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

NACA 4421 (naca4421-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NACA 4421 (naca4421-il)
Reynolds number: 500,000
Max Cl/Cd: 83.3 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca4421-il-500000.txt
Download as CSV file: xf-naca4421-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 4421                                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -19.750  -0.9257   0.08876   0.08422  -0.0908   1.0000   0.0525
 -19.500  -0.9314   0.08493   0.08034  -0.0926   1.0000   0.0530
 -19.250  -0.9378   0.08112   0.07646  -0.0942   1.0000   0.0535
 -19.000  -0.9460   0.07712   0.07239  -0.0959   1.0000   0.0540
 -18.750  -0.9550   0.07315   0.06833  -0.0975   1.0000   0.0545
 -18.500  -0.9644   0.06929   0.06436  -0.0989   1.0000   0.0550
 -18.250  -0.9744   0.06547   0.06044  -0.1001   1.0000   0.0554
 -18.000  -0.9779   0.06303   0.05803  -0.1000   1.0000   0.0560
 -17.750  -0.9860   0.06003   0.05502  -0.1003   1.0000   0.0566
 -17.500  -0.9969   0.05682   0.05176  -0.1005   1.0000   0.0570
 -17.250  -1.0092   0.05366   0.04855  -0.1005   1.0000   0.0575
 -17.000  -1.0224   0.05062   0.04546  -0.1001   1.0000   0.0580
 -16.750  -1.0365   0.04771   0.04248  -0.0994   1.0000   0.0585
 -16.500  -1.0515   0.04495   0.03966  -0.0983   1.0000   0.0590
 -16.250  -1.0670   0.04241   0.03705  -0.0967   1.0000   0.0595
 -16.000  -1.0829   0.04007   0.03463  -0.0948   1.0000   0.0599
 -15.750  -1.0763   0.03758   0.03202  -0.0965   0.9986   0.0607
 -15.500  -1.0668   0.03458   0.02901  -0.0996   0.9960   0.0619
 -15.250  -1.0506   0.03228   0.02666  -0.1026   0.9937   0.0630
 -15.000  -1.0301   0.03042   0.02473  -0.1055   0.9919   0.0644
 -14.750  -1.0129   0.02885   0.02306  -0.1069   0.9880   0.0657
 -14.500  -0.9953   0.02716   0.02133  -0.1086   0.9843   0.0671
 -14.250  -0.9738   0.02570   0.01985  -0.1106   0.9816   0.0687
 -14.000  -0.9471   0.02460   0.01870  -0.1126   0.9798   0.0707
 -13.750  -0.9246   0.02368   0.01770  -0.1134   0.9760   0.0725
 -13.500  -0.9066   0.02260   0.01664  -0.1136   0.9709   0.0745
 -13.250  -0.8776   0.02180   0.01581  -0.1151   0.9685   0.0770
 -13.000  -0.8472   0.02098   0.01496  -0.1168   0.9666   0.0798
 -12.750  -0.8167   0.02024   0.01422  -0.1184   0.9648   0.0828
 -12.500  -0.8009   0.01981   0.01373  -0.1166   0.9571   0.0854
 -12.250  -0.7780   0.01911   0.01305  -0.1164   0.9528   0.0883
 -12.000  -0.7487   0.01860   0.01251  -0.1171   0.9499   0.0917
 -11.750  -0.7324   0.01816   0.01204  -0.1153   0.9424   0.0946
 -11.500  -0.7091   0.01770   0.01159  -0.1147   0.9371   0.0978
 -11.250  -0.6808   0.01737   0.01116  -0.1148   0.9333   0.1012
 -11.000  -0.6640   0.01691   0.01074  -0.1131   0.9260   0.1043
 -10.750  -0.6401   0.01659   0.01039  -0.1124   0.9201   0.1076
 -10.500  -0.6137   0.01626   0.00998  -0.1122   0.9155   0.1108
 -10.250  -0.5939   0.01587   0.00962  -0.1109   0.9084   0.1137
 -10.000  -0.5695   0.01560   0.00932  -0.1102   0.9019   0.1168
  -9.750  -0.5416   0.01538   0.00900  -0.1101   0.8968   0.1197
  -9.500  -0.5211   0.01497   0.00863  -0.1089   0.8893   0.1229
  -9.250  -0.4963   0.01471   0.00835  -0.1083   0.8824   0.1260
  -9.000  -0.4682   0.01449   0.00805  -0.1083   0.8768   0.1290
  -8.750  -0.4458   0.01420   0.00775  -0.1073   0.8689   0.1320
  -8.500  -0.4209   0.01390   0.00745  -0.1067   0.8617   0.1352
  -8.250  -0.3939   0.01370   0.00720  -0.1065   0.8551   0.1384
  -8.000  -0.3686   0.01355   0.00699  -0.1059   0.8470   0.1411
  -7.750  -0.3436   0.01320   0.00664  -0.1053   0.8396   0.1447
  -7.500  -0.3181   0.01298   0.00642  -0.1048   0.8321   0.1482
  -7.250  -0.2921   0.01282   0.00621  -0.1044   0.8240   0.1516
  -6.750  -0.2410   0.01236   0.00572  -0.1033   0.8079   0.1595
  -6.500  -0.2143   0.01220   0.00551  -0.1030   0.7995   0.1639
  -6.250  -0.1882   0.01201   0.00530  -0.1026   0.7917   0.1687
  -6.000  -0.1629   0.01181   0.00513  -0.1020   0.7826   0.1748
  -5.750  -0.1358   0.01169   0.00494  -0.1017   0.7742   0.1817
  -5.500  -0.1108   0.01149   0.00481  -0.1011   0.7647   0.1896
  -5.250  -0.0843   0.01136   0.00464  -0.1007   0.7557   0.1979
  -5.000  -0.0582   0.01124   0.00454  -0.1003   0.7467   0.2073
  -4.750  -0.0321   0.01112   0.00442  -0.0998   0.7372   0.2169
  -4.500  -0.0051   0.01108   0.00434  -0.0995   0.7278   0.2266
  -4.250   0.0206   0.01096   0.00425  -0.0990   0.7175   0.2369
  -4.000   0.0477   0.01096   0.00418  -0.0986   0.7079   0.2454
  -3.750   0.0731   0.01083   0.00408  -0.0981   0.6976   0.2549
  -3.500   0.0999   0.01082   0.00401  -0.0977   0.6882   0.2629
  -3.250   0.1257   0.01073   0.00393  -0.0972   0.6781   0.2712
  -3.000   0.1516   0.01071   0.00386  -0.0967   0.6683   0.2796
  -2.750   0.1779   0.01067   0.00381  -0.0963   0.6581   0.2874
  -2.500   0.2032   0.01064   0.00376  -0.0957   0.6483   0.2969
  -2.250   0.2297   0.01061   0.00373  -0.0953   0.6390   0.3054
  -2.000   0.2551   0.01058   0.00369  -0.0947   0.6298   0.3158
  -1.750   0.2814   0.01056   0.00368  -0.0943   0.6212   0.3265
  -1.500   0.3068   0.01052   0.00366  -0.0938   0.6122   0.3400
  -1.250   0.3324   0.01051   0.00366  -0.0933   0.6039   0.3556
  -1.000   0.3582   0.01047   0.00367  -0.0928   0.5955   0.3744
  -0.750   0.3835   0.01048   0.00368  -0.0922   0.5877   0.3958
  -0.500   0.4093   0.01043   0.00371  -0.0918   0.5806   0.4194
  -0.250   0.4346   0.01040   0.00374  -0.0912   0.5730   0.4451
   0.000   0.4595   0.01042   0.00379  -0.0906   0.5655   0.4733
   0.250   0.4847   0.01034   0.00384  -0.0900   0.5583   0.5043
   0.500   0.5093   0.01033   0.00389  -0.0893   0.5506   0.5373
   0.750   0.5335   0.01033   0.00398  -0.0886   0.5433   0.5732
   1.000   0.5585   0.01028   0.00407  -0.0879   0.5371   0.6125
   1.250   0.5830   0.01027   0.00416  -0.0872   0.5307   0.6500
   1.500   0.6077   0.01036   0.00427  -0.0865   0.5244   0.6813
   1.750   0.6328   0.01036   0.00438  -0.0858   0.5191   0.7102
   2.000   0.6574   0.01037   0.00449  -0.0850   0.5132   0.7388
   2.250   0.6814   0.01043   0.00460  -0.0842   0.5076   0.7668
   2.500   0.7058   0.01053   0.00475  -0.0834   0.5021   0.7951
   2.750   0.7294   0.01055   0.00489  -0.0823   0.4970   0.8250
   3.000   0.7523   0.01061   0.00503  -0.0811   0.4916   0.8559
   3.250   0.7740   0.01074   0.00520  -0.0796   0.4864   0.8875
   3.500   0.7966   0.01091   0.00539  -0.0783   0.4813   0.9182
   3.750   0.8208   0.01102   0.00556  -0.0773   0.4764   0.9445
   4.000   0.8516   0.01121   0.00574  -0.0779   0.4708   0.9635
   4.250   0.8863   0.01148   0.00595  -0.0794   0.4653   0.9778
   4.500   0.9265   0.01173   0.00618  -0.0821   0.4598   0.9872
   4.750   0.9686   0.01194   0.00640  -0.0853   0.4539   0.9938
   5.000   1.0126   0.01222   0.00663  -0.0889   0.4479   0.9995
   5.250   1.0213   0.01237   0.00671  -0.0853   0.4428   1.0000
   5.500   1.0293   0.01240   0.00677  -0.0815   0.4386   1.0000
   5.750   1.0421   0.01251   0.00688  -0.0786   0.4330   1.0000
   6.000   1.0571   0.01271   0.00703  -0.0763   0.4269   1.0000
   6.250   1.0745   0.01294   0.00723  -0.0745   0.4206   1.0000
   6.500   1.0927   0.01313   0.00743  -0.0728   0.4135   1.0000
   6.750   1.1097   0.01343   0.00767  -0.0710   0.4063   1.0000
   7.000   1.1294   0.01368   0.00793  -0.0698   0.3998   1.0000
   7.250   1.1490   0.01396   0.00820  -0.0685   0.3931   1.0000
   7.500   1.1665   0.01434   0.00853  -0.0670   0.3865   1.0000
   7.750   1.1870   0.01463   0.00884  -0.0659   0.3802   1.0000
   8.000   1.2059   0.01498   0.00919  -0.0647   0.3732   1.0000
   8.250   1.2227   0.01544   0.00961  -0.0632   0.3663   1.0000
   8.500   1.2425   0.01580   0.00999  -0.0622   0.3589   1.0000
   8.750   1.2586   0.01632   0.01046  -0.0607   0.3512   1.0000
   9.000   1.2769   0.01677   0.01093  -0.0595   0.3439   1.0000
   9.250   1.2933   0.01732   0.01146  -0.0581   0.3360   1.0000
   9.500   1.3093   0.01791   0.01204  -0.0568   0.3285   1.0000
   9.750   1.3252   0.01853   0.01265  -0.0554   0.3202   1.0000
  10.000   1.3393   0.01925   0.01334  -0.0539   0.3124   1.0000
  10.250   1.3546   0.01994   0.01403  -0.0527   0.3043   1.0000
  10.500   1.3668   0.02081   0.01487  -0.0511   0.2968   1.0000
  10.750   1.3821   0.02155   0.01563  -0.0499   0.2894   1.0000
  11.000   1.3923   0.02258   0.01661  -0.0482   0.2819   1.0000
  11.250   1.4068   0.02341   0.01747  -0.0471   0.2750   1.0000
  11.500   1.4165   0.02454   0.01857  -0.0455   0.2672   1.0000
  11.750   1.4285   0.02558   0.01962  -0.0443   0.2601   1.0000
  12.000   1.4380   0.02679   0.02082  -0.0429   0.2524   1.0000
  12.250   1.4477   0.02804   0.02208  -0.0416   0.2454   1.0000
  12.500   1.4568   0.02937   0.02341  -0.0403   0.2376   1.0000
  12.750   1.4647   0.03084   0.02487  -0.0391   0.2304   1.0000
  13.000   1.4723   0.03237   0.02641  -0.0379   0.2223   1.0000
  13.250   1.4785   0.03404   0.02808  -0.0367   0.2146   1.0000
  13.500   1.4828   0.03592   0.02995  -0.0355   0.2062   1.0000
  13.750   1.4874   0.03784   0.03188  -0.0345   0.1977   1.0000
  14.000   1.4868   0.04025   0.03426  -0.0333   0.1892   1.0000
  14.250   1.4909   0.04231   0.03633  -0.0324   0.1808   1.0000
  14.500   1.4905   0.04482   0.03884  -0.0314   0.1734   1.0000
  14.750   1.4899   0.04742   0.04145  -0.0306   0.1663   1.0000
  15.000   1.4900   0.05000   0.04403  -0.0299   0.1600   1.0000
  15.250   1.4880   0.05282   0.04686  -0.0292   0.1540   1.0000
  15.500   1.4865   0.05565   0.04971  -0.0286   0.1491   1.0000
  15.750   1.4856   0.05847   0.05257  -0.0282   0.1443   1.0000
  16.000   1.4803   0.06178   0.05588  -0.0277   0.1401   1.0000
  16.250   1.4824   0.06434   0.05850  -0.0275   0.1364   1.0000
  16.500   1.4802   0.06738   0.06157  -0.0272   0.1328   1.0000
  16.750   1.4746   0.07083   0.06502  -0.0270   0.1295   1.0000
  17.000   1.4769   0.07347   0.06773  -0.0270   0.1267   1.0000
  17.250   1.4772   0.07632   0.07063  -0.0270   0.1237   1.0000
  17.500   1.4727   0.07973   0.07406  -0.0271   0.1211   1.0000
  17.750   1.4704   0.08289   0.07724  -0.0271   0.1186   1.0000
  18.000   1.4725   0.08563   0.08006  -0.0274   0.1163   1.0000
  18.250   1.4731   0.08852   0.08300  -0.0276   0.1139   1.0000
  18.500   1.4701   0.09188   0.08639  -0.0280   0.1116   1.0000
<< Back to NACA 4421 (naca4421-il)

Polar data table (+)

Polar graphs


<< Back to NACA 4421 (naca4421-il)