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CLARK W AIRFOIL (clarkw-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: CLARK W AIRFOIL (clarkw-il)
Reynolds number: 500,000
Max Cl/Cd: 98.74 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-clarkw-il-500000.txt
Download as CSV file: xf-clarkw-il-500000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3212   0.08831   0.08613  -0.0401   0.9986   0.0419
  -9.500  -0.3111   0.08456   0.08238  -0.0425   0.9971   0.0429
  -9.250  -0.5941   0.03731   0.03372  -0.0824   0.9844   0.0341
  -9.000  -0.5712   0.03458   0.03067  -0.0842   0.9811   0.0339
  -8.750  -0.5516   0.03154   0.02733  -0.0851   0.9762   0.0338
  -8.500  -0.5284   0.02822   0.02360  -0.0867   0.9732   0.0339
  -8.250  -0.5040   0.02431   0.01928  -0.0884   0.9713   0.0343
  -8.000  -0.4727   0.02214   0.01688  -0.0902   0.9702   0.0346
  -7.750  -0.4510   0.02074   0.01532  -0.0895   0.9639   0.0349
  -7.500  -0.4201   0.01943   0.01388  -0.0906   0.9613   0.0353
  -7.250  -0.3881   0.01831   0.01264  -0.0918   0.9592   0.0357
  -7.000  -0.3556   0.01734   0.01156  -0.0930   0.9572   0.0363
  -6.750  -0.3288   0.01663   0.01077  -0.0929   0.9525   0.0369
  -6.500  -0.3015   0.01591   0.00997  -0.0929   0.9476   0.0376
  -6.250  -0.2714   0.01513   0.00910  -0.0933   0.9442   0.0380
  -6.000  -0.2409   0.01443   0.00831  -0.0938   0.9413   0.0385
  -5.750  -0.2177   0.01390   0.00772  -0.0928   0.9342   0.0389
  -5.500  -0.1896   0.01335   0.00710  -0.0927   0.9294   0.0394
  -5.000  -0.1375   0.01227   0.00591  -0.0917   0.9181   0.0405
  -4.750  -0.1110   0.01167   0.00529  -0.0913   0.9127   0.0418
  -4.500  -0.0847   0.01129   0.00489  -0.0909   0.9064   0.0430
  -4.250  -0.0586   0.01094   0.00450  -0.0903   0.8984   0.0441
  -4.000  -0.0319   0.01062   0.00412  -0.0898   0.8904   0.0454
  -3.750  -0.0055   0.01035   0.00380  -0.0892   0.8819   0.0467
  -3.500   0.0215   0.01003   0.00345  -0.0888   0.8749   0.0494
  -3.250   0.0480   0.00978   0.00320  -0.0884   0.8669   0.0534
  -3.000   0.0752   0.00949   0.00295  -0.0880   0.8598   0.0660
  -2.750   0.1010   0.00915   0.00279  -0.0875   0.8514   0.1050
  -2.500   0.1283   0.00897   0.00264  -0.0873   0.8441   0.1301
  -2.250   0.1546   0.00878   0.00253  -0.0869   0.8354   0.1525
  -2.000   0.1817   0.00861   0.00243  -0.0866   0.8279   0.1815
  -1.750   0.2081   0.00845   0.00236  -0.0862   0.8191   0.2136
  -1.500   0.2351   0.00833   0.00231  -0.0859   0.8110   0.2476
  -1.250   0.2619   0.00824   0.00228  -0.0855   0.8019   0.2761
  -1.000   0.2889   0.00818   0.00225  -0.0852   0.7931   0.3011
  -0.500   0.3427   0.00808   0.00221  -0.0845   0.7740   0.3442
  -0.250   0.3697   0.00805   0.00217  -0.0842   0.7646   0.3649
   0.000   0.3962   0.00799   0.00216  -0.0838   0.7535   0.3864
   0.500   0.4489   0.00787   0.00210  -0.0829   0.7316   0.4307
   0.750   0.4741   0.00771   0.00207  -0.0823   0.7191   0.4760
   1.000   0.4874   0.00660   0.00224  -0.0787   0.7072   0.8988
   1.250   0.5313   0.00673   0.00237  -0.0816   0.6931   0.9681
   1.500   0.5874   0.00688   0.00243  -0.0875   0.6767   0.9879
   1.750   0.6365   0.00700   0.00245  -0.0921   0.6589   0.9969
   2.000   0.6715   0.00711   0.00246  -0.0936   0.6398   1.0000
   2.250   0.6948   0.00725   0.00250  -0.0926   0.6209   1.0000
   2.500   0.7180   0.00739   0.00255  -0.0916   0.6014   1.0000
   2.750   0.7406   0.00754   0.00262  -0.0905   0.5803   1.0000
   3.000   0.7624   0.00774   0.00270  -0.0892   0.5579   1.0000
   3.250   0.7840   0.00794   0.00280  -0.0879   0.5353   1.0000
   3.500   0.8052   0.00817   0.00292  -0.0865   0.5123   1.0000
   3.750   0.8258   0.00842   0.00306  -0.0850   0.4903   1.0000
   4.000   0.8468   0.00866   0.00320  -0.0836   0.4695   1.0000
   4.250   0.8678   0.00890   0.00336  -0.0822   0.4513   1.0000
   4.500   0.8890   0.00914   0.00353  -0.0809   0.4349   1.0000
   4.750   0.9102   0.00938   0.00371  -0.0795   0.4196   1.0000
   5.000   0.9315   0.00962   0.00389  -0.0782   0.4061   1.0000
   5.250   0.9527   0.00987   0.00408  -0.0769   0.3928   1.0000
   5.750   0.9955   0.01037   0.00447  -0.0744   0.3631   1.0000
   6.000   1.0172   0.01062   0.00467  -0.0732   0.3477   1.0000
   6.250   1.0396   0.01086   0.00488  -0.0722   0.3345   1.0000
   6.500   1.0622   0.01110   0.00511  -0.0712   0.3232   1.0000
   6.750   1.0843   0.01137   0.00535  -0.0701   0.3112   1.0000
   7.000   1.1061   0.01167   0.00560  -0.0690   0.2981   1.0000
   7.250   1.1282   0.01195   0.00586  -0.0680   0.2844   1.0000
   7.500   1.1500   0.01226   0.00614  -0.0670   0.2694   1.0000
   8.000   1.1915   0.01301   0.00678  -0.0646   0.2321   1.0000
   8.250   1.2098   0.01354   0.00718  -0.0631   0.2069   1.0000
   8.500   1.2265   0.01419   0.00766  -0.0614   0.1739   1.0000
   8.750   1.2396   0.01506   0.00830  -0.0592   0.1373   1.0000
   9.000   1.2523   0.01586   0.00896  -0.0568   0.1129   1.0000
   9.250   1.2651   0.01664   0.00963  -0.0545   0.0932   1.0000
   9.500   1.2771   0.01749   0.01036  -0.0521   0.0740   1.0000
   9.750   1.2892   0.01834   0.01113  -0.0498   0.0616   1.0000
  10.000   1.3022   0.01913   0.01190  -0.0477   0.0547   1.0000
  10.250   1.3157   0.01989   0.01269  -0.0457   0.0502   1.0000
  10.500   1.3278   0.02075   0.01356  -0.0437   0.0466   1.0000
  10.750   1.3389   0.02168   0.01453  -0.0416   0.0437   1.0000
  11.000   1.3523   0.02248   0.01539  -0.0398   0.0413   1.0000
  11.250   1.3620   0.02354   0.01647  -0.0378   0.0391   1.0000
  11.500   1.3683   0.02487   0.01785  -0.0355   0.0372   1.0000
  11.750   1.3803   0.02583   0.01890  -0.0339   0.0357   1.0000
  12.000   1.3904   0.02696   0.02009  -0.0323   0.0342   1.0000
  12.250   1.3969   0.02839   0.02156  -0.0305   0.0327   1.0000
  12.500   1.3965   0.03042   0.02365  -0.0282   0.0314   1.0000
  12.750   1.4071   0.03164   0.02497  -0.0270   0.0304   1.0000
  13.000   1.4147   0.03316   0.02658  -0.0257   0.0293   1.0000
  13.250   1.4205   0.03486   0.02834  -0.0245   0.0283   1.0000
  13.500   1.4237   0.03685   0.03040  -0.0233   0.0275   1.0000
  13.750   1.4202   0.03955   0.03315  -0.0219   0.0267   1.0000
  14.000   1.4195   0.04206   0.03576  -0.0208   0.0260   1.0000
  14.250   1.4248   0.04410   0.03791  -0.0202   0.0253   1.0000
  14.500   1.4281   0.04640   0.04031  -0.0196   0.0246   1.0000
  14.750   1.4305   0.04885   0.04286  -0.0192   0.0239   1.0000
  15.000   1.4317   0.05153   0.04561  -0.0190   0.0234   1.0000
  15.250   1.4312   0.05449   0.04863  -0.0189   0.0228   1.0000
  15.500   1.4268   0.05792   0.05213  -0.0189   0.0223   1.0000
  15.750   1.4182   0.06181   0.05609  -0.0187   0.0218   1.0000
  16.000   1.4190   0.06490   0.05930  -0.0190   0.0215   1.0000
  16.250   1.4182   0.06822   0.06275  -0.0195   0.0211   1.0000
  16.500   1.4164   0.07172   0.06636  -0.0201   0.0207   1.0000
  16.750   1.4139   0.07535   0.07010  -0.0207   0.0204   1.0000
  17.000   1.4111   0.07910   0.07395  -0.0215   0.0200   1.0000
  17.250   1.4080   0.08293   0.07788  -0.0225   0.0196   1.0000
  17.500   1.4047   0.08684   0.08187  -0.0235   0.0193   1.0000
  17.750   1.4011   0.09080   0.08590  -0.0247   0.0190   1.0000
  18.000   1.3972   0.09482   0.08998  -0.0258   0.0187   1.0000
  18.250   1.3925   0.09879   0.09401  -0.0268   0.0183   1.0000
  18.500   1.3866   0.10281   0.09811  -0.0276   0.0180   1.0000
  18.750   1.3811   0.10741   0.10285  -0.0294   0.0178   1.0000
  19.000   1.3755   0.11204   0.10761  -0.0313   0.0175   1.0000
  19.250   1.3698   0.11669   0.11239  -0.0333   0.0173   1.0000
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