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DF 101 AIRFOIL (df101-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: DF 101 AIRFOIL (df101-il)
Reynolds number: 50,000
Max Cl/Cd: 31.53 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-df101-il-50000.txt
Download as CSV file: xf-df101-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: DF 101 AIRFOIL                                  
  
 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  -0.3896   0.09769   0.09092  -0.0193   1.0000   0.2740
  -8.250  -0.4136   0.09624   0.08967  -0.0203   1.0000   0.2798
  -8.000  -0.4999   0.07775   0.07146  -0.0418   1.0000   0.1347
  -7.750  -0.5279   0.07015   0.06380  -0.0446   1.0000   0.1207
  -7.500  -0.5275   0.06630   0.05994  -0.0434   1.0000   0.1187
  -7.250  -0.5328   0.06224   0.05584  -0.0423   1.0000   0.1169
  -7.000  -0.5404   0.05792   0.05139  -0.0413   1.0000   0.1151
  -6.750  -0.5475   0.05329   0.04650  -0.0401   1.0000   0.1132
  -6.500  -0.5504   0.04889   0.04174  -0.0387   1.0000   0.1125
  -6.250  -0.5473   0.04495   0.03740  -0.0371   1.0000   0.1129
  -6.000  -0.5400   0.04121   0.03318  -0.0354   1.0000   0.1137
  -5.750  -0.5287   0.03779   0.02921  -0.0337   1.0000   0.1156
  -5.500  -0.5151   0.03485   0.02564  -0.0320   1.0000   0.1212
  -5.250  -0.4980   0.03304   0.02378  -0.0304   1.0000   0.1304
  -5.000  -0.4793   0.03082   0.02130  -0.0288   1.0000   0.1396
  -4.750  -0.4609   0.02934   0.01972  -0.0272   1.0000   0.1570
  -4.500  -0.4412   0.02771   0.01803  -0.0256   1.0000   0.1805
  -4.250  -0.4240   0.02661   0.01714  -0.0236   1.0000   0.2267
  -4.000  -0.4093   0.02578   0.01657  -0.0210   1.0000   0.2981
  -3.750  -0.3952   0.02538   0.01638  -0.0185   1.0000   0.3584
  -3.500  -0.3800   0.02500   0.01615  -0.0161   1.0000   0.4068
  -3.250  -0.3629   0.02452   0.01570  -0.0141   1.0000   0.4479
  -3.000  -0.3447   0.02399   0.01520  -0.0124   1.0000   0.4828
  -2.750  -0.3263   0.02349   0.01465  -0.0108   1.0000   0.5171
  -2.500  -0.3071   0.02302   0.01420  -0.0094   1.0000   0.5526
  -2.250  -0.2874   0.02258   0.01381  -0.0080   1.0000   0.5936
  -2.000  -0.2687   0.02211   0.01351  -0.0064   1.0000   0.6430
  -1.750  -0.2523   0.02155   0.01328  -0.0039   1.0000   0.7140
  -1.500  -0.1616   0.02089   0.01296  -0.0154   1.0000   1.0000
  -1.250  -0.1472   0.02101   0.01260  -0.0152   1.0000   1.0000
  -1.000  -0.1314   0.02131   0.01256  -0.0146   1.0000   1.0000
  -0.750  -0.1153   0.02168   0.01263  -0.0140   1.0000   1.0000
  -0.500  -0.0991   0.02210   0.01281  -0.0133   1.0000   1.0000
  -0.250  -0.0828   0.02257   0.01307  -0.0127   1.0000   1.0000
   0.000  -0.0665   0.02309   0.01340  -0.0122   1.0000   1.0000
   0.250  -0.0501   0.02365   0.01379  -0.0117   1.0000   1.0000
   0.500  -0.0201   0.02457   0.01454  -0.0138   0.9948   1.0000
   0.750   0.0298   0.02589   0.01568  -0.0196   0.9796   1.0000
   1.000   0.0757   0.02706   0.01672  -0.0244   0.9639   1.0000
   1.250   0.1201   0.02815   0.01771  -0.0288   0.9476   1.0000
   1.500   0.1646   0.02919   0.01866  -0.0330   0.9308   1.0000
   1.750   0.2108   0.03016   0.01959  -0.0372   0.9136   1.0000
   2.000   0.2525   0.03098   0.02039  -0.0404   0.8956   1.0000
   2.250   0.2882   0.03166   0.02106  -0.0424   0.8762   1.0000
   2.500   0.3318   0.03226   0.02168  -0.0454   0.8568   1.0000
   2.750   0.3837   0.03265   0.02213  -0.0492   0.8380   1.0000
   3.000   0.4127   0.03308   0.02261  -0.0494   0.8163   1.0000
   3.250   0.4628   0.03310   0.02272  -0.0523   0.7966   1.0000
   3.500   0.5050   0.03308   0.02281  -0.0538   0.7758   1.0000
   3.750   0.5517   0.03270   0.02256  -0.0554   0.7546   1.0000
   4.000   0.6086   0.03162   0.02167  -0.0575   0.7360   1.0000
   4.250   0.6375   0.03143   0.02158  -0.0562   0.7119   1.0000
   4.500   0.6913   0.02997   0.02028  -0.0570   0.6918   1.0000
   4.750   0.7210   0.02957   0.01997  -0.0553   0.6657   1.0000
   5.000   0.7547   0.02897   0.01944  -0.0540   0.6394   1.0000
   5.250   0.7883   0.02840   0.01891  -0.0525   0.6118   1.0000
   5.500   0.8187   0.02811   0.01865  -0.0509   0.5833   1.0000
   5.750   0.8464   0.02808   0.01859  -0.0492   0.5545   1.0000
   6.000   0.8731   0.02825   0.01871  -0.0476   0.5267   1.0000
   6.250   0.8996   0.02853   0.01895  -0.0462   0.5002   1.0000
   6.500   0.9191   0.02935   0.01981  -0.0443   0.4749   1.0000
   6.750   0.9418   0.03008   0.02052  -0.0428   0.4518   1.0000
   7.000   0.9640   0.03093   0.02139  -0.0414   0.4302   1.0000
   7.250   0.9874   0.03183   0.02227  -0.0402   0.4102   1.0000
   7.500   1.0053   0.03311   0.02372  -0.0386   0.3914   1.0000
   7.750   1.0256   0.03431   0.02499  -0.0372   0.3735   1.0000
   8.000   1.0467   0.03558   0.02632  -0.0359   0.3567   1.0000
   8.250   1.0686   0.03685   0.02763  -0.0347   0.3401   1.0000
   8.500   1.0891   0.03833   0.02916  -0.0334   0.3241   1.0000
   8.750   1.1036   0.04003   0.03109  -0.0316   0.3085   1.0000
   9.000   1.1173   0.04181   0.03306  -0.0297   0.2930   1.0000
   9.250   1.1290   0.04363   0.03507  -0.0275   0.2770   1.0000
   9.500   1.1397   0.04550   0.03713  -0.0253   0.2607   1.0000
   9.750   1.1528   0.04698   0.03869  -0.0232   0.2422   1.0000
  10.000   1.1706   0.04806   0.03970  -0.0214   0.2209   1.0000
  10.500   1.1907   0.05062   0.04224  -0.0165   0.1791   1.0000
  10.750   1.1890   0.05280   0.04460  -0.0133   0.1640   1.0000
  11.000   1.1891   0.05499   0.04688  -0.0104   0.1501   1.0000
  11.250   0.9182   0.08952   0.08228  -0.0184   0.2407   1.0000
  11.500   0.8937   0.09861   0.09129  -0.0223   0.2385   1.0000
  11.750   0.8721   0.10742   0.10003  -0.0260   0.2378   1.0000
  12.000   0.8540   0.11560   0.10817  -0.0295   0.2375   1.0000
  12.250   0.8400   0.12318   0.11573  -0.0326   0.2373   1.0000
  12.500   1.0357   0.08369   0.07693  -0.0009   0.1403   1.0000
  12.750   1.0146   0.09033   0.08361  -0.0029   0.1390   1.0000
  13.000   0.5833   0.14530   0.13807  -0.0426   0.3472   1.0000
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