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DRAGONFLY CANARD (drgnfly-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: DRAGONFLY CANARD (drgnfly-il)
Reynolds number: 500,000
Max Cl/Cd: 104.74 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-drgnfly-il-500000-n5.txt
Download as CSV file: xf-drgnfly-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: DRAGONFLY CANARD                                
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500   0.0070   0.08840   0.08377  -0.1160   0.5865   0.0169
 -11.250   0.0063   0.08479   0.08016  -0.1174   0.5857   0.0171
 -11.000  -0.0020   0.07993   0.07532  -0.1193   0.5849   0.0171
 -10.750  -0.0064   0.07597   0.07136  -0.1210   0.5841   0.0174
 -10.500  -0.2390   0.03908   0.03425  -0.1375   0.5856   0.0176
 -10.250  -0.2763   0.03559   0.03052  -0.1322   0.5847   0.0177
 -10.000  -0.3005   0.03299   0.02765  -0.1268   0.5838   0.0179
  -9.750  -0.3090   0.03057   0.02495  -0.1232   0.5830   0.0181
  -9.500  -0.3107   0.02833   0.02242  -0.1200   0.5820   0.0184
  -9.250  -0.3060   0.02641   0.02022  -0.1174   0.5811   0.0188
  -9.000  -0.2958   0.02485   0.01840  -0.1153   0.5800   0.0190
  -8.750  -0.2821   0.02356   0.01687  -0.1136   0.5788   0.0193
  -8.500  -0.2652   0.02258   0.01566  -0.1122   0.5776   0.0195
  -8.250  -0.2473   0.02157   0.01451  -0.1109   0.5765   0.0198
  -8.000  -0.2271   0.02083   0.01370  -0.1100   0.5752   0.0200
  -7.750  -0.2056   0.02030   0.01309  -0.1093   0.5740   0.0203
  -7.500  -0.1832   0.01987   0.01261  -0.1086   0.5727   0.0206
  -7.250  -0.1606   0.01941   0.01206  -0.1080   0.5715   0.0210
  -7.000  -0.1379   0.01890   0.01144  -0.1073   0.5703   0.0213
  -6.750  -0.1149   0.01839   0.01082  -0.1067   0.5691   0.0217
  -6.500  -0.0916   0.01787   0.01020  -0.1061   0.5681   0.0221
  -6.250  -0.0679   0.01736   0.00962  -0.1055   0.5672   0.0225
  -6.000  -0.0439   0.01689   0.00908  -0.1050   0.5661   0.0229
  -5.750  -0.0197   0.01648   0.00859  -0.1045   0.5650   0.0232
  -5.500   0.0049   0.01613   0.00818  -0.1040   0.5639   0.0236
  -5.250   0.0283   0.01563   0.00765  -0.1034   0.5628   0.0240
  -5.000   0.0520   0.01524   0.00724  -0.1028   0.5616   0.0244
  -4.750   0.0765   0.01495   0.00694  -0.1024   0.5605   0.0249
  -4.500   0.1012   0.01470   0.00667  -0.1020   0.5594   0.0256
  -4.250   0.1259   0.01445   0.00639  -0.1015   0.5582   0.0263
  -4.000   0.1506   0.01421   0.00610  -0.1011   0.5571   0.0269
  -3.750   0.1752   0.01397   0.00582  -0.1006   0.5559   0.0275
  -3.500   0.2002   0.01378   0.00558  -0.1002   0.5548   0.0280
  -3.250   0.2249   0.01358   0.00533  -0.0997   0.5538   0.0285
  -3.000   0.2490   0.01333   0.00508  -0.0992   0.5528   0.0293
  -2.750   0.2740   0.01315   0.00491  -0.0988   0.5519   0.0302
  -2.500   0.2994   0.01302   0.00479  -0.0985   0.5509   0.0315
  -2.250   0.3249   0.01290   0.00466  -0.0982   0.5498   0.0327
  -2.000   0.3506   0.01280   0.00454  -0.0980   0.5487   0.0336
  -1.750   0.3758   0.01266   0.00440  -0.0976   0.5476   0.0352
  -1.500   0.4014   0.01256   0.00430  -0.0974   0.5466   0.0372
  -1.250   0.4272   0.01248   0.00421  -0.0971   0.5454   0.0397
  -1.000   0.4528   0.01239   0.00414  -0.0969   0.5443   0.0453
  -0.750   0.4775   0.01222   0.00407  -0.0965   0.5431   0.0700
  -0.500   0.5012   0.01199   0.00400  -0.0960   0.5420   0.1275
  -0.250   0.5242   0.01171   0.00396  -0.0954   0.5410   0.2111
   0.000   0.5444   0.01126   0.00393  -0.0943   0.5401   0.3525
   0.250   0.5638   0.01088   0.00396  -0.0930   0.5391   0.4970
   0.500   0.5843   0.01067   0.00403  -0.0918   0.5382   0.5873
   0.750   0.6032   0.01046   0.00412  -0.0901   0.5373   0.6725
   1.000   0.6193   0.01011   0.00424  -0.0877   0.5363   0.8000
   1.500   0.7677   0.01030   0.00469  -0.1078   0.5338   0.9430
   2.000   0.8315   0.01055   0.00489  -0.1101   0.5314   0.9618
   2.250   0.8615   0.01067   0.00499  -0.1109   0.5303   0.9698
   2.500   0.8970   0.01079   0.00507  -0.1129   0.5293   0.9745
   2.750   0.9281   0.01091   0.00517  -0.1139   0.5282   0.9804
   3.000   0.9633   0.01101   0.00524  -0.1159   0.5271   0.9839
   3.250   0.9990   0.01110   0.00530  -0.1180   0.5260   0.9871
   3.500   1.0333   0.01122   0.00538  -0.1198   0.5249   0.9906
   3.750   1.0668   0.01136   0.00550  -0.1214   0.5239   0.9935
   4.000   1.1019   0.01147   0.00563  -0.1235   0.5228   0.9962
   4.250   1.1368   0.01158   0.00577  -0.1256   0.5216   0.9988
   4.500   1.1665   0.01170   0.00592  -0.1265   0.5203   1.0000
   4.750   1.1871   0.01183   0.00607  -0.1255   0.5189   1.0000
   5.000   1.2077   0.01196   0.00621  -0.1245   0.5176   1.0000
   5.250   1.2284   0.01209   0.00636  -0.1235   0.5163   1.0000
   5.500   1.2490   0.01221   0.00650  -0.1225   0.5150   1.0000
   5.750   1.2696   0.01234   0.00664  -0.1215   0.5137   1.0000
   6.000   1.2905   0.01246   0.00678  -0.1205   0.5126   1.0000
   6.250   1.3116   0.01259   0.00691  -0.1196   0.5114   1.0000
   6.500   1.3333   0.01273   0.00704  -0.1188   0.5101   1.0000
   6.750   1.3523   0.01292   0.00726  -0.1176   0.5089   1.0000
   7.000   1.3691   0.01312   0.00753  -0.1159   0.5075   1.0000
   7.250   1.3855   0.01332   0.00779  -0.1142   0.5059   1.0000
   7.500   1.4018   0.01353   0.00805  -0.1124   0.5043   1.0000
   7.750   1.4177   0.01373   0.00829  -0.1106   0.5026   1.0000
   8.000   1.4334   0.01393   0.00854  -0.1088   0.5011   1.0000
   8.250   1.4457   0.01411   0.00875  -0.1062   0.4995   1.0000
   8.500   1.4594   0.01427   0.00893  -0.1040   0.4980   1.0000
   8.750   1.4758   0.01444   0.00912  -0.1023   0.4966   1.0000
   9.000   1.4934   0.01464   0.00934  -0.1009   0.4951   1.0000
   9.250   1.4980   0.01505   0.00985  -0.0973   0.4932   1.0000
   9.500   1.5052   0.01549   0.01038  -0.0944   0.4910   1.0000
   9.750   1.5140   0.01597   0.01092  -0.0920   0.4887   1.0000
  10.000   1.5244   0.01646   0.01148  -0.0899   0.4865   1.0000
  10.250   1.5375   0.01692   0.01198  -0.0883   0.4843   1.0000
  10.500   1.5543   0.01729   0.01237  -0.0874   0.4824   1.0000
  10.750   1.5677   0.01783   0.01297  -0.0860   0.4803   1.0000
  11.000   1.5641   0.01924   0.01451  -0.0830   0.4769   1.0000
  11.250   1.5645   0.02066   0.01602  -0.0808   0.4731   1.0000
  11.500   1.5736   0.02164   0.01705  -0.0795   0.4698   1.0000
  11.750   1.5806   0.02279   0.01822  -0.0781   0.4651   1.0000
  12.000   1.5632   0.02575   0.02131  -0.0750   0.4586   1.0000
  12.250   1.5655   0.02729   0.02284  -0.0735   0.4510   1.0000
  12.500   1.5464   0.03049   0.02607  -0.0705   0.4396   1.0000
  12.750   1.5242   0.03405   0.02963  -0.0674   0.4257   1.0000
  13.000   1.5080   0.03727   0.03282  -0.0648   0.4105   1.0000
  13.250   1.4859   0.04111   0.03660  -0.0621   0.3896   1.0000
  13.500   1.4746   0.04412   0.03954  -0.0600   0.3733   1.0000
  13.750   1.4580   0.04768   0.04300  -0.0578   0.3543   1.0000
  14.000   1.4386   0.05159   0.04681  -0.0556   0.3327   1.0000
  14.250   1.4275   0.05487   0.05002  -0.0539   0.3161   1.0000
  14.500   1.4152   0.05834   0.05343  -0.0523   0.2987   1.0000
  14.750   1.3959   0.06256   0.05754  -0.0505   0.2778   1.0000
  15.000   1.3814   0.06643   0.06133  -0.0490   0.2575   1.0000
  15.250   1.3692   0.07016   0.06497  -0.0478   0.2390   1.0000
  15.500   1.3551   0.07414   0.06886  -0.0466   0.2202   1.0000
  15.750   1.3439   0.07789   0.07253  -0.0456   0.2002   1.0000
  16.000   1.3242   0.08267   0.07715  -0.0444   0.1743   1.0000
  16.250   1.3190   0.08590   0.08035  -0.0438   0.1601   1.0000
  16.500   1.3044   0.09026   0.08457  -0.0431   0.1368   1.0000
  16.750   1.3003   0.09348   0.08774  -0.0427   0.1233   1.0000
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