1266   1.0000
  10.250   1.0477   0.05295   0.04370   0.0002   0.1233   1.0000
  10.500   1.0614   0.05603   0.04697   0.0011   0.1200   1.0000
  10.750   1.0770   0.05985   0.05093   0.0015   0.1179   1.0000
  11.000   1.0770   0.06363   0.05506   0.0032   0.1178   1.0000
  11.250   1.0542   0.06699   0.05890   0.0064   0.1190   1.0000
  11.500   1.0192   0.07057   0.06285   0.0098   0.1205   1.0000
  11.750   0.9823   0.07519   0.06776   0.0112   0.1222   1.0000
  12.000   0.9437   0.08090   0.07371   0.0107   0.1242   1.0000
  12.250   0.9021   0.08809   0.08105   0.0082   0.1265   1.0000
  12.500   0.8703   0.09600   0.08905   0.0048   0.1288   1.0000
  12.750   0.8595   0.10295   0.09603   0.0023   0.1305   1.0000
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