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CHEN AIRFOIL (chen-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: CHEN AIRFOIL (chen-il)
Reynolds number: 1,000,000
Max Cl/Cd: 125.39 at α=14.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-chen-il-1000000.txt
Download as CSV file: xf-chen-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: CHEN AIRFOIL                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.0197   0.11018   0.10570  -0.0601   0.3293   0.0119
 -10.250  -0.0143   0.10686   0.10240  -0.0625   0.3291   0.0124
 -10.000  -0.0071   0.10403   0.09958  -0.0645   0.3293   0.0124
  -9.750   0.0543   0.09074   0.08657  -0.0643   0.3297   0.0124
  -9.500   0.0634   0.08754   0.08337  -0.0640   0.3297   0.0127
  -9.250   0.0191   0.09617   0.09175  -0.0686   0.3293   0.0124
  -9.000   0.0283   0.09384   0.08943  -0.0697   0.3292   0.0124
  -8.750   0.0391   0.09105   0.08665  -0.0698   0.3292   0.0129
  -8.500   0.0482   0.08897   0.08459  -0.0706   0.3292   0.0131
  -8.250   0.0555   0.08653   0.08216  -0.0716   0.3292   0.0132
  -8.000   0.0640   0.08453   0.08018  -0.0723   0.3291   0.0136
  -7.750   0.0702   0.08219   0.07787  -0.0732   0.3292   0.0138
  -7.500   0.0761   0.08002   0.07572  -0.0738   0.3292   0.0139
  -7.250   0.0791   0.07765   0.07338  -0.0746   0.3292   0.0149
  -7.000   0.0798   0.07546   0.07123  -0.0750   0.3292   0.0149
  -6.750   0.0711   0.07326   0.06906  -0.0741   0.3292   0.0154
  -6.500   0.0644   0.07174   0.06756  -0.0728   0.3292   0.0155
  -6.250   0.0661   0.06953   0.06536  -0.0722   0.3293   0.0156
  -6.000   0.0702   0.06739   0.06323  -0.0715   0.3294   0.0156
  -5.750   0.0764   0.06535   0.06117  -0.0708   0.3294   0.0156
  -5.500   0.0772   0.06215   0.05796  -0.0696   0.3294   0.0158
  -5.250   0.0854   0.06001   0.05581  -0.0686   0.3293   0.0158
  -5.000   0.0960   0.05852   0.05433  -0.0673   0.3293   0.0161
  -4.750   0.1072   0.05687   0.05265  -0.0663   0.3292   0.0162
  -4.500   0.1188   0.05520   0.05097  -0.0652   0.3293   0.0164
  -4.250   0.1314   0.05358   0.04933  -0.0640   0.3292   0.0168
  -4.000   0.1444   0.05185   0.04756  -0.0628   0.3292   0.0172
  -3.750   0.1578   0.04998   0.04565  -0.0614   0.3292   0.0180
  -3.500   0.1677   0.04586   0.04135  -0.0585   0.3292   0.0194
  -3.250   0.1820   0.04439   0.03985  -0.0569   0.3290   0.0197
  -3.000   0.1985   0.04361   0.03908  -0.0557   0.3292   0.0201
  -2.750   0.2151   0.04229   0.03770  -0.0541   0.3290   0.0204
  -2.500   0.2323   0.04103   0.03640  -0.0525   0.3290   0.0210
  -2.250   0.2524   0.03883   0.03403  -0.0498   0.3289   0.0233
  -2.000   0.2071   0.01855   0.01196  -0.0327   0.3290   0.0196
  -1.750   0.2340   0.01791   0.01120  -0.0323   0.3288   0.0200
  -1.500   0.2595   0.01786   0.01115  -0.0317   0.3289   0.0207
  -1.250   0.2865   0.01757   0.01080  -0.0313   0.3287   0.0213
  -1.000   0.3129   0.01745   0.01064  -0.0308   0.3286   0.0221
  -0.750   0.3392   0.01736   0.01052  -0.0303   0.3285   0.0229
  -0.500   0.3648   0.01733   0.01046  -0.0296   0.3284   0.0233
  -0.250   0.3905   0.01706   0.01016  -0.0290   0.3281   0.0245
   0.000   0.4157   0.01703   0.01015  -0.0282   0.3277   0.0262
   0.250   0.4400   0.01708   0.01019  -0.0273   0.3274   0.0275
   0.500   0.4634   0.01714   0.01027  -0.0263   0.3274   0.0295
   0.750   0.4867   0.01731   0.01048  -0.0252   0.3274   0.0317
   1.000   0.5098   0.01742   0.01062  -0.0241   0.3271   0.0354
   1.250   0.5329   0.01768   0.01091  -0.0230   0.3271   0.0394
   1.500   0.5554   0.01794   0.01122  -0.0219   0.3271   0.0448
   1.750   0.5783   0.01819   0.01148  -0.0209   0.3268   0.0486
   2.000   0.6008   0.01848   0.01183  -0.0197   0.3267   0.0522
   2.250   0.6235   0.01882   0.01220  -0.0187   0.3266   0.0552
   2.500   0.6456   0.01908   0.01248  -0.0175   0.3265   0.0575
   2.750   0.6683   0.01925   0.01270  -0.0165   0.3261   0.0611
   3.000   0.6909   0.01957   0.01305  -0.0154   0.3259   0.0642
   3.250   0.7134   0.01999   0.01350  -0.0145   0.3256   0.0668
   3.500   0.7336   0.02026   0.01383  -0.0130   0.3255   0.0714
   3.750   0.7548   0.02067   0.01428  -0.0119   0.3253   0.0753
   4.000   0.7775   0.02093   0.01455  -0.0109   0.3249   0.0783
   4.250   0.7982   0.02118   0.01485  -0.0096   0.3246   0.0834
   4.500   0.8211   0.02135   0.01504  -0.0087   0.3241   0.0873
   4.750   0.8427   0.02170   0.01541  -0.0076   0.3238   0.0907
   5.000   0.8633   0.02206   0.01581  -0.0065   0.3236   0.0946
   5.250   0.8842   0.02243   0.01622  -0.0053   0.3233   0.0994
   5.500   0.9059   0.02274   0.01657  -0.0044   0.3230   0.1033
   5.750   0.9270   0.02312   0.01698  -0.0033   0.3227   0.1069
   6.000   0.9491   0.02341   0.01732  -0.0025   0.3224   0.1146
   6.250   0.9708   0.02376   0.01771  -0.0016   0.3221   0.1235
   6.500   0.9934   0.02404   0.01804  -0.0008   0.3218   0.1391
   6.750   1.0160   0.02433   0.01837  -0.0001   0.3215   0.1552
   7.000   1.0389   0.02461   0.01868   0.0006   0.3212   0.1681
   7.250   1.0638   0.02475   0.01884   0.0009   0.3208   0.1811
   7.500   1.0906   0.02477   0.01887   0.0010   0.3205   0.1942
   8.500   1.3634   0.02496   0.02067  -0.0358   0.3154   0.9917
   8.750   1.3876   0.02654   0.02236  -0.0367   0.3156   0.9944
   9.000   1.4655   0.02536   0.02116  -0.0467   0.3136   0.9990
   9.250   1.4935   0.02587   0.02173  -0.0476   0.3130   1.0000
   9.500   1.5119   0.02611   0.02201  -0.0462   0.3123   1.0000
   9.750   1.5324   0.02619   0.02212  -0.0451   0.3117   1.0000
  10.000   1.5658   0.02516   0.02101  -0.0457   0.3107   1.0000
  10.250   1.5806   0.02576   0.02167  -0.0439   0.3103   1.0000
  10.500   1.6075   0.02530   0.02120  -0.0437   0.3098   1.0000
  10.750   1.6332   0.02500   0.02089  -0.0433   0.3092   1.0000
  11.000   1.6655   0.02410   0.01992  -0.0438   0.3085   1.0000
  11.250   1.6759   0.02506   0.02098  -0.0415   0.3084   1.0000
  11.500   1.7058   0.02441   0.02029  -0.0417   0.3078   1.0000
  11.750   1.7331   0.02397   0.01983  -0.0416   0.3073   1.0000
  12.000   1.7773   0.02205   0.01773  -0.0437   0.3061   1.0000
  12.250   1.7994   0.02228   0.01795  -0.0431   0.3047   1.0000
  12.500   1.8251   0.02115   0.01685  -0.0424   0.3037   1.0000
  12.750   1.8438   0.02099   0.01676  -0.0409   0.3027   1.0000
  13.000   1.8597   0.02127   0.01713  -0.0393   0.3021   1.0000
  13.250   1.8895   0.01987   0.01572  -0.0391   0.2990   1.0000
  13.500   1.9268   0.01790   0.01366  -0.0400   0.2954   1.0000
  13.750   1.9492   0.01761   0.01339  -0.0392   0.2943   1.0000
  14.000   1.9725   0.01715   0.01297  -0.0384   0.2919   1.0000
  14.250   1.9878   0.01762   0.01356  -0.0368   0.2897   1.0000
  14.500   2.0094   0.01752   0.01355  -0.0361   0.2819   1.0000
  14.750   2.0350   0.01623   0.01196  -0.0353   0.2562   1.0000
  15.000   2.0345   0.01691   0.01262  -0.0309   0.2465   1.0000
  15.250   2.0028   0.01843   0.01409  -0.0215   0.2288   1.0000
  15.500   1.9797   0.02002   0.01570  -0.0145   0.2178   1.0000
  15.750   1.9208   0.02387   0.01958  -0.0056   0.2015   1.0000
  16.000   1.9208   0.02529   0.02113  -0.0040   0.2034   1.0000
  16.250   1.8708   0.03272   0.02884  -0.0050   0.2051   1.0000
  16.500   1.7355   0.05120   0.04794  -0.0080   0.2261   1.0000
  16.750   1.4696   0.08346   0.08056  -0.0131   0.2328   1.0000
  17.000   1.4703   0.08587   0.08299  -0.0134   0.2307   1.0000
  17.250   1.4594   0.08974   0.08679  -0.0141   0.2197   1.0000
  17.500   1.4474   0.09380   0.09075  -0.0148   0.2060   1.0000
  17.750   1.4463   0.09653   0.09347  -0.0153   0.2005   1.0000
  18.000   1.4370   0.10033   0.09722  -0.0160   0.1915   1.0000
  18.250   1.4354   0.10321   0.10010  -0.0166   0.1866   1.0000
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