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Davis AIRFOIL (davis-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: Davis AIRFOIL (davis-il)
Reynolds number: 200,000
Max Cl/Cd: 72.09 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-davis-il-200000-n5.txt
Download as CSV file: xf-davis-il-200000-n5.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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4223   0.08519   0.08191  -0.0432   1.0000   0.0148
  -9.250  -0.4443   0.08006   0.07689  -0.0433   1.0000   0.0145
  -9.000  -0.5393   0.04368   0.03981  -0.0777   0.9814   0.0129
  -8.750  -0.5338   0.03811   0.03374  -0.0812   0.9743   0.0130
  -8.500  -0.5188   0.03423   0.02945  -0.0833   0.9691   0.0134
  -8.250  -0.5017   0.03165   0.02656  -0.0838   0.9632   0.0138
  -8.000  -0.4776   0.02930   0.02387  -0.0851   0.9591   0.0143
  -7.750  -0.4561   0.02725   0.02149  -0.0853   0.9533   0.0149
  -7.500  -0.4293   0.02534   0.01925  -0.0862   0.9490   0.0157
  -7.250  -0.4002   0.02392   0.01752  -0.0871   0.9452   0.0173
  -7.000  -0.3751   0.02271   0.01598  -0.0869   0.9391   0.0183
  -6.750  -0.3457   0.02080   0.01389  -0.0880   0.9359   0.0196
  -6.500  -0.3209   0.01982   0.01281  -0.0877   0.9298   0.0210
  -6.250  -0.2906   0.01897   0.01183  -0.0885   0.9252   0.0235
  -6.000  -0.2570   0.01814   0.01082  -0.0898   0.9222   0.0261
  -5.750  -0.2356   0.01713   0.00971  -0.0887   0.9140   0.0282
  -5.500  -0.2049   0.01631   0.00879  -0.0895   0.9097   0.0321
  -5.250  -0.1788   0.01575   0.00811  -0.0892   0.9024   0.0358
  -5.000  -0.1497   0.01501   0.00727  -0.0895   0.8963   0.0403
  -4.750  -0.1212   0.01448   0.00666  -0.0897   0.8896   0.0466
  -4.500  -0.0934   0.01394   0.00609  -0.0897   0.8822   0.0552
  -4.250  -0.0637   0.01338   0.00559  -0.0902   0.8763   0.0775
  -4.000  -0.0373   0.01295   0.00528  -0.0900   0.8680   0.1164
  -3.750  -0.0065   0.01264   0.00499  -0.0906   0.8619   0.1467
  -3.500   0.0206   0.01239   0.00474  -0.0905   0.8535   0.1668
  -3.250   0.0507   0.01214   0.00449  -0.0909   0.8468   0.1877
  -3.000   0.0785   0.01195   0.00429  -0.0909   0.8380   0.2057
  -2.750   0.1072   0.01175   0.00409  -0.0910   0.8292   0.2306
  -2.500   0.1368   0.01154   0.00387  -0.0913   0.8199   0.2550
  -2.250   0.1638   0.01134   0.00370  -0.0911   0.8087   0.2825
  -2.000   0.1914   0.01112   0.00354  -0.0910   0.7987   0.3148
  -1.500   0.2460   0.01080   0.00331  -0.0907   0.7799   0.3850
  -1.250   0.2729   0.01066   0.00321  -0.0904   0.7702   0.4226
  -0.750   0.3247   0.01038   0.00305  -0.0895   0.7501   0.5073
  -0.500   0.3487   0.01016   0.00301  -0.0886   0.7406   0.5680
  -0.250   0.3702   0.00977   0.00305  -0.0870   0.7313   0.6965
   0.000   0.4087   0.00953   0.00317  -0.0886   0.7209   0.8641
   0.250   0.4685   0.00957   0.00318  -0.0951   0.7094   0.9451
   0.500   0.5174   0.00965   0.00316  -0.0996   0.6967   0.9800
   0.750   0.5619   0.00974   0.00316  -0.1032   0.6833   1.0000
   1.000   0.5838   0.00984   0.00318  -0.1020   0.6704   1.0000
   1.250   0.6055   0.00993   0.00320  -0.1007   0.6568   1.0000
   1.500   0.6271   0.01003   0.00324  -0.0995   0.6421   1.0000
   1.750   0.6488   0.01013   0.00328  -0.0982   0.6268   1.0000
   2.000   0.6704   0.01025   0.00333  -0.0968   0.6104   1.0000
   2.250   0.6917   0.01039   0.00338  -0.0955   0.5934   1.0000
   2.500   0.7128   0.01055   0.00345  -0.0941   0.5766   1.0000
   2.750   0.7339   0.01073   0.00355  -0.0927   0.5610   1.0000
   3.000   0.7551   0.01093   0.00367  -0.0913   0.5469   1.0000
   3.250   0.7764   0.01114   0.00381  -0.0900   0.5333   1.0000
   3.500   0.7977   0.01137   0.00399  -0.0887   0.5199   1.0000
   4.000   0.8402   0.01184   0.00437  -0.0861   0.4914   1.0000
   4.250   0.8614   0.01208   0.00459  -0.0848   0.4758   1.0000
   4.500   0.8825   0.01231   0.00481  -0.0835   0.4593   1.0000
   4.750   0.9033   0.01255   0.00504  -0.0822   0.4410   1.0000
   5.000   0.9235   0.01281   0.00528  -0.0807   0.4216   1.0000
   5.250   0.9429   0.01312   0.00556  -0.0791   0.4028   1.0000
   5.500   0.9620   0.01345   0.00584  -0.0775   0.3867   1.0000
   5.750   0.9812   0.01380   0.00616  -0.0760   0.3730   1.0000
   6.000   1.0004   0.01417   0.00651  -0.0744   0.3604   1.0000
   6.250   1.0180   0.01460   0.00691  -0.0726   0.3453   1.0000
   6.500   1.0345   0.01509   0.00731  -0.0707   0.3283   1.0000
   6.750   1.0506   0.01557   0.00773  -0.0687   0.3098   1.0000
   7.000   1.0679   0.01599   0.00815  -0.0669   0.2929   1.0000
   7.250   1.0856   0.01638   0.00856  -0.0652   0.2775   1.0000
   7.500   1.1017   0.01677   0.00896  -0.0632   0.2585   1.0000
   7.750   1.1133   0.01732   0.00943  -0.0604   0.2274   1.0000
   8.000   1.1198   0.01819   0.01004  -0.0571   0.1772   1.0000
   8.250   1.1083   0.02034   0.01146  -0.0514   0.0782   1.0000
   8.500   1.1099   0.02181   0.01268  -0.0478   0.0359   1.0000
   8.750   1.1164   0.02296   0.01376  -0.0448   0.0240   1.0000
   9.000   1.1263   0.02391   0.01479  -0.0424   0.0209   1.0000
   9.250   1.1360   0.02488   0.01588  -0.0401   0.0192   1.0000
   9.500   1.1436   0.02601   0.01712  -0.0376   0.0176   1.0000
   9.750   1.1488   0.02732   0.01854  -0.0351   0.0164   1.0000
  10.000   1.1490   0.02902   0.02039  -0.0322   0.0152   1.0000
  10.500   1.1595   0.03190   0.02356  -0.0281   0.0140   1.0000
  10.750   1.1616   0.03370   0.02549  -0.0261   0.0133   1.0000
  11.000   1.1630   0.03565   0.02756  -0.0242   0.0130   1.0000
  11.250   1.1645   0.03769   0.02972  -0.0226   0.0127   1.0000
  11.500   1.1648   0.03994   0.03208  -0.0212   0.0123   1.0000
  11.750   1.1662   0.04217   0.03441  -0.0200   0.0119   1.0000
  12.000   1.1666   0.04458   0.03692  -0.0189   0.0116   1.0000
  12.250   1.1676   0.04701   0.03944  -0.0180   0.0113   1.0000
  12.500   1.1659   0.04977   0.04226  -0.0173   0.0107   1.0000
  12.750   1.1644   0.05264   0.04521  -0.0163   0.0104   1.0000
  13.000   1.1661   0.05524   0.04790  -0.0156   0.0100   1.0000
  13.250   1.1701   0.05768   0.05048  -0.0151   0.0098   1.0000
  13.500   1.1738   0.06021   0.05315  -0.0146   0.0096   1.0000
  13.750   1.1771   0.06285   0.05597  -0.0142   0.0094   1.0000
  14.000   1.1799   0.06563   0.05890  -0.0139   0.0092   1.0000
  14.250   1.1818   0.06860   0.06203  -0.0137   0.0090   1.0000
  14.500   1.1825   0.07179   0.06539  -0.0137   0.0088   1.0000
  14.750   1.1818   0.07526   0.06903  -0.0139   0.0087   1.0000
  15.000   1.1798   0.07897   0.07292  -0.0144   0.0087   1.0000
  15.250   1.1754   0.08313   0.07727  -0.0153   0.0085   1.0000
  15.500   1.1701   0.08753   0.08186  -0.0164   0.0084   1.0000
  15.750   1.1635   0.09220   0.08670  -0.0180   0.0083   1.0000
  16.000   1.1558   0.09719   0.09188  -0.0198   0.0082   1.0000
  16.250   1.1468   0.10259   0.09747  -0.0220   0.0082   1.0000
  16.500   1.1371   0.10827   0.10333  -0.0247   0.0081   1.0000
  16.750   1.1298   0.11358   0.10877  -0.0274   0.0079   1.0000
  17.000   1.1169   0.12030   0.11569  -0.0308   0.0079   1.0000
  17.250   1.1003   0.12818   0.12380  -0.0352   0.0080   1.0000
  17.500   1.0960   0.13329   0.12899  -0.0382   0.0078   1.0000
  17.750   1.0747   0.14298   0.13893  -0.0440   0.0080   1.0000
  18.000   1.0570   0.15219   0.14832  -0.0497   0.0080   1.0000
  18.250   1.0334   0.16374   0.16007  -0.0569   0.0083   1.0000
  18.500   1.0089   0.17676   0.17323  -0.0648   0.0084   1.0000
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