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NACA 63-412 AIRFOIL (n63412-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NACA 63-412 AIRFOIL (n63412-il)
Reynolds number: 200,000
Max Cl/Cd: 77.24 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n63412-il-200000.txt
Download as CSV file: xf-n63412-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 63-412 AIRFOIL                             
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4467   0.08769   0.08412  -0.0429   1.0000   0.0652
  -9.500  -0.4538   0.08272   0.07921  -0.0460   1.0000   0.0676
  -9.250  -0.4725   0.07531   0.07188  -0.0526   1.0000   0.0690
  -9.000  -0.5037   0.06876   0.06535  -0.0580   1.0000   0.0693
  -8.750  -0.5326   0.06517   0.06176  -0.0584   1.0000   0.0695
  -8.500  -0.5687   0.06296   0.05939  -0.0564   1.0000   0.0705
  -8.250  -0.6022   0.06274   0.05895  -0.0516   1.0000   0.0712
  -7.750  -0.5964   0.05274   0.04895  -0.0524   0.9962   0.0742
  -7.500  -0.5786   0.03930   0.03390  -0.0582   0.9873   0.0481
  -7.250  -0.5474   0.03412   0.02852  -0.0611   0.9837   0.0453
  -7.000  -0.5176   0.03044   0.02435  -0.0632   0.9774   0.0452
  -6.750  -0.4826   0.02699   0.02043  -0.0656   0.9729   0.0447
  -6.500  -0.4443   0.02451   0.01754  -0.0681   0.9696   0.0454
  -6.250  -0.4104   0.02355   0.01623  -0.0694   0.9625   0.0474
  -6.000  -0.3745   0.02078   0.01331  -0.0715   0.9591   0.0495
  -5.750  -0.3342   0.01934   0.01184  -0.0742   0.9565   0.0520
  -5.500  -0.3011   0.01843   0.01086  -0.0754   0.9500   0.0557
  -5.250  -0.2642   0.01746   0.00979  -0.0772   0.9452   0.0595
  -5.000  -0.2272   0.01613   0.00855  -0.0794   0.9416   0.0650
  -4.750  -0.1974   0.01552   0.00788  -0.0800   0.9335   0.0720
  -4.500  -0.1635   0.01458   0.00698  -0.0815   0.9279   0.0841
  -4.250  -0.1343   0.01367   0.00621  -0.0823   0.9202   0.1121
  -4.000  -0.1094   0.01142   0.00546  -0.0836   0.9128   0.4221
  -3.750  -0.0823   0.01120   0.00551  -0.0833   0.9049   0.5244
  -3.500  -0.0533   0.01116   0.00548  -0.0831   0.8976   0.5694
  -3.250  -0.0263   0.01119   0.00551  -0.0826   0.8894   0.6004
  -3.000   0.0014   0.01123   0.00551  -0.0821   0.8820   0.6263
  -2.750   0.0270   0.01137   0.00567  -0.0811   0.8737   0.6505
  -2.500   0.0536   0.01152   0.00578  -0.0803   0.8663   0.6752
  -2.250   0.0784   0.01166   0.00593  -0.0791   0.8578   0.6933
  -2.000   0.1047   0.01174   0.00598  -0.0782   0.8507   0.7093
  -1.750   0.1309   0.01178   0.00598  -0.0777   0.8421   0.7217
  -1.500   0.1578   0.01177   0.00592  -0.0771   0.8350   0.7319
  -1.250   0.1836   0.01179   0.00592  -0.0765   0.8264   0.7415
  -1.000   0.2115   0.01177   0.00582  -0.0763   0.8195   0.7520
  -0.750   0.2370   0.01179   0.00585  -0.0756   0.8108   0.7606
  -0.500   0.2644   0.01177   0.00577  -0.0752   0.8040   0.7700
  -0.250   0.2907   0.01180   0.00580  -0.0748   0.7953   0.7799
   0.000   0.3173   0.01178   0.00575  -0.0743   0.7886   0.7882
   0.250   0.3437   0.01182   0.00579  -0.0740   0.7799   0.7984
   0.500   0.3701   0.01181   0.00576  -0.0733   0.7732   0.8073
   0.750   0.3955   0.01185   0.00584  -0.0728   0.7644   0.8168
   1.000   0.4232   0.01186   0.00580  -0.0725   0.7578   0.8275
   1.250   0.4470   0.01190   0.00591  -0.0715   0.7491   0.8365
   1.500   0.4734   0.01190   0.00588  -0.0710   0.7424   0.8466
   1.750   0.4986   0.01195   0.00599  -0.0704   0.7336   0.8579
   2.000   0.5235   0.01194   0.00597  -0.0695   0.7270   0.8680
   2.250   0.5467   0.01196   0.00607  -0.0684   0.7179   0.8792
   2.500   0.5720   0.01194   0.00604  -0.0676   0.7114   0.8909
   2.750   0.5944   0.01194   0.00613  -0.0664   0.7020   0.9039
   3.000   0.6182   0.01190   0.00609  -0.0653   0.6948   0.9173
   3.250   0.6401   0.01183   0.00610  -0.0639   0.6853   0.9323
   3.500   0.6658   0.01175   0.00608  -0.0632   0.6760   0.9485
   3.750   0.6989   0.01164   0.00596  -0.0640   0.6659   0.9651
   4.000   0.7376   0.01155   0.00592  -0.0662   0.6520   0.9852
   4.250   0.7689   0.01153   0.00593  -0.0672   0.6373   1.0000
   4.500   0.7973   0.01153   0.00591  -0.0675   0.6211   1.0000
   4.750   0.8245   0.01151   0.00591  -0.0675   0.5989   1.0000
   5.000   0.8521   0.01156   0.00593  -0.0675   0.5773   1.0000
   5.250   0.8794   0.01167   0.00606  -0.0676   0.5556   1.0000
   5.500   0.9058   0.01183   0.00618  -0.0674   0.5307   1.0000
   5.750   0.9307   0.01205   0.00638  -0.0669   0.4976   1.0000
   6.000   0.9534   0.01238   0.00660  -0.0661   0.4487   1.0000
   6.250   0.9692   0.01321   0.00698  -0.0642   0.3553   1.0000
   6.500   0.9740   0.01510   0.00798  -0.0614   0.2118   1.0000
   6.750   0.9777   0.01732   0.00939  -0.0585   0.1050   1.0000
   7.000   0.9900   0.01876   0.01063  -0.0565   0.0767   1.0000
   7.250   1.0041   0.01996   0.01178  -0.0548   0.0648   1.0000
   7.500   1.0193   0.02102   0.01284  -0.0532   0.0575   1.0000
   7.750   1.0315   0.02235   0.01420  -0.0511   0.0529   1.0000
   8.000   1.0466   0.02339   0.01527  -0.0494   0.0489   1.0000
   8.250   1.0583   0.02483   0.01666  -0.0475   0.0455   1.0000
   8.500   1.0751   0.02619   0.01809  -0.0461   0.0429   1.0000
   8.750   1.0947   0.02746   0.01943  -0.0450   0.0409   1.0000
   9.000   1.1161   0.02884   0.02087  -0.0444   0.0391   1.0000
   9.250   1.1399   0.03042   0.02247  -0.0441   0.0376   1.0000
   9.500   1.1763   0.03365   0.02572  -0.0460   0.0357   1.0000
   9.750   1.1955   0.03527   0.02758  -0.0450   0.0347   1.0000
  10.000   1.2142   0.03707   0.02962  -0.0440   0.0339   1.0000
  10.250   1.2327   0.03948   0.03232  -0.0430   0.0333   1.0000
  10.500   1.2475   0.04223   0.03537  -0.0417   0.0330   1.0000
  10.750   1.2574   0.04528   0.03876  -0.0400   0.0329   1.0000
  11.000   1.2622   0.04866   0.04250  -0.0379   0.0331   1.0000
  11.250   1.2600   0.05207   0.04623  -0.0352   0.0334   1.0000
  11.500   1.2527   0.05542   0.04986  -0.0322   0.0336   1.0000
  11.750   1.2410   0.05883   0.05355  -0.0295   0.0337   1.0000
  12.000   1.2268   0.06254   0.05751  -0.0273   0.0339   1.0000
  12.250   1.2100   0.06648   0.06169  -0.0257   0.0340   1.0000
  12.500   1.1923   0.07096   0.06639  -0.0250   0.0342   1.0000
  12.750   1.1730   0.07591   0.07154  -0.0250   0.0345   1.0000
  13.000   1.1533   0.08150   0.07731  -0.0258   0.0348   1.0000
  13.250   1.1583   0.08612   0.08201  -0.0261   0.0360   1.0000
  13.500   0.7877   0.13131   0.12857  -0.0524   0.0573   1.0000
  13.750   0.7291   0.15114   0.14834  -0.0648   0.0739   1.0000
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