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 a=0.5 (naca654421a05-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NACA 65(4)-421 a=0.5 (naca654421a05-il)
Reynolds number: 200,000
Max Cl/Cd: 31.7 at α=11.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca654421a05-il-200000.txt
Download as CSV file: xf-naca654421a05-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 65(4)-421 a=0.5                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.250  -0.7089   0.06241   0.05697  -0.1039   0.8433   0.0550
 -14.000  -0.7134   0.05887   0.05328  -0.1033   0.8378   0.0548
 -13.750  -0.7234   0.05585   0.05006  -0.1019   0.8328   0.0546
 -13.500  -0.7365   0.05324   0.04721  -0.0999   0.8282   0.0546
 -13.250  -0.7483   0.05095   0.04471  -0.0978   0.8223   0.0547
 -13.000  -0.7602   0.04896   0.04246  -0.0949   0.8171   0.0548
 -12.750  -0.7697   0.04719   0.04042  -0.0915   0.8128   0.0549
 -12.500  -0.7723   0.04544   0.03844  -0.0888   0.8085   0.0549
 -12.250  -0.7682   0.04363   0.03641  -0.0868   0.8035   0.0549
 -12.000  -0.7506   0.04075   0.03335  -0.0867   0.7995   0.0554
 -11.750  -0.7241   0.03843   0.03092  -0.0876   0.7962   0.0561
 -11.500  -0.7002   0.03696   0.02937  -0.0877   0.7932   0.0570
 -11.250  -0.6779   0.03552   0.02780  -0.0877   0.7895   0.0575
 -11.000  -0.6532   0.03413   0.02629  -0.0880   0.7856   0.0580
 -10.750  -0.6285   0.03294   0.02497  -0.0882   0.7820   0.0588
 -10.500  -0.6044   0.03186   0.02376  -0.0881   0.7789   0.0598
 -10.250  -0.5771   0.03080   0.02254  -0.0883   0.7762   0.0605
 -10.000  -0.5482   0.02987   0.02146  -0.0885   0.7738   0.0611
  -9.750  -0.5193   0.02909   0.02058  -0.0890   0.7706   0.0619
  -9.500  -0.4868   0.02828   0.01973  -0.0898   0.7669   0.0627
  -9.250  -0.4522   0.02744   0.01900  -0.0907   0.7638   0.0641
  -9.000  -0.4289   0.02682   0.01841  -0.0904   0.7608   0.0657
  -8.750  -0.4079   0.02623   0.01780  -0.0898   0.7583   0.0674
  -8.500  -0.3886   0.02568   0.01719  -0.0889   0.7560   0.0691
  -8.250  -0.3702   0.02521   0.01664  -0.0879   0.7536   0.0708
  -8.000  -0.3560   0.02446   0.01601  -0.0869   0.7502   0.0727
  -7.750  -0.3435   0.02385   0.01544  -0.0856   0.7468   0.0751
  -7.500  -0.3313   0.02327   0.01484  -0.0840   0.7436   0.0779
  -7.250  -0.3216   0.02266   0.01419  -0.0818   0.7408   0.0811
  -7.000  -0.3173   0.02204   0.01358  -0.0788   0.7383   0.0853
  -6.750  -0.3117   0.02166   0.01314  -0.0756   0.7362   0.0919
  -6.500  -0.3093   0.02131   0.01291  -0.0723   0.7332   0.1043
  -6.250  -0.3128   0.02063   0.01261  -0.0684   0.7295   0.1496
  -6.000  -0.3260   0.01943   0.01211  -0.0630   0.7260   0.2684
  -5.750  -0.3373   0.01825   0.01183  -0.0573   0.7231   0.4291
  -5.500  -0.3219   0.01822   0.01205  -0.0550   0.7209   0.5194
  -5.250  -0.2989   0.01836   0.01215  -0.0539   0.7191   0.5527
  -5.000  -0.2737   0.01861   0.01235  -0.0531   0.7175   0.5751
  -4.750  -0.2546   0.01925   0.01299  -0.0520   0.7142   0.5912
  -4.500  -0.2375   0.01995   0.01367  -0.0508   0.7102   0.6047
  -4.250  -0.2146   0.02052   0.01428  -0.0500   0.7074   0.6171
  -4.000  -0.1902   0.02103   0.01479  -0.0491   0.7052   0.6320
  -3.750  -0.1643   0.02142   0.01514  -0.0484   0.7034   0.6470
  -3.500  -0.1357   0.02189   0.01561  -0.0478   0.7018   0.6598
  -3.250  -0.1058   0.02244   0.01618  -0.0472   0.7004   0.6716
  -3.000  -0.0799   0.02282   0.01649  -0.0465   0.6992   0.6842
  -2.750  -0.0884   0.02483   0.01870  -0.0423   0.6916   0.6890
  -2.500  -0.0745   0.02548   0.01934  -0.0407   0.6879   0.6943
  -2.250  -0.0508   0.02545   0.01922  -0.0404   0.6858   0.7002
  -2.000  -0.0231   0.02529   0.01898  -0.0406   0.6844   0.7045
  -1.750   0.0068   0.02526   0.01890  -0.0409   0.6833   0.7076
  -1.500  -0.0754   0.02954   0.02336  -0.0279   0.6688   0.7128
  -1.250  -0.0507   0.02961   0.02336  -0.0279   0.6670   0.7171
  -1.000  -0.0220   0.02957   0.02321  -0.0285   0.6658   0.7218
  -0.750   0.0103   0.02947   0.02308  -0.0293   0.6649   0.7248
  -0.500  -0.0605   0.03335   0.02706  -0.0181   0.6529   0.7293
  -0.250  -0.0411   0.03381   0.02749  -0.0175   0.6506   0.7331
   0.000  -0.0153   0.03402   0.02764  -0.0177   0.6489   0.7377
   0.250   0.0154   0.03403   0.02756  -0.0185   0.6477   0.7424
   0.500   0.0497   0.03385   0.02737  -0.0193   0.6467   0.7454
   0.750   0.0847   0.03369   0.02720  -0.0203   0.6459   0.7486
   1.000   0.1210   0.03350   0.02699  -0.0214   0.6452   0.7525
   1.250   0.1579   0.03332   0.02677  -0.0227   0.6447   0.7572
   1.500   0.0854   0.03761   0.03110  -0.0129   0.6304   0.7639
   1.750   0.1164   0.03767   0.03118  -0.0134   0.6293   0.7677
   2.000   0.0972   0.03987   0.03342  -0.0092   0.6213   0.7730
   2.250   0.1089   0.04072   0.03425  -0.0081   0.6170   0.7787
   2.500   0.1354   0.04094   0.03445  -0.0083   0.6147   0.7838
   2.750   0.1663   0.04095   0.03450  -0.0087   0.6130   0.7883
   3.000   0.1997   0.04089   0.03445  -0.0093   0.6118   0.7940
   3.250   0.2369   0.04069   0.03423  -0.0105   0.6109   0.8003
   3.500   0.2719   0.04059   0.03415  -0.0113   0.6101   0.8054
   3.750   0.2304   0.04357   0.03721  -0.0053   0.5966   0.8131
   4.000   0.2630   0.04354   0.03717  -0.0059   0.5952   0.8202
   4.250   0.2961   0.04342   0.03710  -0.0064   0.5941   0.8261
   4.500   0.3317   0.04320   0.03692  -0.0071   0.5933   0.8331
   4.750   0.3013   0.04580   0.03957  -0.0024   0.5800   0.8432
   5.000   0.3320   0.04566   0.03949  -0.0025   0.5784   0.8515
   5.250   0.3666   0.04535   0.03921  -0.0030   0.5773   0.8608
   5.500   0.4002   0.04506   0.03898  -0.0033   0.5764   0.8697
   5.750   0.3755   0.04743   0.04144   0.0009   0.5631   0.8831
   6.000   0.4073   0.04712   0.04118   0.0008   0.5616   0.8956
   6.250   0.4032   0.04876   0.04292   0.0030   0.5518   0.9118
   6.500   0.4317   0.04885   0.04309   0.0025   0.5482   0.9286
   6.750   0.4753   0.04860   0.04293  -0.0002   0.5463   0.9456
   7.000   0.5284   0.04826   0.04268  -0.0045   0.5451   0.9610
   7.250   0.5835   0.04788   0.04238  -0.0093   0.5441   0.9785
   7.500   0.6289   0.04725   0.04179  -0.0120   0.5434   1.0000
   7.750   0.6176   0.04956   0.04409  -0.0103   0.5298   1.0000
   8.000   0.6560   0.04878   0.04333  -0.0115   0.5287   1.0000
   8.250   0.6965   0.04775   0.04233  -0.0126   0.5278   1.0000
   8.500   0.7377   0.04656   0.04117  -0.0137   0.5271   1.0000
   8.750   0.7286   0.04880   0.04343  -0.0117   0.5135   1.0000
   9.000   0.7702   0.04738   0.04207  -0.0126   0.5127   1.0000
   9.250   0.8107   0.04599   0.04072  -0.0134   0.5119   1.0000
   9.500   0.8529   0.04436   0.03917  -0.0142   0.5113   1.0000
   9.750   0.8988   0.04203   0.03690  -0.0150   0.5104   1.0000
  10.000   0.9650   0.03727   0.03221  -0.0165   0.5100   1.0000
  10.250   0.9704   0.03797   0.03294  -0.0148   0.4975   1.0000
  10.500   0.9812   0.03834   0.03335  -0.0135   0.4855   1.0000
  10.750   1.0495   0.03393   0.02898  -0.0155   0.4802   1.0000
  11.000   1.0561   0.03496   0.03003  -0.0141   0.4651   1.0000
  11.250   1.0786   0.03474   0.02982  -0.0136   0.4482   1.0000
  11.500   1.0888   0.03560   0.03066  -0.0125   0.4270   1.0000
  11.750   1.1136   0.03513   0.03001  -0.0119   0.3960   1.0000
  12.000   1.1215   0.03600   0.03061  -0.0103   0.3569   1.0000
  12.250   1.1173   0.03800   0.03234  -0.0082   0.3208   1.0000
  12.500   1.1083   0.04060   0.03471  -0.0062   0.2876   1.0000
  12.750   1.0967   0.04358   0.03748  -0.0043   0.2543   1.0000
  13.000   1.0858   0.04668   0.04038  -0.0027   0.2224   1.0000
  13.250   1.0728   0.05011   0.04357  -0.0012   0.1883   1.0000
  13.500   1.0597   0.05371   0.04693   0.0000   0.1522   1.0000
  13.750   1.0417   0.05792   0.05079   0.0013   0.1094   1.0000
  14.000   1.0279   0.06186   0.05445   0.0022   0.0815   1.0000
  14.250   1.0227   0.06509   0.05756   0.0028   0.0678   1.0000
  14.500   1.0205   0.06812   0.06055   0.0032   0.0607   1.0000
  14.750   1.0215   0.07085   0.06327   0.0034   0.0569   1.0000
  15.000   1.0236   0.07350   0.06594   0.0035   0.0530   1.0000
  15.250   1.0266   0.07607   0.06851   0.0036   0.0503   1.0000
  15.500   1.0298   0.07857   0.07098   0.0036   0.0486   1.0000
  15.750   1.0369   0.08070   0.07318   0.0036   0.0466   1.0000
  16.000   1.0448   0.08269   0.07519   0.0036   0.0452   1.0000
  16.250   1.0532   0.08455   0.07702   0.0037   0.0438   1.0000
  16.500   1.0648   0.08591   0.07835   0.0039   0.0424   1.0000
  16.750   1.0773   0.08734   0.07985   0.0040   0.0414   1.0000
  17.000   1.0890   0.08889   0.08144   0.0039   0.0402   1.0000
  17.250   1.1022   0.09017   0.08273   0.0039   0.0391   1.0000
  17.500   1.1215   0.09051   0.08295   0.0043   0.0379   1.0000
  17.750   1.1414   0.09092   0.08337   0.0047   0.0372   1.0000
  18.000   1.1549   0.09232   0.08490   0.0047   0.0367   1.0000
  18.250   1.1678   0.09381   0.08650   0.0046   0.0360   1.0000
  18.500   1.1807   0.09533   0.08813   0.0046   0.0355   1.0000
  18.750   1.1937   0.09684   0.08975   0.0045   0.0350   1.0000
  19.000   1.2062   0.09846   0.09145   0.0043   0.0346   1.0000
  19.250   1.2173   0.10025   0.09336   0.0040   0.0343   1.0000
<< Back to NACA 65(4)-421 a=0.5 (naca654421a05-il)

Polar data table (+)

Polar graphs


<< Back to NACA 65(4)-421 a=0.5 (naca654421a05-il)