Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

NACA 4415 (naca4415-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NACA 4415 (naca4415-il)
Reynolds number: 1,000,000
Max Cl/Cd: 119.37 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca4415-il-1000000.txt
Download as CSV file: xf-naca4415-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 4415                                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -16.500  -0.8197   0.08120   0.07821  -0.0728   1.0000   0.0145
 -16.250  -0.8474   0.07460   0.07153  -0.0758   1.0000   0.0144
 -16.000  -0.8819   0.06723   0.06407  -0.0791   1.0000   0.0145
 -15.750  -0.9187   0.05986   0.05658  -0.0822   1.0000   0.0143
 -15.500  -0.9634   0.05142   0.04800  -0.0859   1.0000   0.0142
 -15.250  -1.0030   0.04293   0.03935  -0.0904   1.0000   0.0142
 -15.000  -1.0357   0.03638   0.03261  -0.0939   1.0000   0.0142
 -14.750  -1.0300   0.03186   0.02793  -0.1005   0.9976   0.0143
 -14.500  -1.0184   0.02927   0.02521  -0.1040   0.9949   0.0144
 -14.250  -1.0048   0.02746   0.02329  -0.1056   0.9925   0.0146
 -14.000  -0.9920   0.02610   0.02184  -0.1056   0.9887   0.0148
 -13.750  -0.9733   0.02498   0.02063  -0.1060   0.9859   0.0151
 -13.500  -0.9512   0.02391   0.01948  -0.1068   0.9840   0.0153
 -13.250  -0.9245   0.02288   0.01835  -0.1082   0.9829   0.0156
 -13.000  -0.9100   0.02206   0.01746  -0.1065   0.9772   0.0158
 -12.750  -0.8837   0.02125   0.01657  -0.1072   0.9749   0.0161
 -12.500  -0.8600   0.01997   0.01521  -0.1080   0.9729   0.0165
 -12.250  -0.8324   0.01899   0.01418  -0.1090   0.9717   0.0170
 -12.000  -0.8121   0.01834   0.01348  -0.1081   0.9676   0.0174
 -11.750  -0.7880   0.01768   0.01277  -0.1080   0.9641   0.0177
 -11.500  -0.7592   0.01704   0.01208  -0.1087   0.9622   0.0183
 -11.250  -0.7290   0.01640   0.01138  -0.1096   0.9608   0.0187
 -11.000  -0.6970   0.01583   0.01074  -0.1108   0.9596   0.0191
 -10.750  -0.6659   0.01496   0.00983  -0.1121   0.9582   0.0200
 -10.500  -0.6468   0.01450   0.00934  -0.1105   0.9520   0.0206
 -10.250  -0.6155   0.01401   0.00880  -0.1115   0.9490   0.0214
 -10.000  -0.5811   0.01357   0.00831  -0.1131   0.9468   0.0225
  -9.750  -0.5458   0.01294   0.00767  -0.1150   0.9447   0.0239
  -9.500  -0.5198   0.01258   0.00727  -0.1147   0.9389   0.0253
  -9.250  -0.4913   0.01211   0.00677  -0.1150   0.9334   0.0268
  -9.000  -0.4561   0.01168   0.00631  -0.1168   0.9297   0.0288
  -8.750  -0.4324   0.01134   0.00593  -0.1160   0.9223   0.0308
  -8.500  -0.4028   0.01100   0.00556  -0.1164   0.9160   0.0334
  -8.250  -0.3752   0.01065   0.00519  -0.1164   0.9094   0.0363
  -8.000  -0.3502   0.01039   0.00490  -0.1158   0.9013   0.0392
  -7.750  -0.3223   0.01010   0.00459  -0.1158   0.8943   0.0435
  -7.500  -0.2994   0.00983   0.00432  -0.1148   0.8853   0.0485
  -7.250  -0.2727   0.00959   0.00407  -0.1145   0.8777   0.0552
  -7.000  -0.2495   0.00938   0.00387  -0.1135   0.8687   0.0621
  -6.750  -0.2237   0.00919   0.00366  -0.1130   0.8605   0.0690
  -6.500  -0.2001   0.00902   0.00350  -0.1120   0.8513   0.0753
  -6.250  -0.1743   0.00890   0.00334  -0.1115   0.8431   0.0807
  -6.000  -0.1506   0.00875   0.00319  -0.1105   0.8338   0.0867
  -5.750  -0.1256   0.00865   0.00305  -0.1098   0.8250   0.0922
  -5.500  -0.1015   0.00853   0.00293  -0.1088   0.8155   0.0981
  -5.250  -0.0770   0.00843   0.00280  -0.1080   0.8067   0.1044
  -5.000  -0.0529   0.00834   0.00270  -0.1071   0.7968   0.1103
  -4.750  -0.0287   0.00824   0.00258  -0.1062   0.7876   0.1166
  -4.500  -0.0047   0.00816   0.00248  -0.1052   0.7776   0.1228
  -4.250   0.0193   0.00808   0.00238  -0.1042   0.7678   0.1296
  -4.000   0.0430   0.00802   0.00229  -0.1032   0.7574   0.1369
  -3.750   0.0670   0.00793   0.00220  -0.1022   0.7472   0.1450
  -3.500   0.0906   0.00789   0.00213  -0.1012   0.7366   0.1536
  -3.250   0.1140   0.00780   0.00206  -0.1001   0.7258   0.1651
  -3.000   0.1377   0.00776   0.00199  -0.0991   0.7155   0.1746
  -2.500   0.1842   0.00766   0.00188  -0.0969   0.6930   0.1964
  -2.250   0.2074   0.00763   0.00183  -0.0957   0.6825   0.2087
  -1.750   0.2539   0.00756   0.00177  -0.0935   0.6602   0.2364
  -1.500   0.2763   0.00755   0.00175  -0.0922   0.6490   0.2522
  -1.250   0.2997   0.00751   0.00173  -0.0912   0.6382   0.2685
  -1.000   0.3225   0.00750   0.00172  -0.0900   0.6277   0.2849
  -0.750   0.3449   0.00749   0.00172  -0.0887   0.6168   0.3027
  -0.500   0.3681   0.00746   0.00171  -0.0876   0.6067   0.3221
  -0.250   0.3897   0.00746   0.00172  -0.0862   0.5965   0.3452
   0.000   0.4126   0.00741   0.00173  -0.0850   0.5868   0.3731
   0.250   0.4333   0.00735   0.00175  -0.0835   0.5774   0.4124
   0.500   0.4538   0.00722   0.00177  -0.0818   0.5683   0.4721
   0.750   0.4718   0.00708   0.00182  -0.0797   0.5596   0.5474
   1.000   0.4892   0.00693   0.00187  -0.0774   0.5512   0.6234
   1.250   0.5050   0.00685   0.00192  -0.0747   0.5427   0.6827
   1.500   0.5212   0.00672   0.00197  -0.0720   0.5349   0.7462
   1.750   0.5341   0.00659   0.00206  -0.0686   0.5265   0.8279
   2.000   0.6481   0.00672   0.00241  -0.0877   0.5139   0.9364
   2.250   0.7151   0.00699   0.00263  -0.0963   0.5038   0.9585
   2.500   0.7486   0.00719   0.00278  -0.0974   0.4953   0.9744
   2.750   0.7821   0.00737   0.00292  -0.0986   0.4871   0.9846
   3.000   0.8209   0.00758   0.00305  -0.1010   0.4761   0.9909
   3.250   0.8611   0.00775   0.00317  -0.1038   0.4652   0.9951
   3.500   0.9034   0.00792   0.00327  -0.1070   0.4549   0.9984
   3.750   0.9405   0.00803   0.00335  -0.1091   0.4460   1.0000
   4.000   0.9571   0.00816   0.00344  -0.1067   0.4384   1.0000
   4.250   0.9761   0.00824   0.00351  -0.1049   0.4315   1.0000
   4.500   0.9928   0.00838   0.00361  -0.1026   0.4237   1.0000
   4.750   1.0113   0.00849   0.00370  -0.1006   0.4165   1.0000
   5.000   1.0270   0.00862   0.00380  -0.0980   0.4085   1.0000
   5.250   1.0420   0.00874   0.00390  -0.0953   0.4012   1.0000
   5.500   1.0576   0.00886   0.00400  -0.0927   0.3936   1.0000
   5.750   1.0730   0.00901   0.00412  -0.0901   0.3858   1.0000
   6.000   1.0903   0.00915   0.00424  -0.0880   0.3775   1.0000
   6.250   1.1061   0.00933   0.00439  -0.0855   0.3685   1.0000
   6.500   1.1232   0.00951   0.00454  -0.0833   0.3594   1.0000
   6.750   1.1403   0.00970   0.00471  -0.0812   0.3505   1.0000
   7.000   1.1572   0.00992   0.00490  -0.0790   0.3407   1.0000
   7.250   1.1745   0.01014   0.00509  -0.0770   0.3304   1.0000
   7.500   1.1908   0.01041   0.00531  -0.0748   0.3196   1.0000
   7.750   1.2073   0.01070   0.00555  -0.0728   0.3070   1.0000
   8.000   1.2236   0.01101   0.00581  -0.0707   0.2935   1.0000
   8.250   1.2385   0.01139   0.00612  -0.0684   0.2779   1.0000
   8.500   1.2537   0.01178   0.00645  -0.0662   0.2630   1.0000
   8.750   1.2671   0.01226   0.00683  -0.0638   0.2460   1.0000
   9.000   1.2816   0.01271   0.00722  -0.0616   0.2314   1.0000
   9.250   1.2960   0.01318   0.00764  -0.0595   0.2183   1.0000
   9.500   1.3097   0.01370   0.00809  -0.0573   0.2051   1.0000
   9.750   1.3236   0.01423   0.00857  -0.0552   0.1938   1.0000
  10.000   1.3374   0.01478   0.00907  -0.0531   0.1827   1.0000
  10.250   1.3519   0.01531   0.00958  -0.0512   0.1730   1.0000
  10.500   1.3649   0.01592   0.01015  -0.0492   0.1635   1.0000
  10.750   1.3786   0.01653   0.01073  -0.0473   0.1557   1.0000
  11.000   1.3925   0.01713   0.01134  -0.0455   0.1489   1.0000
  11.250   1.4054   0.01781   0.01199  -0.0437   0.1422   1.0000
  11.500   1.4188   0.01849   0.01267  -0.0420   0.1363   1.0000
  11.750   1.4320   0.01919   0.01337  -0.0403   0.1308   1.0000
  12.000   1.4434   0.02001   0.01418  -0.0385   0.1251   1.0000
  12.250   1.4568   0.02074   0.01493  -0.0370   0.1205   1.0000
  12.500   1.4675   0.02166   0.01584  -0.0352   0.1151   1.0000
  12.750   1.4798   0.02250   0.01671  -0.0338   0.1107   1.0000
  13.000   1.4905   0.02346   0.01768  -0.0322   0.1057   1.0000
  13.250   1.4998   0.02455   0.01877  -0.0306   0.1004   1.0000
  13.500   1.5095   0.02565   0.01987  -0.0291   0.0951   1.0000
  13.750   1.5168   0.02696   0.02117  -0.0276   0.0893   1.0000
  14.000   1.5230   0.02837   0.02258  -0.0260   0.0828   1.0000
  14.250   1.5290   0.02986   0.02407  -0.0246   0.0768   1.0000
  14.500   1.5324   0.03161   0.02581  -0.0231   0.0707   1.0000
  14.750   1.5343   0.03353   0.02772  -0.0216   0.0646   1.0000
  15.000   1.5372   0.03544   0.02964  -0.0204   0.0597   1.0000
  15.250   1.5382   0.03759   0.03180  -0.0192   0.0554   1.0000
  15.500   1.5397   0.03977   0.03402  -0.0182   0.0518   1.0000
  15.750   1.5401   0.04210   0.03637  -0.0173   0.0490   1.0000
  16.000   1.5418   0.04438   0.03871  -0.0166   0.0467   1.0000
  16.250   1.5405   0.04702   0.04138  -0.0159   0.0447   1.0000
  16.500   1.5404   0.04962   0.04404  -0.0154   0.0430   1.0000
  16.750   1.5425   0.05202   0.04650  -0.0151   0.0417   1.0000
  17.000   1.5411   0.05484   0.04938  -0.0147   0.0404   1.0000
  17.250   1.5371   0.05802   0.05261  -0.0145   0.0390   1.0000
  17.500   1.5326   0.06134   0.05599  -0.0145   0.0378   1.0000
  17.750   1.5334   0.06407   0.05881  -0.0145   0.0371   1.0000
  18.000   1.5317   0.06713   0.06195  -0.0146   0.0363   1.0000
  18.250   1.5284   0.07045   0.06534  -0.0148   0.0356   1.0000
  18.500   1.5237   0.07399   0.06894  -0.0151   0.0349   1.0000
  18.750   1.5167   0.07784   0.07286  -0.0156   0.0342   1.0000
  19.000   1.5073   0.08207   0.07717  -0.0162   0.0335   1.0000
  19.250   1.4995   0.08616   0.08134  -0.0170   0.0329   1.0000
<< Back to NACA 4415 (naca4415-il)

Polar data table (+)

Polar graphs


<< Back to NACA 4415 (naca4415-il)