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DF102 (df102-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: DF102 (df102-il)
Reynolds number: 50,000
Max Cl/Cd: 32.65 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-df102-il-50000.txt
Download as CSV file: xf-df102-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: DF102                                           
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3927   0.09841   0.09162  -0.0177   1.0000   0.2819
  -8.250  -0.3842   0.09466   0.08790  -0.0174   1.0000   0.2858
  -8.000  -0.4840   0.08193   0.07555  -0.0364   1.0000   0.1599
  -7.750  -0.4830   0.07640   0.07008  -0.0363   1.0000   0.1488
  -7.500  -0.4975   0.07069   0.06439  -0.0379   1.0000   0.1379
  -7.250  -0.5242   0.06376   0.05734  -0.0399   1.0000   0.1276
  -7.000  -0.5573   0.05568   0.04865  -0.0408   1.0000   0.1171
  -6.750  -0.5578   0.05169   0.04441  -0.0392   1.0000   0.1168
  -6.500  -0.5567   0.04771   0.04004  -0.0375   1.0000   0.1169
  -6.250  -0.5516   0.04399   0.03582  -0.0358   1.0000   0.1174
  -6.000  -0.5414   0.04064   0.03219  -0.0341   1.0000   0.1188
  -5.750  -0.5272   0.03795   0.02934  -0.0324   1.0000   0.1213
  -5.500  -0.5121   0.03564   0.02674  -0.0308   1.0000   0.1263
  -5.250  -0.4960   0.03314   0.02374  -0.0292   1.0000   0.1333
  -5.000  -0.4774   0.03133   0.02181  -0.0277   1.0000   0.1417
  -4.750  -0.4583   0.02961   0.01993  -0.0261   1.0000   0.1538
  -4.500  -0.4387   0.02811   0.01820  -0.0246   1.0000   0.1744
  -4.250  -0.4201   0.02686   0.01717  -0.0228   1.0000   0.2074
  -4.000  -0.4042   0.02590   0.01655  -0.0205   1.0000   0.2711
  -3.750  -0.3900   0.02538   0.01622  -0.0180   1.0000   0.3396
  -3.500  -0.3755   0.02504   0.01611  -0.0154   1.0000   0.3914
  -3.250  -0.3592   0.02462   0.01578  -0.0133   1.0000   0.4358
  -3.000  -0.3415   0.02414   0.01537  -0.0114   1.0000   0.4732
  -2.750  -0.3232   0.02364   0.01485  -0.0097   1.0000   0.5080
  -2.500  -0.3043   0.02317   0.01442  -0.0082   1.0000   0.5430
  -2.250  -0.2847   0.02274   0.01404  -0.0068   1.0000   0.5821
  -2.000  -0.2656   0.02229   0.01372  -0.0052   1.0000   0.6295
  -1.750  -0.2482   0.02175   0.01348  -0.0031   1.0000   0.6942
  -1.500  -0.1569   0.02101   0.01336  -0.0135   1.0000   1.0000
  -1.250  -0.1436   0.02102   0.01284  -0.0136   1.0000   1.0000
  -1.000  -0.1276   0.02130   0.01276  -0.0130   1.0000   1.0000
  -0.750  -0.1114   0.02166   0.01283  -0.0123   1.0000   1.0000
  -0.500  -0.0949   0.02206   0.01298  -0.0117   1.0000   1.0000
  -0.250  -0.0784   0.02252   0.01323  -0.0110   1.0000   1.0000
   0.000  -0.0617   0.02301   0.01354  -0.0105   1.0000   1.0000
   0.250  -0.0450   0.02356   0.01392  -0.0099   1.0000   1.0000
   0.500  -0.0283   0.02414   0.01435  -0.0095   1.0000   1.0000
   0.750  -0.0070   0.02487   0.01494  -0.0099   0.9980   1.0000
   1.000   0.0419   0.02630   0.01622  -0.0155   0.9844   1.0000
   1.250   0.0893   0.02765   0.01746  -0.0206   0.9702   1.0000
   1.500   0.1331   0.02884   0.01857  -0.0250   0.9551   1.0000
   1.750   0.1739   0.02986   0.01953  -0.0286   0.9375   1.0000
   2.000   0.2318   0.03085   0.02051  -0.0344   0.9128   1.0000
   2.250   0.2847   0.03139   0.02105  -0.0387   0.8851   1.0000
   2.500   0.3356   0.03174   0.02144  -0.0423   0.8599   1.0000
   2.750   0.3923   0.03183   0.02160  -0.0463   0.8372   1.0000
   3.000   0.4335   0.03183   0.02168  -0.0477   0.8131   1.0000
   3.250   0.5073   0.03080   0.02084  -0.0528   0.7904   1.0000
   3.500   0.5497   0.03007   0.02023  -0.0531   0.7643   1.0000
   3.750   0.5984   0.02877   0.01909  -0.0534   0.7374   1.0000
   4.000   0.6471   0.02711   0.01756  -0.0529   0.7072   1.0000
   4.250   0.6968   0.02509   0.01558  -0.0518   0.6708   1.0000
   4.500   0.7262   0.02409   0.01453  -0.0487   0.6201   1.0000
   4.750   0.7530   0.02356   0.01371  -0.0455   0.5598   1.0000
   5.000   0.7761   0.02377   0.01350  -0.0428   0.5034   1.0000
   5.250   0.7975   0.02443   0.01382  -0.0407   0.4590   1.0000
   5.500   0.8188   0.02533   0.01452  -0.0391   0.4245   1.0000
   5.750   0.8422   0.02630   0.01527  -0.0379   0.3974   1.0000
   6.000   0.8652   0.02737   0.01625  -0.0369   0.3747   1.0000
   6.250   0.8906   0.02855   0.01731  -0.0363   0.3569   1.0000
   6.500   0.9152   0.02982   0.01850  -0.0356   0.3411   1.0000
   6.750   0.9379   0.03115   0.01985  -0.0348   0.3267   1.0000
   7.000   0.9584   0.03266   0.02157  -0.0337   0.3149   1.0000
   7.250   0.9795   0.03440   0.02347  -0.0329   0.3056   1.0000
   7.500   1.0053   0.03601   0.02503  -0.0326   0.2965   1.0000
   7.750   1.0183   0.03798   0.02739  -0.0309   0.2881   1.0000
   8.250   1.0498   0.04228   0.03218  -0.0283   0.2747   1.0000
   8.500   1.0663   0.04460   0.03470  -0.0272   0.2698   1.0000
   8.750   1.0817   0.04721   0.03748  -0.0262   0.2653   1.0000
   9.000   1.0774   0.05061   0.04136  -0.0236   0.2618   1.0000
   9.250   1.0750   0.05399   0.04506  -0.0215   0.2580   1.0000
   9.500   1.1016   0.05604   0.04710  -0.0213   0.2522   1.0000
   9.750   1.0904   0.06043   0.05184  -0.0190   0.2512   1.0000
  10.000   1.0689   0.06553   0.05721  -0.0168   0.2513   1.0000
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