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

NACA 65(4)-421 (naca654421-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NACA 65(4)-421 (naca654421-il)
Reynolds number: 500,000
Max Cl/Cd: 91.05 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca654421-il-500000-n5.txt
Download as CSV file: xf-naca654421-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 65(4)-421                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -19.750  -0.8928   0.08986   0.08551  -0.0788   1.0000   0.0209
 -19.500  -0.8965   0.08599   0.08155  -0.0805   1.0000   0.0211
 -19.250  -0.8989   0.08236   0.07783  -0.0822   1.0000   0.0212
 -19.000  -0.9010   0.07889   0.07426  -0.0836   1.0000   0.0213
 -18.750  -0.9023   0.07562   0.07090  -0.0848   1.0000   0.0215
 -18.500  -0.9022   0.07260   0.06779  -0.0858   1.0000   0.0216
 -18.250  -0.9016   0.06967   0.06476  -0.0867   1.0000   0.0218
 -18.000  -0.8999   0.06697   0.06197  -0.0875   1.0000   0.0220
 -17.750  -0.8974   0.06442   0.05933  -0.0881   1.0000   0.0222
 -17.500  -0.8941   0.06205   0.05688  -0.0886   1.0000   0.0223
 -17.250  -0.8898   0.05981   0.05455  -0.0890   1.0000   0.0225
 -17.000  -0.8858   0.05754   0.05218  -0.0895   1.0000   0.0228
 -16.750  -0.8664   0.05509   0.04963  -0.0924   0.9686   0.0228
 -16.500  -0.8413   0.05250   0.04690  -0.0973   0.9550   0.0231
 -16.250  -0.8132   0.05025   0.04458  -0.1020   0.9434   0.0234
 -16.000  -0.7847   0.04810   0.04235  -0.1067   0.9294   0.0237
 -15.750  -0.7619   0.04628   0.04042  -0.1098   0.9122   0.0239
 -15.500  -0.7470   0.04473   0.03875  -0.1110   0.8943   0.0242
 -15.250  -0.7349   0.04341   0.03731  -0.1111   0.8793   0.0243
 -15.000  -0.7242   0.04211   0.03592  -0.1110   0.8669   0.0246
 -14.750  -0.7142   0.04083   0.03453  -0.1107   0.8557   0.0248
 -14.500  -0.7032   0.03965   0.03327  -0.1103   0.8462   0.0250
 -14.250  -0.6923   0.03851   0.03203  -0.1099   0.8369   0.0252
 -14.000  -0.6816   0.03734   0.03078  -0.1094   0.8287   0.0254
 -13.750  -0.6701   0.03626   0.02962  -0.1089   0.8200   0.0257
 -13.500  -0.6588   0.03519   0.02847  -0.1084   0.8125   0.0258
 -13.250  -0.6476   0.03412   0.02732  -0.1078   0.8043   0.0261
 -13.000  -0.6359   0.03313   0.02624  -0.1072   0.7972   0.0263
 -12.750  -0.6227   0.03221   0.02525  -0.1067   0.7907   0.0266
 -12.500  -0.6111   0.03121   0.02418  -0.1060   0.7841   0.0268
 -12.000  -0.5899   0.02917   0.02204  -0.1044   0.7721   0.0274
 -11.750  -0.5788   0.02821   0.02104  -0.1036   0.7658   0.0276
 -11.500  -0.5674   0.02733   0.02010  -0.1027   0.7597   0.0279
 -11.250  -0.5562   0.02641   0.01914  -0.1018   0.7543   0.0283
 -11.000  -0.5437   0.02559   0.01827  -0.1009   0.7484   0.0286
 -10.750  -0.5310   0.02482   0.01744  -0.1000   0.7429   0.0290
 -10.500  -0.5184   0.02404   0.01660  -0.0990   0.7382   0.0293
 -10.250  -0.5051   0.02329   0.01582  -0.0981   0.7334   0.0296
 -10.000  -0.4920   0.02255   0.01504  -0.0971   0.7284   0.0301
  -9.750  -0.4783   0.02189   0.01431  -0.0961   0.7238   0.0307
  -9.500  -0.4643   0.02123   0.01360  -0.0951   0.7194   0.0311
  -9.250  -0.4513   0.02052   0.01286  -0.0940   0.7149   0.0316
  -9.000  -0.4385   0.01983   0.01214  -0.0928   0.7100   0.0324
  -8.750  -0.4251   0.01920   0.01148  -0.0916   0.7056   0.0330
  -8.500  -0.4107   0.01863   0.01086  -0.0905   0.7019   0.0340
  -8.250  -0.3957   0.01807   0.01028  -0.0894   0.6981   0.0351
  -8.000  -0.3805   0.01754   0.00972  -0.0883   0.6942   0.0362
  -7.750  -0.3668   0.01698   0.00914  -0.0869   0.6904   0.0377
  -7.500  -0.3527   0.01646   0.00859  -0.0856   0.6868   0.0397
  -7.250  -0.3384   0.01596   0.00807  -0.0842   0.6834   0.0424
  -7.000  -0.3253   0.01543   0.00755  -0.0826   0.6798   0.0466
  -6.500  -0.3084   0.01431   0.00651  -0.0778   0.6724   0.0687
  -6.250  -0.3034   0.01385   0.00609  -0.0746   0.6692   0.0865
  -6.000  -0.2926   0.01333   0.00567  -0.0725   0.6663   0.1147
  -5.750  -0.2794   0.01277   0.00527  -0.0707   0.6636   0.1500
  -5.500  -0.2640   0.01222   0.00489  -0.0693   0.6607   0.1896
  -5.250  -0.2484   0.01160   0.00448  -0.0680   0.6578   0.2415
  -5.000  -0.2325   0.01087   0.00402  -0.0668   0.6549   0.3074
  -4.750  -0.2182   0.00990   0.00347  -0.0655   0.6521   0.4092
  -4.500  -0.1961   0.00946   0.00329  -0.0650   0.6494   0.4860
  -4.250  -0.1690   0.00935   0.00327  -0.0652   0.6469   0.5168
  -4.000  -0.1408   0.00932   0.00326  -0.0655   0.6444   0.5362
  -3.750  -0.1123   0.00933   0.00328  -0.0658   0.6420   0.5504
  -3.500  -0.0838   0.00937   0.00333  -0.0661   0.6395   0.5646
  -3.250  -0.0550   0.00944   0.00336  -0.0665   0.6372   0.5763
  -3.000  -0.0262   0.00947   0.00338  -0.0668   0.6349   0.5818
  -2.750   0.0028   0.00948   0.00333  -0.0672   0.6328   0.5844
  -2.500   0.0319   0.00949   0.00328  -0.0677   0.6306   0.5869
  -2.250   0.0611   0.00948   0.00324  -0.0682   0.6284   0.5890
  -2.000   0.0903   0.00947   0.00320  -0.0687   0.6260   0.5909
  -1.750   0.1193   0.00946   0.00317  -0.0691   0.6237   0.5930
  -1.500   0.1482   0.00945   0.00316  -0.0695   0.6215   0.5950
  -1.250   0.1772   0.00946   0.00315  -0.0700   0.6195   0.5969
  -1.000   0.2061   0.00947   0.00315  -0.0704   0.6175   0.5988
  -0.750   0.2352   0.00950   0.00314  -0.0709   0.6155   0.6008
  -0.250   0.2933   0.00955   0.00316  -0.0718   0.6117   0.6054
   0.000   0.3223   0.00957   0.00318  -0.0723   0.6096   0.6075
   0.250   0.3513   0.00959   0.00319  -0.0727   0.6074   0.6093
   0.500   0.3801   0.00960   0.00322  -0.0732   0.6053   0.6111
   0.750   0.4088   0.00962   0.00325  -0.0736   0.6034   0.6130
   1.000   0.4375   0.00965   0.00330  -0.0740   0.6015   0.6149
   1.250   0.4663   0.00969   0.00334  -0.0744   0.5996   0.6172
   1.500   0.4951   0.00975   0.00339  -0.0748   0.5976   0.6196
   1.750   0.5240   0.00981   0.00345  -0.0753   0.5956   0.6219
   2.000   0.5525   0.00985   0.00352  -0.0756   0.5938   0.6241
   2.250   0.5810   0.00989   0.00359  -0.0760   0.5919   0.6262
   2.500   0.6095   0.00995   0.00366  -0.0764   0.5899   0.6281
   2.750   0.6378   0.00999   0.00374  -0.0768   0.5878   0.6302
   3.000   0.6658   0.01003   0.00383  -0.0771   0.5856   0.6323
   3.250   0.6940   0.01009   0.00392  -0.0774   0.5835   0.6346
   3.500   0.7223   0.01015   0.00401  -0.0777   0.5816   0.6372
   3.750   0.7508   0.01024   0.00411  -0.0781   0.5796   0.6399
   4.000   0.7787   0.01032   0.00423  -0.0784   0.5774   0.6426
   4.250   0.8057   0.01038   0.00435  -0.0785   0.5745   0.6451
   4.500   0.8325   0.01043   0.00445  -0.0786   0.5708   0.6473
   4.750   0.8589   0.01048   0.00454  -0.0786   0.5670   0.6498
   5.000   0.8853   0.01054   0.00462  -0.0785   0.5627   0.6523
   5.250   0.9091   0.01058   0.00474  -0.0780   0.5555   0.6549
   5.500   0.9318   0.01064   0.00479  -0.0772   0.5463   0.6578
   5.750   0.9545   0.01071   0.00492  -0.0765   0.5376   0.6609
   6.000   0.9759   0.01083   0.00502  -0.0755   0.5287   0.6641
   6.250   0.9961   0.01094   0.00517  -0.0744   0.5171   0.6671
   6.500   1.0098   0.01111   0.00533  -0.0719   0.5000   0.6702
   6.750   1.0160   0.01137   0.00555  -0.0681   0.4794   0.6735
   7.000   1.0223   0.01180   0.00593  -0.0646   0.4552   0.6769
   7.250   1.0182   0.01260   0.00657  -0.0595   0.4206   0.6806
   7.500   1.0083   0.01375   0.00753  -0.0540   0.3827   0.6841
   7.750   0.9964   0.01517   0.00878  -0.0486   0.3449   0.6876
   8.000   0.9871   0.01670   0.01017  -0.0440   0.3098   0.6914
   8.250   0.9791   0.01834   0.01167  -0.0400   0.2759   0.6956
   8.500   0.9714   0.02011   0.01330  -0.0363   0.2425   0.7001
   8.750   0.9663   0.02189   0.01493  -0.0332   0.2121   0.7042
   9.000   0.9622   0.02368   0.01660  -0.0303   0.1830   0.7083
   9.250   0.9637   0.02523   0.01809  -0.0282   0.1610   0.7127
   9.500   0.9659   0.02680   0.01958  -0.0263   0.1402   0.7172
   9.750   0.9682   0.02846   0.02115  -0.0245   0.1196   0.7216
  10.000   0.9708   0.03014   0.02275  -0.0228   0.0998   0.7258
  10.250   0.9739   0.03182   0.02436  -0.0213   0.0813   0.7303
  10.500   0.9784   0.03348   0.02597  -0.0200   0.0663   0.7353
  10.750   0.9833   0.03516   0.02759  -0.0188   0.0515   0.7406
  11.000   0.9893   0.03680   0.02920  -0.0177   0.0410   0.7455
  11.250   0.9971   0.03832   0.03072  -0.0168   0.0349   0.7511
  11.500   1.0068   0.03975   0.03219  -0.0161   0.0316   0.7570
  11.750   1.0175   0.04114   0.03360  -0.0155   0.0294   0.7626
  12.000   1.0279   0.04254   0.03506  -0.0149   0.0276   0.7681
  12.250   1.0376   0.04403   0.03660  -0.0144   0.0262   0.7742
  12.500   1.0489   0.04543   0.03805  -0.0140   0.0251   0.7805
  12.750   1.0594   0.04691   0.03961  -0.0135   0.0242   0.7866
  13.000   1.0691   0.04846   0.04123  -0.0131   0.0233   0.7939
  13.250   1.0786   0.05009   0.04290  -0.0127   0.0226   0.8012
  13.500   1.0873   0.05178   0.04467  -0.0123   0.0219   0.8087
  13.750   1.0975   0.05337   0.04634  -0.0120   0.0214   0.8170
  14.000   1.1072   0.05501   0.04806  -0.0117   0.0208   0.8248
  14.250   1.1159   0.05679   0.04991  -0.0115   0.0201   0.8335
  14.500   1.1240   0.05864   0.05183  -0.0112   0.0194   0.8420
  14.750   1.1311   0.06059   0.05385  -0.0110   0.0191   0.8517
  15.000   1.1369   0.06268   0.05602  -0.0107   0.0188   0.8621
  15.250   1.1448   0.06451   0.05797  -0.0105   0.0184   0.8749
  15.500   1.1509   0.06648   0.06005  -0.0101   0.0182   0.8915
  15.750   1.1568   0.06850   0.06219  -0.0098   0.0179   0.9169
  16.000   1.1689   0.07084   0.06466  -0.0113   0.0175   0.9590
  16.250   1.1734   0.07312   0.06700  -0.0113   0.0172   1.0000
  16.500   1.1803   0.07547   0.06940  -0.0117   0.0170   1.0000
  16.750   1.1861   0.07798   0.07197  -0.0122   0.0167   1.0000
  17.000   1.1914   0.08059   0.07463  -0.0127   0.0165   1.0000
  17.250   1.1957   0.08336   0.07745  -0.0133   0.0163   1.0000
  17.500   1.1988   0.08630   0.08045  -0.0140   0.0161   1.0000
  17.750   1.2008   0.08941   0.08361  -0.0147   0.0158   1.0000
<< Back to NACA 65(4)-421 (naca654421-il)

Polar data table (+)

Polar graphs


<< Back to NACA 65(4)-421 (naca654421-il)