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Davis AIRFOIL (davis-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: Davis AIRFOIL (davis-il)
Reynolds number: 100,000
Max Cl/Cd: 54.99 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-davis-il-100000-n5.txt
Download as CSV file: xf-davis-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4008   0.08966   0.08494  -0.0466   1.0000   0.0266
  -9.250  -0.4107   0.08594   0.08130  -0.0466   1.0000   0.0264
  -9.000  -0.4258   0.08167   0.07712  -0.0466   1.0000   0.0265
  -8.750  -0.4402   0.07852   0.07407  -0.0458   1.0000   0.0262
  -8.500  -0.4619   0.07497   0.07063  -0.0448   1.0000   0.0261
  -8.250  -0.4865   0.07146   0.06726  -0.0439   1.0000   0.0259
  -8.000  -0.5050   0.06513   0.06094  -0.0469   0.9991   0.0255
  -7.750  -0.5025   0.05325   0.04862  -0.0597   0.9888   0.0251
  -7.500  -0.4941   0.04555   0.04027  -0.0657   0.9801   0.0254
  -7.250  -0.4793   0.04011   0.03413  -0.0684   0.9727   0.0258
  -7.000  -0.4573   0.03608   0.02937  -0.0702   0.9674   0.0264
  -6.750  -0.4372   0.03276   0.02553  -0.0707   0.9609   0.0274
  -6.500  -0.4106   0.03075   0.02335  -0.0720   0.9560   0.0298
  -6.250  -0.3839   0.02896   0.02123  -0.0726   0.9497   0.0324
  -6.000  -0.3540   0.02702   0.01890  -0.0734   0.9448   0.0344
  -5.500  -0.2948   0.02401   0.01549  -0.0749   0.9332   0.0418
  -5.250  -0.2669   0.02288   0.01414  -0.0750   0.9256   0.0455
  -5.000  -0.2326   0.02175   0.01290  -0.0766   0.9212   0.0524
  -4.750  -0.2072   0.02098   0.01198  -0.0761   0.9125   0.0591
  -4.500  -0.1727   0.02011   0.01107  -0.0776   0.9087   0.0720
  -4.250  -0.1495   0.01942   0.01042  -0.0768   0.9005   0.0883
  -4.000  -0.1171   0.01877   0.00989  -0.0779   0.8960   0.1321
  -3.750  -0.0867   0.01836   0.00949  -0.0785   0.8906   0.1668
  -3.500  -0.0593   0.01809   0.00919  -0.0785   0.8836   0.1922
  -3.250  -0.0244   0.01779   0.00887  -0.0799   0.8797   0.2237
  -3.000   0.0004   0.01760   0.00869  -0.0794   0.8718   0.2541
  -2.750   0.0320   0.01725   0.00839  -0.0801   0.8666   0.2862
  -2.500   0.0612   0.01695   0.00810  -0.0804   0.8605   0.3133
  -2.250   0.0890   0.01668   0.00788  -0.0803   0.8534   0.3428
  -2.000   0.1232   0.01633   0.00759  -0.0814   0.8494   0.3814
  -1.750   0.1467   0.01616   0.00748  -0.0806   0.8405   0.4195
  -1.500   0.1804   0.01578   0.00720  -0.0816   0.8354   0.4706
  -1.250   0.2058   0.01548   0.00705  -0.0810   0.8264   0.5266
  -1.000   0.2370   0.01486   0.00680  -0.0811   0.8201   0.6271
  -0.750   0.2901   0.01427   0.00683  -0.0850   0.8129   0.8779
  -0.500   0.3701   0.01401   0.00644  -0.0954   0.8068   0.9907
  -0.250   0.4028   0.01398   0.00627  -0.0964   0.7964   1.0000
   0.000   0.4322   0.01391   0.00605  -0.0965   0.7865   1.0000
   0.250   0.4608   0.01387   0.00587  -0.0964   0.7760   1.0000
   0.500   0.4863   0.01388   0.00578  -0.0958   0.7640   1.0000
   0.750   0.5128   0.01389   0.00567  -0.0954   0.7515   1.0000
   1.000   0.5395   0.01393   0.00560  -0.0949   0.7395   1.0000
   1.250   0.5667   0.01397   0.00555  -0.0947   0.7283   1.0000
   1.500   0.5923   0.01406   0.00556  -0.0940   0.7165   1.0000
   1.750   0.6156   0.01419   0.00563  -0.0931   0.7039   1.0000
   2.000   0.6391   0.01431   0.00571  -0.0921   0.6909   1.0000
   2.250   0.6625   0.01444   0.00580  -0.0911   0.6776   1.0000
   2.500   0.6854   0.01458   0.00590  -0.0900   0.6637   1.0000
   2.750   0.7079   0.01471   0.00602  -0.0889   0.6490   1.0000
   3.000   0.7303   0.01486   0.00614  -0.0877   0.6340   1.0000
   3.250   0.7525   0.01500   0.00627  -0.0865   0.6185   1.0000
   3.500   0.7750   0.01516   0.00639  -0.0853   0.6024   1.0000
   3.750   0.7978   0.01532   0.00653  -0.0842   0.5862   1.0000
   4.000   0.8207   0.01551   0.00667  -0.0831   0.5698   1.0000
   4.250   0.8434   0.01573   0.00683  -0.0820   0.5534   1.0000
   4.500   0.8660   0.01600   0.00707  -0.0809   0.5374   1.0000
   4.750   0.8883   0.01630   0.00733  -0.0798   0.5215   1.0000
   5.000   0.9101   0.01663   0.00765  -0.0786   0.5053   1.0000
   5.250   0.9311   0.01697   0.00802  -0.0774   0.4886   1.0000
   5.500   0.9518   0.01732   0.00841  -0.0760   0.4716   1.0000
   5.750   0.9722   0.01768   0.00881  -0.0747   0.4552   1.0000
   6.000   0.9929   0.01806   0.00922  -0.0734   0.4398   1.0000
   6.250   1.0137   0.01845   0.00965  -0.0721   0.4260   1.0000
   6.500   1.0345   0.01886   0.01013  -0.0709   0.4134   1.0000
   6.750   1.0554   0.01928   0.01060  -0.0697   0.4020   1.0000
   7.000   1.0757   0.01973   0.01112  -0.0684   0.3901   1.0000
   7.250   1.0925   0.02021   0.01158  -0.0665   0.3738   1.0000
   7.500   1.1051   0.02076   0.01207  -0.0639   0.3512   1.0000
   8.000   1.1298   0.02201   0.01327  -0.0589   0.3116   1.0000
   8.250   1.1387   0.02260   0.01392  -0.0558   0.2874   1.0000
   8.500   1.1441   0.02327   0.01458  -0.0522   0.2562   1.0000
   8.750   1.1472   0.02418   0.01534  -0.0486   0.2120   1.0000
   9.000   1.1366   0.02615   0.01662  -0.0437   0.1162   1.0000
   9.250   1.1289   0.02851   0.01854  -0.0395   0.0652   1.0000
   9.500   1.1284   0.03041   0.02031  -0.0364   0.0430   1.0000
   9.750   1.1303   0.03213   0.02206  -0.0336   0.0357   1.0000
  10.000   1.1317   0.03390   0.02390  -0.0310   0.0315   1.0000
  10.250   1.1322   0.03577   0.02588  -0.0287   0.0287   1.0000
  10.500   1.1332   0.03766   0.02794  -0.0266   0.0269   1.0000
  10.750   1.1317   0.03984   0.03033  -0.0246   0.0253   1.0000
  11.000   1.1289   0.04226   0.03290  -0.0229   0.0243   1.0000
  11.250   1.1251   0.04489   0.03568  -0.0215   0.0237   1.0000
  11.500   1.1185   0.04794   0.03885  -0.0203   0.0230   1.0000
  11.750   1.1121   0.05109   0.04210  -0.0193   0.0225   1.0000
  12.000   1.1114   0.05380   0.04498  -0.0185   0.0219   1.0000
  12.250   1.1118   0.05648   0.04780  -0.0179   0.0212   1.0000
  12.500   1.1128   0.05915   0.05063  -0.0173   0.0203   1.0000
  12.750   1.1149   0.06178   0.05338  -0.0167   0.0194   1.0000
  13.000   1.1191   0.06424   0.05595  -0.0161   0.0189   1.0000
  13.250   1.1247   0.06662   0.05844  -0.0153   0.0183   1.0000
  13.500   1.1313   0.06900   0.06095  -0.0146   0.0178   1.0000
  13.750   1.1374   0.07156   0.06364  -0.0140   0.0174   1.0000
  14.000   1.1427   0.07433   0.06657  -0.0135   0.0170   1.0000
  14.250   1.1454   0.07747   0.06986  -0.0134   0.0166   1.0000
  14.500   1.1459   0.08092   0.07352  -0.0136   0.0162   1.0000
  14.750   1.1443   0.08477   0.07754  -0.0140   0.0158   1.0000
  15.000   1.1409   0.08897   0.08193  -0.0147   0.0156   1.0000
  15.250   1.1319   0.09427   0.08744  -0.0158   0.0152   1.0000
  15.500   1.1219   0.09958   0.09293  -0.0177   0.0150   1.0000
  15.750   1.1103   0.10519   0.09878  -0.0202   0.0150   1.0000
  16.000   1.0990   0.11105   0.10485  -0.0230   0.0149   1.0000
  16.250   1.0863   0.11737   0.11139  -0.0263   0.0149   1.0000
  16.500   1.0728   0.12418   0.11839  -0.0301   0.0149   1.0000
  16.750   1.0590   0.13139   0.12579  -0.0344   0.0150   1.0000
  17.000   1.0445   0.13911   0.13368  -0.0392   0.0150   1.0000
  17.250   1.0306   0.14708   0.14179  -0.0441   0.0150   1.0000
  17.500   1.0170   0.15553   0.15042  -0.0496   0.0152   1.0000
  17.750   0.9957   0.16770   0.16274  -0.0576   0.0158   1.0000
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