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CLARK W AIRFOIL (clarkw-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: CLARK W AIRFOIL (clarkw-il)
Reynolds number: 500,000
Max Cl/Cd: 91.15 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-clarkw-il-500000-n5.txt
Download as CSV file: xf-clarkw-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: CLARK W AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.8045   0.04341   0.04038  -0.0784   1.0000   0.0219
 -11.750  -0.8066   0.03720   0.03374  -0.0840   0.9948   0.0221
 -11.500  -0.7949   0.03368   0.02986  -0.0865   0.9902   0.0224
 -11.250  -0.7762   0.03121   0.02709  -0.0882   0.9865   0.0228
 -11.000  -0.7521   0.02947   0.02507  -0.0898   0.9843   0.0230
 -10.750  -0.7342   0.02726   0.02266  -0.0903   0.9800   0.0234
 -10.500  -0.7104   0.02579   0.02106  -0.0911   0.9767   0.0237
 -10.250  -0.6842   0.02457   0.01972  -0.0920   0.9741   0.0240
 -10.000  -0.6571   0.02346   0.01850  -0.0929   0.9717   0.0243
  -9.750  -0.6349   0.02252   0.01744  -0.0925   0.9663   0.0245
  -9.500  -0.6086   0.02161   0.01642  -0.0929   0.9627   0.0249
  -9.250  -0.5808   0.02075   0.01543  -0.0936   0.9598   0.0253
  -9.000  -0.5575   0.01996   0.01452  -0.0931   0.9542   0.0257
  -8.750  -0.5323   0.01913   0.01356  -0.0930   0.9493   0.0260
  -8.500  -0.5051   0.01832   0.01262  -0.0933   0.9457   0.0263
  -8.250  -0.4812   0.01761   0.01180  -0.0928   0.9397   0.0266
  -8.000  -0.4557   0.01695   0.01102  -0.0925   0.9342   0.0269
  -7.750  -0.4285   0.01632   0.01029  -0.0925   0.9299   0.0272
  -7.500  -0.4039   0.01579   0.00967  -0.0920   0.9234   0.0274
  -7.250  -0.3775   0.01534   0.00911  -0.0917   0.9176   0.0277
  -7.000  -0.3517   0.01466   0.00835  -0.0915   0.9124   0.0281
  -6.750  -0.3273   0.01402   0.00766  -0.0909   0.9055   0.0286
  -6.500  -0.3011   0.01351   0.00708  -0.0906   0.8996   0.0289
  -6.250  -0.2752   0.01307   0.00660  -0.0903   0.8933   0.0293
  -6.000  -0.2490   0.01268   0.00616  -0.0899   0.8866   0.0297
  -5.750  -0.2222   0.01231   0.00574  -0.0897   0.8808   0.0301
  -5.500  -0.1960   0.01198   0.00536  -0.0893   0.8736   0.0305
  -5.250  -0.1691   0.01167   0.00499  -0.0891   0.8673   0.0309
  -5.000  -0.1424   0.01138   0.00466  -0.0887   0.8604   0.0314
  -4.750  -0.1155   0.01112   0.00434  -0.0885   0.8535   0.0319
  -4.500  -0.0885   0.01088   0.00405  -0.0882   0.8461   0.0324
  -4.250  -0.0617   0.01068   0.00377  -0.0878   0.8361   0.0330
  -4.000  -0.0351   0.01046   0.00350  -0.0874   0.8248   0.0338
  -3.750  -0.0085   0.01024   0.00321  -0.0871   0.8146   0.0349
  -3.500   0.0185   0.01005   0.00298  -0.0868   0.8055   0.0359
  -3.250   0.0456   0.00989   0.00279  -0.0865   0.7971   0.0372
  -3.000   0.0727   0.00976   0.00260  -0.0862   0.7879   0.0386
  -2.750   0.0998   0.00963   0.00244  -0.0859   0.7788   0.0410
  -2.500   0.1266   0.00946   0.00228  -0.0856   0.7697   0.0478
  -2.250   0.1531   0.00923   0.00216  -0.0852   0.7602   0.0767
  -2.000   0.1798   0.00909   0.00206  -0.0849   0.7509   0.0972
  -1.750   0.2066   0.00897   0.00198  -0.0846   0.7406   0.1127
  -1.500   0.2334   0.00887   0.00190  -0.0843   0.7305   0.1302
  -1.250   0.2599   0.00877   0.00184  -0.0840   0.7198   0.1522
  -1.000   0.2865   0.00868   0.00179  -0.0836   0.7081   0.1767
  -0.750   0.3129   0.00858   0.00177  -0.0833   0.6964   0.2074
  -0.500   0.3391   0.00852   0.00176  -0.0829   0.6837   0.2393
  -0.250   0.3654   0.00851   0.00176  -0.0825   0.6704   0.2626
   0.000   0.3915   0.00850   0.00177  -0.0821   0.6561   0.2868
   0.500   0.4438   0.00854   0.00182  -0.0812   0.6250   0.3312
   0.750   0.4696   0.00859   0.00184  -0.0807   0.6080   0.3482
   1.000   0.4954   0.00866   0.00188  -0.0802   0.5903   0.3641
   1.250   0.5209   0.00871   0.00193  -0.0797   0.5717   0.3836
   1.500   0.5460   0.00875   0.00198  -0.0791   0.5516   0.4132
   1.750   0.5706   0.00875   0.00204  -0.0785   0.5324   0.4551
   2.000   0.5832   0.00781   0.00218  -0.0753   0.5151   0.8331
   2.250   0.6138   0.00790   0.00239  -0.0754   0.4943   0.9412
   2.500   0.6495   0.00812   0.00252  -0.0771   0.4740   0.9657
   2.750   0.6841   0.00834   0.00265  -0.0786   0.4568   0.9795
   3.000   0.7192   0.00855   0.00278  -0.0802   0.4410   0.9884
   3.250   0.7540   0.00876   0.00292  -0.0818   0.4258   0.9947
   3.500   0.7900   0.00899   0.00306  -0.0838   0.4102   0.9994
   3.750   0.8135   0.00920   0.00320  -0.0829   0.3959   1.0000
   4.000   0.8355   0.00939   0.00334  -0.0817   0.3824   1.0000
   4.250   0.8579   0.00956   0.00347  -0.0806   0.3717   1.0000
   4.500   0.8799   0.00976   0.00362  -0.0794   0.3615   1.0000
   4.750   0.9017   0.00997   0.00379  -0.0782   0.3494   1.0000
   5.000   0.9240   0.01016   0.00395  -0.0771   0.3383   1.0000
   5.250   0.9461   0.01038   0.00413  -0.0760   0.3277   1.0000
   5.500   0.9678   0.01063   0.00432  -0.0748   0.3146   1.0000
   5.750   0.9895   0.01090   0.00453  -0.0736   0.2986   1.0000
   6.000   1.0109   0.01120   0.00475  -0.0725   0.2800   1.0000
   6.250   1.0327   0.01150   0.00498  -0.0714   0.2647   1.0000
   6.500   1.0548   0.01178   0.00523  -0.0704   0.2523   1.0000
   6.750   1.0769   0.01208   0.00548  -0.0693   0.2386   1.0000
   7.000   1.0981   0.01244   0.00577  -0.0682   0.2224   1.0000
   7.250   1.1190   0.01282   0.00609  -0.0671   0.2039   1.0000
   7.500   1.1390   0.01327   0.00645  -0.0658   0.1822   1.0000
   7.750   1.1572   0.01384   0.00688  -0.0643   0.1558   1.0000
   8.000   1.1742   0.01449   0.00738  -0.0626   0.1308   1.0000
   8.250   1.1919   0.01507   0.00788  -0.0610   0.1135   1.0000
   8.500   1.2097   0.01561   0.00837  -0.0595   0.1002   1.0000
   8.750   1.2263   0.01616   0.00886  -0.0577   0.0875   1.0000
   9.000   1.2419   0.01677   0.00940  -0.0558   0.0742   1.0000
   9.250   1.2572   0.01740   0.00998  -0.0539   0.0629   1.0000
   9.500   1.2729   0.01801   0.01056  -0.0522   0.0551   1.0000
   9.750   1.2885   0.01863   0.01117  -0.0504   0.0496   1.0000
  10.000   1.3040   0.01926   0.01181  -0.0487   0.0453   1.0000
  10.250   1.3193   0.01991   0.01248  -0.0471   0.0421   1.0000
  10.500   1.3347   0.02055   0.01316  -0.0455   0.0394   1.0000
  10.750   1.3485   0.02131   0.01393  -0.0437   0.0370   1.0000
  11.000   1.3630   0.02204   0.01471  -0.0421   0.0352   1.0000
  11.250   1.3772   0.02279   0.01551  -0.0406   0.0334   1.0000
  11.500   1.3898   0.02366   0.01642  -0.0389   0.0316   1.0000
  11.750   1.4010   0.02465   0.01744  -0.0372   0.0300   1.0000
  12.000   1.4141   0.02552   0.01839  -0.0358   0.0288   1.0000
  12.250   1.4259   0.02651   0.01944  -0.0343   0.0275   1.0000
  12.500   1.4361   0.02765   0.02063  -0.0328   0.0261   1.0000
  12.750   1.4447   0.02895   0.02197  -0.0313   0.0249   1.0000
  13.000   1.4553   0.03011   0.02322  -0.0300   0.0238   1.0000
  13.250   1.4646   0.03142   0.02460  -0.0288   0.0226   1.0000
  13.500   1.4722   0.03291   0.02614  -0.0275   0.0216   1.0000
  13.750   1.4777   0.03462   0.02791  -0.0263   0.0207   1.0000
  14.000   1.4845   0.03628   0.02967  -0.0252   0.0200   1.0000
  14.250   1.4904   0.03806   0.03154  -0.0242   0.0191   1.0000
  14.500   1.4951   0.04001   0.03357  -0.0234   0.0183   1.0000
  14.750   1.4983   0.04217   0.03579  -0.0226   0.0176   1.0000
  15.000   1.4993   0.04465   0.03834  -0.0220   0.0170   1.0000
  15.250   1.5009   0.04715   0.04094  -0.0215   0.0164   1.0000
  15.500   1.5019   0.04980   0.04370  -0.0212   0.0159   1.0000
  15.750   1.5017   0.05269   0.04669  -0.0211   0.0154   1.0000
  16.000   1.5004   0.05583   0.04993  -0.0211   0.0150   1.0000
  16.250   1.4976   0.05921   0.05341  -0.0214   0.0146   1.0000
  16.500   1.4935   0.06288   0.05718  -0.0218   0.0143   1.0000
  16.750   1.4875   0.06692   0.06132  -0.0225   0.0140   1.0000
  17.000   1.4795   0.07136   0.06586  -0.0235   0.0137   1.0000
  17.250   1.4717   0.07582   0.07044  -0.0245   0.0135   1.0000
  17.500   1.4644   0.08031   0.07506  -0.0257   0.0133   1.0000
  17.750   1.4561   0.08504   0.07991  -0.0270   0.0130   1.0000
  18.000   1.4472   0.08991   0.08489  -0.0285   0.0128   1.0000
  18.250   1.4377   0.09489   0.09000  -0.0301   0.0126   1.0000
  18.500   1.4279   0.10002   0.09523  -0.0318   0.0124   1.0000
  18.750   1.4177   0.10526   0.10059  -0.0337   0.0122   1.0000
  19.000   1.4078   0.11051   0.10594  -0.0357   0.0120   1.0000
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