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

NACA 64(4)-421 (naca644421-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA 64(4)-421 (naca644421-il)
Reynolds number: 100,000
Max Cl/Cd: 26.11 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca644421-il-100000-n5.txt
Download as CSV file: xf-naca644421-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64(4)-421                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -17.250  -0.6929   0.09816   0.09162  -0.0713   1.0000   0.0504
 -17.000  -0.7268   0.08941   0.08261  -0.0759   1.0000   0.0505
 -16.750  -0.7468   0.08332   0.07630  -0.0788   1.0000   0.0509
 -16.500  -0.7616   0.07826   0.07104  -0.0810   1.0000   0.0513
 -16.250  -0.7719   0.07393   0.06652  -0.0825   1.0000   0.0518
 -16.000  -0.7795   0.07010   0.06249  -0.0837   1.0000   0.0524
 -15.750  -0.7855   0.06658   0.05877  -0.0846   1.0000   0.0531
 -15.500  -0.7899   0.06336   0.05531  -0.0852   1.0000   0.0538
 -15.250  -0.7816   0.06149   0.05343  -0.0853   1.0000   0.0546
 -15.000  -0.7732   0.05981   0.05175  -0.0853   1.0000   0.0557
 -14.750  -0.7660   0.05796   0.04985  -0.0853   1.0000   0.0566
 -14.500  -0.7597   0.05610   0.04791  -0.0852   1.0000   0.0578
 -14.250  -0.7527   0.05430   0.04599  -0.0849   1.0000   0.0591
 -14.000  -0.7450   0.05260   0.04414  -0.0845   1.0000   0.0603
 -13.750  -0.7323   0.05148   0.04308  -0.0839   1.0000   0.0616
 -13.500  -0.7218   0.05032   0.04196  -0.0833   1.0000   0.0628
 -13.250  -0.7133   0.04916   0.04079  -0.0824   1.0000   0.0644
 -13.000  -0.7063   0.04808   0.03968  -0.0813   1.0000   0.0662
 -12.750  -0.6986   0.04711   0.03866  -0.0801   0.9976   0.0680
 -12.500  -0.6696   0.04569   0.03731  -0.0826   0.9795   0.0704
 -12.250  -0.6417   0.04439   0.03596  -0.0850   0.9658   0.0735
 -12.000  -0.6133   0.04311   0.03462  -0.0874   0.9536   0.0771
 -11.750  -0.5865   0.04180   0.03330  -0.0898   0.9411   0.0810
 -11.500  -0.5597   0.04064   0.03208  -0.0917   0.9288   0.0857
 -11.250  -0.5366   0.03938   0.03080  -0.0935   0.9165   0.0906
 -11.000  -0.5162   0.03826   0.02964  -0.0944   0.9034   0.0965
 -10.750  -0.5007   0.03717   0.02853  -0.0945   0.8901   0.1028
 -10.500  -0.4871   0.03607   0.02741  -0.0944   0.8783   0.1099
 -10.250  -0.4750   0.03504   0.02634  -0.0938   0.8665   0.1187
 -10.000  -0.4662   0.03391   0.02524  -0.0929   0.8553   0.1282
  -9.750  -0.4586   0.03272   0.02407  -0.0919   0.8450   0.1398
  -9.500  -0.4534   0.03150   0.02289  -0.0907   0.8346   0.1533
  -9.250  -0.4496   0.03019   0.02162  -0.0893   0.8253   0.1699
  -9.000  -0.4487   0.02882   0.02034  -0.0877   0.8156   0.1897
  -8.750  -0.4498   0.02735   0.01896  -0.0859   0.8065   0.2130
  -8.500  -0.4542   0.02585   0.01759  -0.0836   0.7979   0.2409
  -8.250  -0.4623   0.02443   0.01635  -0.0806   0.7885   0.2726
  -8.000  -0.4723   0.02335   0.01544  -0.0766   0.7813   0.3084
  -7.750  -0.4725   0.02287   0.01527  -0.0732   0.7722   0.3543
  -7.500  -0.4548   0.02313   0.01576  -0.0711   0.7657   0.4029
  -7.250  -0.4458   0.02278   0.01530  -0.0691   0.7595   0.4338
  -7.000  -0.4336   0.02260   0.01501  -0.0673   0.7521   0.4556
  -6.750  -0.4157   0.02253   0.01480  -0.0661   0.7462   0.4735
  -6.500  -0.3931   0.02263   0.01474  -0.0652   0.7417   0.4885
  -6.250  -0.3683   0.02308   0.01518  -0.0642   0.7346   0.4993
  -6.000  -0.3486   0.02302   0.01496  -0.0633   0.7284   0.5115
  -5.750  -0.3188   0.02353   0.01541  -0.0627   0.7238   0.5211
  -5.500  -0.2961   0.02369   0.01545  -0.0618   0.7184   0.5318
  -5.250  -0.2682   0.02433   0.01609  -0.0610   0.7122   0.5409
  -5.000  -0.2452   0.02441   0.01605  -0.0603   0.7073   0.5507
  -4.750  -0.2136   0.02495   0.01653  -0.0598   0.7034   0.5564
  -4.500  -0.1943   0.02466   0.01611  -0.0592   0.6985   0.5649
  -4.250  -0.1713   0.02460   0.01599  -0.0587   0.6930   0.5698
  -4.000  -0.1440   0.02471   0.01603  -0.0583   0.6885   0.5728
  -3.750  -0.1173   0.02463   0.01586  -0.0582   0.6848   0.5764
  -3.500  -0.0925   0.02435   0.01544  -0.0582   0.6813   0.5811
  -3.250  -0.0747   0.02380   0.01477  -0.0580   0.6756   0.5874
  -3.000  -0.0488   0.02384   0.01478  -0.0577   0.6709   0.5896
  -2.750  -0.0218   0.02380   0.01468  -0.0575   0.6670   0.5920
  -2.500   0.0059   0.02370   0.01449  -0.0575   0.6639   0.5949
  -2.250   0.0304   0.02363   0.01437  -0.0574   0.6600   0.5984
  -2.000   0.0526   0.02350   0.01420  -0.0572   0.6554   0.6027
  -1.750   0.0768   0.02320   0.01378  -0.0577   0.6515   0.6076
  -1.500   0.1036   0.02320   0.01376  -0.0575   0.6483   0.6096
  -1.250   0.1314   0.02317   0.01368  -0.0576   0.6456   0.6118
  -1.000   0.1600   0.02312   0.01357  -0.0579   0.6434   0.6145
  -0.750   0.1811   0.02327   0.01376  -0.0573   0.6391   0.6176
  -0.500   0.2044   0.02330   0.01378  -0.0572   0.6350   0.6209
  -0.250   0.2301   0.02322   0.01364  -0.0575   0.6315   0.6244
   0.000   0.2579   0.02309   0.01344  -0.0581   0.6286   0.6281
   0.250   0.2859   0.02312   0.01345  -0.0581   0.6262   0.6304
   0.500   0.3148   0.02315   0.01346  -0.0584   0.6243   0.6330
   0.750   0.3338   0.02349   0.01388  -0.0575   0.6203   0.6359
   1.000   0.3549   0.02375   0.01419  -0.0571   0.6167   0.6391
   1.250   0.3790   0.02391   0.01436  -0.0570   0.6136   0.6427
   1.500   0.4058   0.02397   0.01439  -0.0575   0.6109   0.6468
   1.750   0.4334   0.02402   0.01444  -0.0577   0.6085   0.6497
   2.000   0.4620   0.02408   0.01451  -0.0579   0.6065   0.6524
   2.250   0.4892   0.02423   0.01470  -0.0581   0.6045   0.6557
   2.500   0.4997   0.02498   0.01558  -0.0562   0.5999   0.6598
   2.750   0.5182   0.02543   0.01609  -0.0555   0.5960   0.6645
   3.000   0.5425   0.02567   0.01635  -0.0555   0.5929   0.6691
   3.250   0.5679   0.02585   0.01659  -0.0553   0.5905   0.6722
   3.500   0.5963   0.02594   0.01672  -0.0555   0.5884   0.6758
   3.750   0.6278   0.02595   0.01675  -0.0562   0.5866   0.6800
   4.000   0.6248   0.02722   0.01818  -0.0528   0.5802   0.6850
   4.250   0.6380   0.02792   0.01894  -0.0514   0.5757   0.6900
   4.500   0.6601   0.02821   0.01933  -0.0508   0.5728   0.6937
   4.750   0.6885   0.02830   0.01949  -0.0509   0.5706   0.6983
   5.000   0.7209   0.02828   0.01951  -0.0517   0.5688   0.7039
   6.000   0.7615   0.03128   0.02289  -0.0440   0.5510   0.7272
   6.250   0.8026   0.03092   0.02260  -0.0457   0.5495   0.7330
   6.750   0.7704   0.03484   0.02675  -0.0368   0.5330   0.7458
   7.000   0.7828   0.03572   0.02771  -0.0356   0.5277   0.7526
   7.250   0.8588   0.03289   0.02497  -0.0394   0.5302   0.7585
   7.750   0.8490   0.03598   0.02826  -0.0336   0.5133   0.7743
   8.250   0.8500   0.03898   0.03146  -0.0296   0.4961   0.7914
   8.500   0.8968   0.03704   0.02963  -0.0300   0.4948   0.7997
   9.000   0.8420   0.04461   0.03742  -0.0240   0.4646   0.8182
   9.250   0.8822   0.04270   0.03561  -0.0237   0.4616   0.8295
   9.500   0.9301   0.03998   0.03299  -0.0234   0.4591   0.8409
  10.000   0.8914   0.04663   0.03989  -0.0189   0.4285   0.8666
  10.500   0.9152   0.04740   0.04091  -0.0161   0.4086   0.9058
  10.750   0.9155   0.04936   0.04302  -0.0154   0.3936   0.9421
  11.000   0.9252   0.05048   0.04420  -0.0154   0.3791   1.0000
  11.250   0.9463   0.05086   0.04461  -0.0156   0.3648   1.0000
  11.500   0.9722   0.05063   0.04433  -0.0157   0.3488   1.0000
  11.750   0.9990   0.05019   0.04378  -0.0156   0.3285   1.0000
  12.000   1.0163   0.05074   0.04419  -0.0153   0.3040   1.0000
  12.250   1.0274   0.05196   0.04521  -0.0149   0.2775   1.0000
  12.500   1.0325   0.05392   0.04700  -0.0146   0.2527   1.0000
  12.750   1.0348   0.05626   0.04918  -0.0144   0.2299   1.0000
  13.000   1.0357   0.05884   0.05160  -0.0143   0.2096   1.0000
  13.250   1.0371   0.06150   0.05417  -0.0143   0.1914   1.0000
  13.500   1.0386   0.06424   0.05682  -0.0145   0.1747   1.0000
  13.750   1.0407   0.06696   0.05947  -0.0147   0.1599   1.0000
  14.000   1.0429   0.06974   0.06218  -0.0150   0.1469   1.0000
  14.500   1.0490   0.07529   0.06766  -0.0158   0.1242   1.0000
  14.750   1.0531   0.07799   0.07036  -0.0163   0.1148   1.0000
  15.000   1.0566   0.08080   0.07313  -0.0168   0.1066   1.0000
  15.250   1.0597   0.08370   0.07601  -0.0174   0.0994   1.0000
  15.500   1.0650   0.08637   0.07871  -0.0180   0.0926   1.0000
  15.750   1.0681   0.08931   0.08162  -0.0187   0.0871   1.0000
  16.000   1.0733   0.09206   0.08443  -0.0194   0.0816   1.0000
  16.250   1.0777   0.09488   0.08724  -0.0201   0.0771   1.0000
  16.500   1.0828   0.09767   0.09008  -0.0209   0.0728   1.0000
  16.750   1.0874   0.10051   0.09291  -0.0218   0.0693   1.0000
  17.000   1.0932   0.10324   0.09572  -0.0226   0.0657   1.0000
<< Back to NACA 64(4)-421 (naca644421-il)

Polar data table (+)

Polar graphs


<< Back to NACA 64(4)-421 (naca644421-il)