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NACA 64(1)-212 MOD B (n64212mb-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NACA 64(1)-212 MOD B (n64212mb-il)
Reynolds number: 50,000
Max Cl/Cd: 24.33 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n64212mb-il-50000.txt
Download as CSV file: xf-n64212mb-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64(1)-212 MOD B                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4065   0.09953   0.09248   0.0039   1.0000   0.3932
  -8.500  -0.5464   0.07723   0.07051  -0.0273   1.0000   0.1933
  -8.250  -0.5981   0.06841   0.06158  -0.0334   1.0000   0.1685
  -8.000  -0.6253   0.06209   0.05491  -0.0349   1.0000   0.1539
  -7.750  -0.6351   0.05687   0.04933  -0.0346   1.0000   0.1444
  -7.500  -0.6331   0.05307   0.04516  -0.0334   1.0000   0.1380
  -7.250  -0.6274   0.04952   0.04137  -0.0319   1.0000   0.1346
  -7.000  -0.6219   0.04630   0.03779  -0.0301   1.0000   0.1324
  -6.750  -0.6131   0.04350   0.03465  -0.0283   1.0000   0.1317
  -6.500  -0.6020   0.04093   0.03173  -0.0264   1.0000   0.1314
  -6.250  -0.5887   0.03853   0.02898  -0.0245   1.0000   0.1312
  -6.000  -0.5730   0.03630   0.02642  -0.0227   1.0000   0.1312
  -5.750  -0.5556   0.03433   0.02419  -0.0209   1.0000   0.1325
  -5.500  -0.5376   0.03266   0.02230  -0.0193   1.0000   0.1364
  -5.250  -0.5186   0.03126   0.02053  -0.0176   1.0000   0.1408
  -5.000  -0.4976   0.02949   0.01887  -0.0161   1.0000   0.1460
  -4.750  -0.4769   0.02826   0.01759  -0.0144   1.0000   0.1540
  -4.500  -0.4570   0.02701   0.01648  -0.0126   1.0000   0.1649
  -4.250  -0.4382   0.02588   0.01543  -0.0105   1.0000   0.1787
  -4.000  -0.4217   0.02469   0.01440  -0.0086   1.0000   0.2018
  -3.750  -0.4069   0.02284   0.01310  -0.0069   1.0000   0.2539
  -3.500  -0.4168   0.02134   0.01418   0.0025   1.0000   0.6345
  -3.250  -0.4221   0.02301   0.01592   0.0136   1.0000   0.7227
  -3.000  -0.4217   0.02407   0.01693   0.0224   1.0000   0.7708
  -2.750  -0.2147   0.02950   0.02148   0.0123   1.0000   0.9283
  -2.500  -0.1678   0.02883   0.02057   0.0075   1.0000   0.9459
  -2.250  -0.1260   0.02818   0.01972   0.0031   1.0000   0.9601
  -2.000  -0.0858   0.02758   0.01897  -0.0012   1.0000   0.9731
  -1.750  -0.0435   0.02702   0.01827  -0.0061   1.0000   0.9855
  -1.500  -0.0003   0.02651   0.01765  -0.0113   1.0000   0.9974
  -1.250   0.0059   0.02638   0.01749  -0.0102   1.0000   1.0000
  -1.000   0.0010   0.02628   0.01739  -0.0072   1.0000   1.0000
  -0.750  -0.0042   0.02615   0.01725  -0.0042   1.0000   1.0000
  -0.500  -0.0098   0.02597   0.01706  -0.0011   1.0000   1.0000
  -0.250  -0.0162   0.02574   0.01682   0.0020   1.0000   1.0000
   0.000  -0.0234   0.02544   0.01652   0.0052   1.0000   1.0000
   0.250  -0.0316   0.02508   0.01615   0.0086   1.0000   1.0000
   0.500   0.0133   0.02550   0.01653   0.0031   0.9864   1.0000
   0.750   0.1283   0.02638   0.01741  -0.0130   0.9509   1.0000
   1.000   0.2324   0.02633   0.01743  -0.0258   0.9165   1.0000
   1.250   0.3799   0.02449   0.01582  -0.0423   0.8670   1.0000
   1.500   0.4432   0.02236   0.01381  -0.0434   0.8091   1.0000
   1.750   0.4600   0.02095   0.01236  -0.0377   0.7336   1.0000
   2.000   0.4699   0.02009   0.01106  -0.0313   0.6175   1.0000
   2.250   0.4801   0.02024   0.01048  -0.0271   0.5266   1.0000
   2.500   0.4929   0.02074   0.01049  -0.0246   0.4799   1.0000
   2.750   0.5088   0.02131   0.01073  -0.0229   0.4522   1.0000
   3.000   0.5261   0.02190   0.01110  -0.0214   0.4323   1.0000
   3.250   0.5441   0.02252   0.01155  -0.0201   0.4164   1.0000
   3.500   0.5627   0.02320   0.01211  -0.0188   0.4033   1.0000
   3.750   0.5830   0.02397   0.01273  -0.0178   0.3928   1.0000
   4.000   0.6026   0.02477   0.01356  -0.0167   0.3841   1.0000
   4.250   0.6251   0.02573   0.01441  -0.0160   0.3765   1.0000
   4.500   0.6463   0.02670   0.01547  -0.0154   0.3686   1.0000
   4.750   0.6713   0.02785   0.01648  -0.0151   0.3613   1.0000
   5.000   0.6928   0.02900   0.01788  -0.0147   0.3548   1.0000
   5.250   0.7169   0.03029   0.01925  -0.0145   0.3497   1.0000
   5.500   0.7428   0.03178   0.02069  -0.0146   0.3449   1.0000
   5.750   0.7622   0.03333   0.02259  -0.0142   0.3402   1.0000
   6.000   0.7830   0.03495   0.02442  -0.0139   0.3349   1.0000
   6.250   0.8062   0.03664   0.02618  -0.0138   0.3304   1.0000
   6.500   0.8284   0.03870   0.02834  -0.0137   0.3274   1.0000
   6.750   0.8411   0.04110   0.03117  -0.0132   0.3244   1.0000
   7.000   0.8522   0.04374   0.03416  -0.0127   0.3209   1.0000
   7.250   0.8634   0.04655   0.03723  -0.0124   0.3176   1.0000
   7.500   0.8709   0.04987   0.04082  -0.0122   0.3159   1.0000
   7.750   0.8825   0.05297   0.04407  -0.0120   0.3131   1.0000
   8.000   0.8926   0.05645   0.04769  -0.0118   0.3101   1.0000
   8.250   0.8821   0.06160   0.05309  -0.0120   0.3102   1.0000
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