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Davis AIRFOIL (davis-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: Davis AIRFOIL (davis-il)
Reynolds number: 500,000
Max Cl/Cd: 101.36 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-davis-il-500000.txt
Download as CSV file: xf-davis-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Davis 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4145   0.09039   0.08830  -0.0382   1.0000   0.0240
  -9.250  -0.5142   0.06096   0.05895  -0.0557   0.9959   0.0162
  -9.000  -0.5364   0.04072   0.03803  -0.0816   0.9845   0.0154
  -8.750  -0.5343   0.03429   0.03105  -0.0845   0.9770   0.0155
  -8.500  -0.5170   0.02952   0.02572  -0.0868   0.9729   0.0157
  -8.250  -0.4894   0.02656   0.02227  -0.0889   0.9709   0.0165
  -8.000  -0.4722   0.02457   0.01993  -0.0878   0.9642   0.0167
  -7.750  -0.4487   0.02121   0.01614  -0.0886   0.9608   0.0174
  -7.500  -0.4169   0.01961   0.01442  -0.0902   0.9590   0.0181
  -7.250  -0.3825   0.01853   0.01321  -0.0921   0.9577   0.0190
  -7.000  -0.3533   0.01759   0.01215  -0.0926   0.9544   0.0200
  -6.750  -0.3249   0.01691   0.01135  -0.0928   0.9496   0.0213
  -6.500  -0.2921   0.01563   0.00989  -0.0941   0.9471   0.0228
  -6.250  -0.2593   0.01449   0.00871  -0.0955   0.9448   0.0244
  -6.000  -0.2238   0.01375   0.00791  -0.0972   0.9428   0.0263
  -5.750  -0.2006   0.01327   0.00736  -0.0961   0.9352   0.0280
  -5.500  -0.1704   0.01235   0.00634  -0.0967   0.9309   0.0304
  -5.250  -0.1417   0.01164   0.00559  -0.0970   0.9257   0.0332
  -5.000  -0.1155   0.01118   0.00506  -0.0965   0.9181   0.0360
  -4.750  -0.0842   0.01063   0.00443  -0.0972   0.9134   0.0397
  -4.500  -0.0609   0.01020   0.00397  -0.0962   0.9035   0.0446
  -4.250  -0.0327   0.00981   0.00353  -0.0961   0.8955   0.0519
  -4.000  -0.0069   0.00922   0.00313  -0.0957   0.8858   0.0940
  -3.750   0.0182   0.00888   0.00294  -0.0951   0.8748   0.1445
  -3.500   0.0454   0.00869   0.00275  -0.0950   0.8647   0.1671
  -3.250   0.0732   0.00850   0.00257  -0.0949   0.8549   0.1874
  -3.000   0.0993   0.00835   0.00246  -0.0945   0.8433   0.2110
  -2.750   0.1257   0.00822   0.00234  -0.0941   0.8323   0.2355
  -2.500   0.1524   0.00811   0.00222  -0.0938   0.8219   0.2590
  -2.250   0.1789   0.00799   0.00211  -0.0935   0.8116   0.2818
  -2.000   0.2044   0.00786   0.00202  -0.0930   0.8005   0.3090
  -1.750   0.2298   0.00772   0.00197  -0.0924   0.7900   0.3499
  -1.500   0.2551   0.00759   0.00193  -0.0919   0.7802   0.4003
  -1.250   0.2801   0.00747   0.00190  -0.0913   0.7703   0.4497
  -1.000   0.3048   0.00734   0.00188  -0.0906   0.7608   0.4965
  -0.750   0.3289   0.00718   0.00185  -0.0898   0.7518   0.5537
  -0.500   0.3483   0.00681   0.00186  -0.0880   0.7415   0.6747
  -0.250   0.3670   0.00644   0.00196  -0.0856   0.7312   0.8375
   0.000   0.4134   0.00643   0.00206  -0.0892   0.7204   0.9297
   0.250   0.4620   0.00655   0.00210  -0.0935   0.7088   0.9586
   0.500   0.5029   0.00665   0.00214  -0.0963   0.6974   0.9736
   0.750   0.5447   0.00675   0.00218  -0.0993   0.6862   0.9856
   1.000   0.5901   0.00684   0.00221  -0.1031   0.6744   0.9948
   1.250   0.6314   0.00690   0.00221  -0.1061   0.6609   1.0000
   1.500   0.6523   0.00696   0.00221  -0.1047   0.6462   1.0000
   1.750   0.6732   0.00703   0.00223  -0.1033   0.6298   1.0000
   2.000   0.6937   0.00713   0.00225  -0.1017   0.6119   1.0000
   2.250   0.7140   0.00725   0.00229  -0.1001   0.5938   1.0000
   2.750   0.7545   0.00758   0.00244  -0.0970   0.5613   1.0000
   3.000   0.7752   0.00776   0.00255  -0.0955   0.5469   1.0000
   3.250   0.7962   0.00794   0.00267  -0.0941   0.5331   1.0000
   3.500   0.8173   0.00813   0.00281  -0.0928   0.5192   1.0000
   3.750   0.8385   0.00831   0.00295  -0.0914   0.5049   1.0000
   4.000   0.8595   0.00850   0.00310  -0.0900   0.4895   1.0000
   4.250   0.8802   0.00870   0.00325  -0.0886   0.4726   1.0000
   4.500   0.9011   0.00889   0.00341  -0.0872   0.4514   1.0000
   4.750   0.9201   0.00914   0.00357  -0.0854   0.4239   1.0000
   5.000   0.9369   0.00950   0.00377  -0.0832   0.3897   1.0000
   5.250   0.9536   0.00991   0.00402  -0.0811   0.3633   1.0000
   5.500   0.9721   0.01027   0.00430  -0.0794   0.3460   1.0000
   5.750   0.9916   0.01059   0.00457  -0.0778   0.3325   1.0000
   6.000   1.0114   0.01089   0.00484  -0.0763   0.3197   1.0000
   6.250   1.0313   0.01119   0.00511  -0.0749   0.3076   1.0000
   6.500   1.0511   0.01149   0.00539  -0.0734   0.2960   1.0000
   6.750   1.0715   0.01176   0.00564  -0.0721   0.2830   1.0000
   7.000   1.0916   0.01203   0.00589  -0.0707   0.2651   1.0000
   7.250   1.1091   0.01242   0.00617  -0.0689   0.2368   1.0000
   7.500   1.1195   0.01316   0.00663  -0.0659   0.1856   1.0000
   7.750   1.1079   0.01501   0.00779  -0.0593   0.0775   1.0000
   8.000   1.1085   0.01634   0.00880  -0.0547   0.0298   1.0000
   8.250   1.1214   0.01699   0.00947  -0.0522   0.0241   1.0000
   8.500   1.1320   0.01780   0.01032  -0.0494   0.0207   1.0000
   8.750   1.1461   0.01840   0.01099  -0.0473   0.0198   1.0000
   9.000   1.1584   0.01912   0.01178  -0.0449   0.0186   1.0000
   9.250   1.1686   0.01996   0.01269  -0.0423   0.0176   1.0000
   9.500   1.1766   0.02093   0.01374  -0.0396   0.0168   1.0000
   9.750   1.1787   0.02227   0.01518  -0.0362   0.0160   1.0000
  10.000   1.1802   0.02371   0.01672  -0.0329   0.0155   1.0000
  10.250   1.1882   0.02480   0.01789  -0.0306   0.0151   1.0000
  10.500   1.1978   0.02582   0.01898  -0.0287   0.0143   1.0000
  10.750   1.2028   0.02721   0.02046  -0.0265   0.0141   1.0000
  11.000   1.2068   0.02875   0.02208  -0.0243   0.0137   1.0000
  11.250   1.2109   0.03036   0.02378  -0.0223   0.0133   1.0000
  11.500   1.2143   0.03211   0.02561  -0.0205   0.0130   1.0000
  11.750   1.2175   0.03395   0.02752  -0.0188   0.0127   1.0000
  12.000   1.2199   0.03596   0.02959  -0.0172   0.0125   1.0000
  12.250   1.2225   0.03802   0.03172  -0.0158   0.0122   1.0000
  12.500   1.2250   0.04022   0.03398  -0.0142   0.0120   1.0000
  12.750   1.2314   0.04276   0.03657  -0.0121   0.0116   1.0000
  13.000   1.2383   0.04460   0.03853  -0.0110   0.0115   1.0000
  13.250   1.2408   0.04655   0.04064  -0.0104   0.0112   1.0000
  13.500   1.2467   0.04867   0.04288  -0.0094   0.0110   1.0000
  13.750   1.2506   0.05089   0.04524  -0.0087   0.0108   1.0000
  14.000   1.2537   0.05334   0.04783  -0.0080   0.0106   1.0000
  14.250   1.2549   0.05595   0.05058  -0.0075   0.0103   1.0000
  14.500   1.2558   0.05891   0.05371  -0.0068   0.0103   1.0000
  14.750   1.2547   0.06201   0.05696  -0.0066   0.0102   1.0000
  15.000   1.2515   0.06546   0.06057  -0.0065   0.0101   1.0000
  15.250   1.2463   0.06924   0.06453  -0.0067   0.0100   1.0000
  15.500   1.2400   0.07327   0.06872  -0.0073   0.0099   1.0000
  15.750   1.2297   0.07809   0.07375  -0.0082   0.0099   1.0000
  16.000   1.2197   0.08293   0.07876  -0.0096   0.0098   1.0000
  16.250   1.2044   0.08893   0.08498  -0.0114   0.0100   1.0000
  16.500   1.1885   0.09521   0.09146  -0.0138   0.0101   1.0000
  16.750   1.1712   0.10198   0.09842  -0.0168   0.0102   1.0000
  17.000   1.1533   0.10918   0.10581  -0.0203   0.0103   1.0000
  17.250   1.1364   0.11649   0.11328  -0.0242   0.0105   1.0000
  17.500   1.1151   0.12501   0.12197  -0.0289   0.0108   1.0000
  17.750   1.0972   0.13322   0.13034  -0.0338   0.0109   1.0000
  18.000   1.0770   0.14249   0.13976  -0.0396   0.0109   1.0000
  18.250   1.0576   0.15194   0.14934  -0.0455   0.0110   1.0000
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