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DRAGONFLY CANARD (drgnfly-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: DRAGONFLY CANARD (drgnfly-il)
Reynolds number: 1,000,000
Max Cl/Cd: 144.64 at α=9.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-drgnfly-il-1000000.txt
Download as CSV file: xf-drgnfly-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250   0.0531   0.08921   0.08545  -0.1204   0.5894   0.0215
 -11.000   0.0551   0.08603   0.08228  -0.1217   0.5885   0.0219
 -10.750  -0.1814   0.02889   0.02521  -0.1352   0.5893   0.0201
 -10.500  -0.1665   0.02881   0.02516  -0.1351   0.5881   0.0203
 -10.250  -0.2560   0.03548   0.03126  -0.1356   0.5889   0.0195
 -10.000  -0.2832   0.03300   0.02858  -0.1296   0.5880   0.0195
  -9.750  -0.3101   0.02955   0.02474  -0.1238   0.5870   0.0197
  -9.500  -0.3187   0.02656   0.02146  -0.1199   0.5857   0.0200
  -9.250  -0.3057   0.02555   0.02035  -0.1183   0.5838   0.0202
  -9.000  -0.2877   0.02497   0.01974  -0.1172   0.5829   0.0205
  -8.750  -0.2673   0.02456   0.01932  -0.1164   0.5821   0.0207
  -8.500  -0.2485   0.02391   0.01862  -0.1154   0.5811   0.0210
  -8.250  -0.2321   0.02289   0.01747  -0.1140   0.5801   0.0212
  -8.000  -0.2154   0.02178   0.01620  -0.1125   0.5790   0.0215
  -7.750  -0.1981   0.02059   0.01484  -0.1111   0.5780   0.0217
  -7.500  -0.1788   0.01957   0.01366  -0.1099   0.5768   0.0220
  -7.250  -0.1581   0.01864   0.01259  -0.1089   0.5757   0.0222
  -7.000  -0.1364   0.01781   0.01162  -0.1081   0.5746   0.0225
  -6.750  -0.1135   0.01715   0.01083  -0.1073   0.5735   0.0229
  -6.500  -0.0896   0.01667   0.01025  -0.1067   0.5724   0.0232
  -6.250  -0.0652   0.01633   0.00980  -0.1062   0.5711   0.0235
  -6.000  -0.0423   0.01543   0.00877  -0.1056   0.5697   0.0239
  -5.750  -0.0187   0.01472   0.00804  -0.1051   0.5682   0.0245
  -5.500   0.0061   0.01430   0.00762  -0.1047   0.5675   0.0250
  -5.250   0.0312   0.01393   0.00723  -0.1044   0.5666   0.0254
  -5.000   0.0564   0.01357   0.00685  -0.1040   0.5655   0.0258
  -4.750   0.0815   0.01323   0.00649  -0.1036   0.5645   0.0262
  -4.500   0.1066   0.01292   0.00615  -0.1032   0.5635   0.0267
  -4.250   0.1319   0.01263   0.00584  -0.1028   0.5624   0.0273
  -4.000   0.1575   0.01241   0.00558  -0.1025   0.5613   0.0278
  -3.750   0.1835   0.01222   0.00536  -0.1022   0.5603   0.0282
  -3.500   0.2065   0.01177   0.00489  -0.1015   0.5592   0.0289
  -3.250   0.2304   0.01146   0.00456  -0.1009   0.5582   0.0298
  -3.000   0.2558   0.01128   0.00436  -0.1005   0.5571   0.0306
  -2.750   0.2815   0.01113   0.00419  -0.1003   0.5559   0.0314
  -2.500   0.3075   0.01105   0.00407  -0.1000   0.5545   0.0323
  -2.250   0.3336   0.01098   0.00397  -0.0999   0.5532   0.0331
  -2.000   0.3600   0.01085   0.00385  -0.0997   0.5524   0.0337
  -1.750   0.3850   0.01062   0.00362  -0.0992   0.5516   0.0356
  -1.500   0.4111   0.01051   0.00352  -0.0991   0.5507   0.0376
  -1.250   0.4377   0.01042   0.00343  -0.0989   0.5497   0.0395
  -1.000   0.4640   0.01032   0.00334  -0.0988   0.5487   0.0428
  -0.750   0.4900   0.01020   0.00327  -0.0986   0.5476   0.0540
  -0.500   0.5116   0.00977   0.00320  -0.0977   0.5466   0.1680
  -0.250   0.5309   0.00922   0.00314  -0.0964   0.5456   0.3351
   0.000   0.5492   0.00870   0.00314  -0.0949   0.5446   0.5108
   0.250   0.5709   0.00847   0.00316  -0.0938   0.5436   0.5986
   0.500   0.5932   0.00832   0.00318  -0.0929   0.5425   0.6640
   0.750   0.6154   0.00821   0.00322  -0.0919   0.5412   0.7202
   1.000   0.6361   0.00810   0.00330  -0.0905   0.5399   0.7890
   1.250   0.7185   0.00803   0.00362  -0.1025   0.5385   0.9356
   1.500   0.7701   0.00823   0.00381  -0.1077   0.5379   0.9606
   1.750   0.8086   0.00839   0.00396  -0.1101   0.5371   0.9710
   2.000   0.8489   0.00849   0.00404  -0.1130   0.5362   0.9750
   2.250   0.8818   0.00859   0.00413  -0.1144   0.5351   0.9802
   2.500   0.9190   0.00867   0.00420  -0.1167   0.5339   0.9829
   2.750   0.9583   0.00874   0.00425  -0.1195   0.5329   0.9848
   3.000   0.9963   0.00881   0.00430  -0.1221   0.5318   0.9872
   3.250   1.0331   0.00888   0.00435  -0.1244   0.5307   0.9899
   3.500   1.0680   0.00895   0.00441  -0.1263   0.5295   0.9927
   3.750   1.1054   0.00901   0.00445  -0.1288   0.5284   0.9944
   4.000   1.1433   0.00906   0.00449  -0.1314   0.5273   0.9963
   4.250   1.1804   0.00915   0.00455  -0.1339   0.5260   0.9982
   4.500   1.2169   0.00931   0.00468  -0.1362   0.5242   0.9997
   4.750   1.2423   0.00937   0.00477  -0.1362   0.5234   1.0000
   5.000   1.2643   0.00943   0.00486  -0.1354   0.5226   1.0000
   5.250   1.2863   0.00950   0.00496  -0.1347   0.5215   1.0000
   5.500   1.3085   0.00957   0.00506  -0.1339   0.5204   1.0000
   5.750   1.3308   0.00965   0.00516  -0.1332   0.5192   1.0000
   6.000   1.3531   0.00973   0.00527  -0.1326   0.5180   1.0000
   6.250   1.3755   0.00981   0.00536  -0.1319   0.5167   1.0000
   6.500   1.3979   0.00989   0.00546  -0.1312   0.5154   1.0000
   6.750   1.4201   0.00998   0.00557  -0.1305   0.5142   1.0000
   7.000   1.4422   0.01009   0.00568  -0.1298   0.5129   1.0000
   7.250   1.4648   0.01023   0.00582  -0.1293   0.5114   1.0000
   7.500   1.4886   0.01044   0.00603  -0.1290   0.5096   1.0000
   7.750   1.5083   0.01055   0.00620  -0.1278   0.5087   1.0000
   8.000   1.5278   0.01066   0.00636  -0.1266   0.5076   1.0000
   8.250   1.5472   0.01077   0.00654  -0.1254   0.5062   1.0000
   8.500   1.5665   0.01088   0.00669  -0.1242   0.5047   1.0000
   8.750   1.5861   0.01100   0.00684  -0.1230   0.5031   1.0000
   9.000   1.6056   0.01111   0.00699  -0.1219   0.5016   1.0000
   9.250   1.6243   0.01123   0.00715  -0.1206   0.5000   1.0000
   9.500   1.6434   0.01137   0.00731  -0.1194   0.4984   1.0000
   9.750   1.6656   0.01156   0.00748  -0.1189   0.4955   1.0000
  10.000   1.6790   0.01174   0.00773  -0.1166   0.4942   1.0000
  10.250   1.6767   0.01181   0.00788  -0.1110   0.4910   1.0000
  10.500   1.6818   0.01191   0.00803  -0.1071   0.4869   1.0000
  10.750   1.6887   0.01214   0.00821  -0.1038   0.4806   1.0000
  11.000   1.6897   0.01254   0.00871  -0.0998   0.4733   1.0000
  11.250   1.6901   0.01324   0.00941  -0.0961   0.4634   1.0000
  11.500   1.6889   0.01430   0.01046  -0.0928   0.4531   1.0000
  11.750   1.6916   0.01549   0.01170  -0.0905   0.4428   1.0000
  12.000   1.6908   0.01709   0.01332  -0.0882   0.4338   1.0000
  12.250   1.6885   0.01897   0.01522  -0.0860   0.4257   1.0000
  12.500   1.6788   0.02142   0.01769  -0.0833   0.4141   1.0000
  12.750   1.6643   0.02422   0.02050  -0.0803   0.4031   1.0000
  13.000   1.6460   0.02730   0.02358  -0.0770   0.3929   1.0000
  13.250   1.6213   0.03087   0.02713  -0.0734   0.3799   1.0000
  13.500   1.6064   0.03394   0.03019  -0.0707   0.3687   1.0000
  13.750   1.5876   0.03742   0.03365  -0.0679   0.3553   1.0000
  14.000   1.5683   0.04107   0.03726  -0.0653   0.3408   1.0000
  14.250   1.5520   0.04456   0.04073  -0.0630   0.3270   1.0000
  14.500   1.5351   0.04819   0.04432  -0.0608   0.3117   1.0000
  14.750   1.5088   0.05273   0.04876  -0.0581   0.2905   1.0000
  15.000   1.4924   0.05653   0.05249  -0.0562   0.2725   1.0000
  15.250   1.4761   0.06040   0.05630  -0.0545   0.2550   1.0000
  15.500   1.4575   0.06456   0.06035  -0.0527   0.2348   1.0000
  15.750   1.4416   0.06857   0.06425  -0.0512   0.2131   1.0000
  16.000   1.4195   0.07329   0.06883  -0.0496   0.1875   1.0000
  16.250   1.4122   0.07656   0.07202  -0.0487   0.1708   1.0000
  16.500   1.3947   0.08101   0.07634  -0.0476   0.1473   1.0000
  16.750   1.3836   0.08481   0.08003  -0.0468   0.1277   1.0000
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