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DRAGONFLY CANARD (drgnfly-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: DRAGONFLY CANARD (drgnfly-il)
Reynolds number: 200,000
Max Cl/Cd: 45.83 at α=2.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-drgnfly-il-200000-n5.txt
Download as CSV file: xf-drgnfly-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000   0.0318   0.10944   0.10358  -0.1071   0.6191   0.0380
 -11.750   0.0351   0.10635   0.10048  -0.1084   0.6181   0.0383
 -11.500   0.0136   0.09884   0.09301  -0.1127   0.6177   0.0337
 -11.250   0.0212   0.09618   0.09033  -0.1133   0.6166   0.0335
 -11.000   0.0323   0.09448   0.08861  -0.1134   0.6154   0.0346
 -10.750   0.0323   0.09089   0.08503  -0.1149   0.6145   0.0346
 -10.250   0.0021   0.07718   0.07142  -0.1204   0.6128   0.0282
 -10.000  -0.0005   0.07352   0.06780  -0.1219   0.6116   0.0281
  -9.750  -0.0102   0.06852   0.06286  -0.1243   0.6106   0.0280
  -9.500  -0.0292   0.06132   0.05571  -0.1290   0.6095   0.0277
  -9.250  -0.0653   0.05402   0.04835  -0.1333   0.6086   0.0274
  -9.000  -0.0922   0.05023   0.04445  -0.1321   0.6074   0.0272
  -8.750  -0.1181   0.04739   0.04147  -0.1284   0.6063   0.0271
  -8.500  -0.1392   0.04378   0.03760  -0.1251   0.6052   0.0271
  -8.250  -0.1505   0.04057   0.03406  -0.1220   0.6042   0.0273
  -8.000  -0.1582   0.03741   0.03044  -0.1186   0.6031   0.0278
  -7.750  -0.1583   0.03492   0.02743  -0.1155   0.6021   0.0283
  -7.500  -0.1469   0.03315   0.02546  -0.1139   0.6011   0.0286
  -7.250  -0.1324   0.03169   0.02378  -0.1125   0.6000   0.0289
  -7.000  -0.1158   0.03042   0.02230  -0.1113   0.5990   0.0292
  -6.750  -0.0988   0.02931   0.02105  -0.1100   0.5973   0.0295
  -6.500  -0.0805   0.02827   0.01986  -0.1088   0.5957   0.0299
  -6.250  -0.0612   0.02728   0.01871  -0.1077   0.5941   0.0304
  -6.000  -0.0408   0.02634   0.01760  -0.1068   0.5927   0.0309
  -5.750  -0.0193   0.02548   0.01655  -0.1059   0.5913   0.0314
  -5.500   0.0031   0.02478   0.01567  -0.1051   0.5900   0.0324
  -5.250   0.0263   0.02415   0.01484  -0.1045   0.5888   0.0333
  -5.000   0.0501   0.02347   0.01401  -0.1039   0.5877   0.0339
  -4.750   0.0741   0.02271   0.01322  -0.1035   0.5867   0.0345
  -4.500   0.0983   0.02216   0.01262  -0.1031   0.5857   0.0352
  -4.250   0.1226   0.02167   0.01208  -0.1027   0.5847   0.0360
  -4.000   0.1471   0.02124   0.01158  -0.1022   0.5838   0.0369
  -3.750   0.1689   0.02095   0.01128  -0.1013   0.5823   0.0379
  -3.500   0.1904   0.02076   0.01108  -0.1004   0.5805   0.0393
  -3.250   0.2116   0.02050   0.01083  -0.0994   0.5789   0.0405
  -3.000   0.2325   0.02023   0.01059  -0.0985   0.5774   0.0418
  -2.750   0.2543   0.02004   0.01040  -0.0976   0.5761   0.0431
  -2.500   0.2767   0.01988   0.01020  -0.0968   0.5748   0.0448
  -2.250   0.2996   0.01974   0.01002  -0.0960   0.5736   0.0467
  -2.000   0.3226   0.01957   0.00983  -0.0954   0.5725   0.0495
  -1.750   0.3465   0.01945   0.00968  -0.0948   0.5715   0.0542
  -1.500   0.3705   0.01929   0.00952  -0.0943   0.5706   0.0611
  -1.250   0.3947   0.01909   0.00935  -0.0938   0.5697   0.0798
  -1.000   0.4171   0.01871   0.00920  -0.0931   0.5688   0.1501
  -0.750   0.4322   0.01831   0.00932  -0.0913   0.5673   0.2886
  -0.500   0.4405   0.01799   0.00969  -0.0882   0.5654   0.4625
  -0.250   0.4524   0.01791   0.01004  -0.0855   0.5636   0.5807
   0.000   0.4668   0.01783   0.01035  -0.0830   0.5620   0.6825
   0.250   0.5988   0.01784   0.01095  -0.1035   0.5611   0.9299
   0.500   0.6350   0.01815   0.01118  -0.1055   0.5598   0.9537
   0.750   0.6725   0.01836   0.01130  -0.1078   0.5586   0.9651
   1.000   0.7100   0.01853   0.01137  -0.1103   0.5574   0.9745
   1.250   0.7476   0.01865   0.01139  -0.1127   0.5564   0.9832
   1.500   0.7877   0.01875   0.01140  -0.1157   0.5555   0.9897
   1.750   0.8275   0.01886   0.01143  -0.1186   0.5547   0.9956
   2.000   0.8673   0.01896   0.01143  -0.1216   0.5540   1.0000
   2.250   0.8831   0.01927   0.01172  -0.1199   0.5528   1.0000
   2.500   0.8815   0.02016   0.01272  -0.1154   0.5500   1.0000
   2.750   0.8870   0.02079   0.01339  -0.1121   0.5475   1.0000
   3.000   0.8976   0.02125   0.01385  -0.1095   0.5456   1.0000
   3.250   0.9109   0.02163   0.01422  -0.1074   0.5441   1.0000
   3.500   0.9266   0.02194   0.01450  -0.1056   0.5429   1.0000
   3.750   0.9449   0.02216   0.01469  -0.1043   0.5418   1.0000
   4.000   0.9661   0.02228   0.01477  -0.1034   0.5408   1.0000
   4.250   0.9891   0.02237   0.01482  -0.1028   0.5399   1.0000
   4.500   1.0143   0.02242   0.01483  -0.1026   0.5392   1.0000
   5.000   0.8844   0.02835   0.02104  -0.0765   0.5263   1.0000
   5.250   0.9086   0.02841   0.02107  -0.0762   0.5256   1.0000
   5.500   0.9341   0.02842   0.02106  -0.0760   0.5250   1.0000
   5.750   0.9615   0.02834   0.02095  -0.0760   0.5245   1.0000
   6.750   0.7611   0.05149   0.04439  -0.0548   0.4766   1.0000
   7.000   0.8034   0.04996   0.04281  -0.0555   0.4794   1.0000
   7.250   0.8369   0.04918   0.04202  -0.0559   0.4805   1.0000
   8.250   0.8300   0.05875   0.05170  -0.0502   0.4563   1.0000
   8.500   0.8524   0.05894   0.05190  -0.0500   0.4551   1.0000
   8.750   0.8752   0.05911   0.05207  -0.0498   0.4542   1.0000
   9.000   0.8985   0.05921   0.05219  -0.0497   0.4535   1.0000
   9.250   0.9229   0.05920   0.05220  -0.0496   0.4529   1.0000
  10.250   0.9227   0.06897   0.06214  -0.0456   0.4282   1.0000
  10.500   0.9438   0.06927   0.06247  -0.0454   0.4269   1.0000
  10.750   0.9667   0.06935   0.06258  -0.0453   0.4259   1.0000
  11.000   0.9906   0.06928   0.06256  -0.0453   0.4251   1.0000
  11.250   1.0147   0.06921   0.06252  -0.0452   0.4244   1.0000
  12.250   1.0212   0.07891   0.07246  -0.0425   0.3998   1.0000
  12.500   1.0425   0.07909   0.07269  -0.0424   0.3984   1.0000
  12.750   1.0655   0.07906   0.07272  -0.0423   0.3973   1.0000
  13.000   1.0892   0.07892   0.07264  -0.0423   0.3965   1.0000
  13.250   1.1140   0.07864   0.07243  -0.0423   0.3958   1.0000
  16.250   1.2560   0.09341   0.08805  -0.0398   0.3260   1.0000
  16.500   1.2723   0.09403   0.08868  -0.0398   0.3122   1.0000
  16.750   1.3016   0.09291   0.08746  -0.0398   0.2940   1.0000
  17.000   1.3108   0.09434   0.08881  -0.0396   0.2724   1.0000
  17.250   1.3196   0.09569   0.08996  -0.0393   0.2458   1.0000
  17.500   1.3167   0.09854   0.09263  -0.0389   0.2205   1.0000
  17.750   1.3073   0.10230   0.09620  -0.0385   0.1946   1.0000
  18.000   1.3005   0.10587   0.09968  -0.0384   0.1753   1.0000
  18.250   1.2891   0.11008   0.10374  -0.0383   0.1538   1.0000
  18.500   1.2801   0.11404   0.10761  -0.0384   0.1355   1.0000
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