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NACA 23012 12% (naca23012-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NACA 23012 12% (naca23012-il)
Reynolds number: 50,000
Max Cl/Cd: 24.18 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca23012-il-50000.txt
Download as CSV file: xf-naca23012-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 23012  12%                                 
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.5047   0.12904   0.12168   0.0135   1.0000   0.2848
 -10.500  -0.5118   0.12671   0.11943   0.0128   1.0000   0.2973
 -10.250  -0.5206   0.12519   0.11797   0.0125   1.0000   0.3117
 -10.000  -0.5113   0.12175   0.11455   0.0133   1.0000   0.3281
  -9.750  -0.5055   0.11864   0.11148   0.0139   1.0000   0.3448
  -9.500  -0.5015   0.11570   0.10859   0.0146   1.0000   0.3616
  -9.250  -0.4936   0.11236   0.10528   0.0154   1.0000   0.3786
  -9.000  -0.4844   0.10893   0.10188   0.0162   1.0000   0.3954
  -8.750  -0.4760   0.10561   0.09859   0.0170   1.0000   0.4123
  -8.500  -0.4651   0.10207   0.09508   0.0178   1.0000   0.4294
  -8.250  -0.4533   0.09850   0.09154   0.0186   1.0000   0.4467
  -8.000  -0.4479   0.09551   0.08859   0.0195   1.0000   0.4633
  -7.750  -0.4230   0.09056   0.08361   0.0188   1.0000   0.4692
  -7.250  -0.6036   0.06155   0.05448  -0.0185   1.0000   0.2082
  -7.000  -0.6138   0.05457   0.04681  -0.0194   1.0000   0.1781
  -6.750  -0.6098   0.04997   0.04160  -0.0180   1.0000   0.1632
  -6.500  -0.5985   0.04632   0.03763  -0.0164   1.0000   0.1575
  -6.250  -0.5883   0.04319   0.03383  -0.0143   1.0000   0.1524
  -6.000  -0.5734   0.04118   0.03116  -0.0120   1.0000   0.1500
  -5.750  -0.5544   0.03843   0.02819  -0.0106   1.0000   0.1491
  -5.500  -0.5343   0.03604   0.02551  -0.0091   1.0000   0.1485
  -5.250  -0.5141   0.03423   0.02329  -0.0074   1.0000   0.1499
  -5.000  -0.4919   0.03189   0.02091  -0.0063   1.0000   0.1534
  -4.750  -0.4682   0.03013   0.01906  -0.0052   1.0000   0.1566
  -4.500  -0.4440   0.02866   0.01743  -0.0041   1.0000   0.1619
  -4.250  -0.4187   0.02722   0.01591  -0.0031   1.0000   0.1689
  -4.000  -0.3926   0.02590   0.01466  -0.0021   1.0000   0.1780
  -3.750  -0.3673   0.02468   0.01355  -0.0012   1.0000   0.1910
  -3.500  -0.3440   0.02357   0.01255   0.0000   1.0000   0.2081
  -3.250  -0.3239   0.02239   0.01165   0.0013   1.0000   0.2363
  -3.000  -0.3096   0.02060   0.01087   0.0033   1.0000   0.3316
  -2.750   0.0002   0.02270   0.01377  -0.0271   1.0000   1.0000
  -2.500   0.0063   0.02214   0.01317  -0.0255   1.0000   1.0000
  -2.250   0.0088   0.02169   0.01270  -0.0233   1.0000   1.0000
  -2.000   0.0071   0.02134   0.01234  -0.0203   1.0000   1.0000
  -1.750   0.0008   0.02111   0.01211  -0.0166   1.0000   1.0000
  -1.500  -0.0103   0.02100   0.01200  -0.0121   1.0000   1.0000
  -1.250  -0.0241   0.02099   0.01198  -0.0071   1.0000   1.0000
  -1.000  -0.0372   0.02110   0.01204  -0.0023   1.0000   1.0000
  -0.750  -0.0466   0.02132   0.01220   0.0018   1.0000   1.0000
  -0.500  -0.0514   0.02167   0.01247   0.0052   1.0000   1.0000
  -0.250  -0.0521   0.02214   0.01286   0.0077   1.0000   1.0000
   0.000   0.0256   0.02304   0.01364  -0.0035   0.9766   1.0000
   0.250   0.1183   0.02356   0.01409  -0.0163   0.9457   1.0000
   0.500   0.2113   0.02356   0.01408  -0.0283   0.9139   1.0000
   0.750   0.2958   0.02306   0.01363  -0.0376   0.8807   1.0000
   1.000   0.3543   0.02248   0.01305  -0.0414   0.8451   1.0000
   1.250   0.3941   0.02203   0.01254  -0.0416   0.8085   1.0000
   1.500   0.4231   0.02175   0.01215  -0.0398   0.7719   1.0000
   1.750   0.4446   0.02177   0.01205  -0.0371   0.7331   1.0000
   2.000   0.4658   0.02188   0.01199  -0.0345   0.6960   1.0000
   2.250   0.4869   0.02212   0.01206  -0.0321   0.6610   1.0000
   2.500   0.5080   0.02248   0.01225  -0.0299   0.6285   1.0000
   2.750   0.5300   0.02287   0.01242  -0.0279   0.6001   1.0000
   3.000   0.5503   0.02349   0.01294  -0.0263   0.5722   1.0000
   3.250   0.5728   0.02403   0.01329  -0.0247   0.5498   1.0000
   3.500   0.5932   0.02480   0.01404  -0.0233   0.5275   1.0000
   3.750   0.6145   0.02557   0.01475  -0.0220   0.5083   1.0000
   4.000   0.6358   0.02638   0.01551  -0.0208   0.4910   1.0000
   4.250   0.6572   0.02725   0.01636  -0.0196   0.4755   1.0000
   4.500   0.6789   0.02814   0.01720  -0.0184   0.4615   1.0000
   4.750   0.7012   0.02900   0.01801  -0.0173   0.4483   1.0000
   5.000   0.7199   0.03021   0.01937  -0.0162   0.4352   1.0000
   5.250   0.7391   0.03147   0.02072  -0.0150   0.4234   1.0000
   5.500   0.7619   0.03244   0.02163  -0.0140   0.4129   1.0000
   5.750   0.7788   0.03394   0.02332  -0.0129   0.4018   1.0000
   6.000   0.7963   0.03550   0.02502  -0.0118   0.3919   1.0000
   6.250   0.8185   0.03661   0.02613  -0.0108   0.3821   1.0000
   6.500   0.8291   0.03891   0.02872  -0.0095   0.3729   1.0000
   6.750   0.8553   0.03981   0.02954  -0.0087   0.3641   1.0000
   7.000   0.8572   0.04292   0.03306  -0.0072   0.3553   1.0000
   7.250   0.8859   0.04370   0.03373  -0.0064   0.3470   1.0000
   7.500   0.8761   0.04807   0.03859  -0.0049   0.3397   1.0000
   7.750   0.9101   0.04830   0.03868  -0.0041   0.3306   1.0000
   8.000   0.8822   0.05464   0.04549  -0.0028   0.3259   1.0000
   8.250   0.8492   0.06185   0.05293  -0.0028   0.3227   1.0000
   8.500   0.7811   0.07349   0.06459  -0.0062   0.3258   1.0000
   8.750   0.7234   0.08559   0.07658  -0.0130   0.3341   1.0000
   9.000   0.7283   0.08983   0.08086  -0.0137   0.3319   1.0000
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