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RONCZ 1046 VOYAGER CANARD AIRFOIL (r1046-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: RONCZ 1046 VOYAGER CANARD AIRFOIL (r1046-il)
Reynolds number: 500,000
Max Cl/Cd: 101.39 at α=10°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-r1046-il-500000.txt
Download as CSV file: xf-r1046-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RONCZ 1046 VOYAGER CANARD AIRFOIL               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750   0.0602   0.09549   0.09108  -0.1140   0.6215   0.0227
 -10.500   0.0405   0.08800   0.08366  -0.1190   0.6209   0.0237
 -10.250   0.0439   0.08464   0.08033  -0.1202   0.6198   0.0237
 -10.000   0.0556   0.08317   0.07887  -0.1199   0.6183   0.0240
  -9.750   0.0636   0.08104   0.07676  -0.1205   0.6169   0.0243
  -9.500   0.0699   0.07865   0.07438  -0.1214   0.6155   0.0247
  -9.250   0.0732   0.07581   0.07156  -0.1225   0.6141   0.0250
  -9.000   0.0739   0.07256   0.06833  -0.1240   0.6128   0.0252
  -8.750   0.0712   0.06879   0.06459  -0.1259   0.6116   0.0264
  -8.250  -0.1386   0.03279   0.02752  -0.1332   0.6115   0.0168
  -8.000  -0.1353   0.02981   0.02428  -0.1314   0.6101   0.0167
  -7.750  -0.1278   0.02720   0.02137  -0.1297   0.6087   0.0166
  -7.500  -0.1169   0.02497   0.01872  -0.1279   0.6072   0.0167
  -7.250  -0.1008   0.02335   0.01673  -0.1266   0.6055   0.0168
  -7.000  -0.0831   0.02158   0.01469  -0.1255   0.6039   0.0170
  -6.750  -0.0620   0.02033   0.01334  -0.1248   0.6028   0.0173
  -6.500  -0.0387   0.01960   0.01253  -0.1244   0.6015   0.0177
  -6.250  -0.0142   0.01911   0.01200  -0.1241   0.6001   0.0184
  -6.000   0.0099   0.01839   0.01113  -0.1236   0.5987   0.0192
  -5.750   0.0346   0.01775   0.01032  -0.1231   0.5974   0.0198
  -5.500   0.0585   0.01685   0.00932  -0.1225   0.5960   0.0205
  -5.250   0.0833   0.01629   0.00874  -0.1222   0.5947   0.0212
  -5.000   0.1087   0.01587   0.00827  -0.1219   0.5935   0.0222
  -4.750   0.1343   0.01548   0.00779  -0.1216   0.5922   0.0232
  -4.500   0.1588   0.01497   0.00725  -0.1211   0.5909   0.0247
  -4.250   0.1848   0.01474   0.00697  -0.1209   0.5895   0.0265
  -4.000   0.2103   0.01450   0.00669  -0.1207   0.5878   0.0288
  -3.750   0.2362   0.01426   0.00646  -0.1205   0.5869   0.0319
  -3.500   0.2612   0.01392   0.00615  -0.1201   0.5859   0.0358
  -3.250   0.2869   0.01366   0.00590  -0.1198   0.5848   0.0407
  -3.000   0.3129   0.01346   0.00572  -0.1197   0.5836   0.0475
  -2.750   0.3392   0.01329   0.00557  -0.1195   0.5824   0.0568
  -2.500   0.3651   0.01306   0.00542  -0.1193   0.5812   0.0751
  -2.250   0.3906   0.01279   0.00531  -0.1192   0.5800   0.1151
  -2.000   0.4156   0.01245   0.00522  -0.1190   0.5788   0.1870
  -1.750   0.4403   0.01210   0.00516  -0.1187   0.5775   0.2838
  -1.500   0.4644   0.01173   0.00514  -0.1184   0.5763   0.3972
  -1.250   0.4886   0.01145   0.00517  -0.1180   0.5752   0.5097
  -1.000   0.5137   0.01132   0.00524  -0.1177   0.5742   0.5869
  -0.750   0.5389   0.01127   0.00535  -0.1173   0.5730   0.6547
  -0.500   0.5630   0.01132   0.00559  -0.1166   0.5717   0.7261
  -0.250   0.5863   0.01120   0.00569  -0.1157   0.5709   0.7885
   0.000   0.6106   0.01114   0.00580  -0.1148   0.5700   0.8492
   0.250   0.6417   0.01119   0.00597  -0.1153   0.5689   0.9099
   0.500   0.6810   0.01133   0.00612  -0.1176   0.5676   0.9484
   0.750   0.7204   0.01150   0.00625  -0.1201   0.5663   0.9704
   1.000   0.7686   0.01164   0.00635  -0.1246   0.5651   0.9773
   1.250   0.8121   0.01178   0.00643  -0.1282   0.5640   0.9846
   1.500   0.8588   0.01189   0.00650  -0.1325   0.5629   0.9901
   1.750   0.9066   0.01199   0.00655  -0.1370   0.5618   0.9959
   2.000   0.9515   0.01207   0.00658  -0.1410   0.5607   1.0000
   2.250   0.9734   0.01218   0.00665  -0.1402   0.5597   1.0000
   2.500   0.9962   0.01230   0.00673  -0.1396   0.5585   1.0000
   2.750   1.0196   0.01247   0.00686  -0.1390   0.5574   1.0000
   3.000   1.0428   0.01275   0.00710  -0.1385   0.5562   1.0000
   3.250   1.0641   0.01302   0.00738  -0.1376   0.5551   1.0000
   3.500   1.0844   0.01317   0.00757  -0.1365   0.5542   1.0000
   3.750   1.1048   0.01335   0.00777  -0.1354   0.5531   1.0000
   4.000   1.1251   0.01352   0.00797  -0.1343   0.5519   1.0000
   4.250   1.1456   0.01369   0.00817  -0.1332   0.5504   1.0000
   4.500   1.1667   0.01386   0.00836  -0.1322   0.5490   1.0000
   4.750   1.1883   0.01405   0.00856  -0.1314   0.5478   1.0000
   5.000   1.2106   0.01422   0.00876  -0.1307   0.5466   1.0000
   5.250   1.2339   0.01437   0.00892  -0.1301   0.5454   1.0000
   5.500   1.2582   0.01450   0.00905  -0.1298   0.5442   1.0000
   5.750   1.2834   0.01464   0.00918  -0.1296   0.5430   1.0000
   6.000   1.3090   0.01483   0.00936  -0.1296   0.5420   1.0000
   6.250   1.3353   0.01509   0.00961  -0.1297   0.5408   1.0000
   6.500   1.3579   0.01544   0.01000  -0.1292   0.5393   1.0000
   6.750   1.3754   0.01559   0.01023  -0.1276   0.5377   1.0000
   7.000   1.3937   0.01578   0.01049  -0.1263   0.5358   1.0000
   7.250   1.4133   0.01598   0.01075  -0.1252   0.5340   1.0000
   7.500   1.4344   0.01617   0.01099  -0.1243   0.5323   1.0000
   7.750   1.4567   0.01630   0.01116  -0.1237   0.5307   1.0000
   8.000   1.4813   0.01641   0.01129  -0.1236   0.5292   1.0000
   8.250   1.5081   0.01648   0.01138  -0.1238   0.5278   1.0000
   8.500   1.5385   0.01648   0.01137  -0.1246   0.5261   1.0000
   8.750   1.5648   0.01663   0.01154  -0.1248   0.5237   1.0000
   9.000   1.5730   0.01678   0.01181  -0.1216   0.5208   1.0000
   9.250   1.5865   0.01686   0.01197  -0.1194   0.5178   1.0000
   9.500   1.6073   0.01671   0.01185  -0.1184   0.5148   1.0000
   9.750   1.6358   0.01644   0.01156  -0.1187   0.5118   1.0000
  10.000   1.6618   0.01639   0.01150  -0.1188   0.5087   1.0000
  10.250   1.6520   0.01662   0.01186  -0.1122   0.5050   1.0000
  10.500   1.6578   0.01668   0.01199  -0.1086   0.5009   1.0000
  10.750   1.6755   0.01655   0.01185  -0.1072   0.4969   1.0000
  11.000   1.6880   0.01672   0.01206  -0.1050   0.4931   1.0000
  11.250   1.6830   0.01735   0.01282  -0.1003   0.4887   1.0000
  11.500   1.6901   0.01775   0.01329  -0.0977   0.4843   1.0000
  11.750   1.7083   0.01791   0.01344  -0.0967   0.4805   1.0000
  12.000   1.7006   0.01909   0.01476  -0.0925   0.4754   1.0000
  12.250   1.7011   0.02012   0.01587  -0.0897   0.4699   1.0000
  12.500   1.7084   0.02091   0.01668  -0.0878   0.4641   1.0000
  12.750   1.6985   0.02283   0.01872  -0.0844   0.4567   1.0000
  13.000   1.6990   0.02426   0.02019  -0.0822   0.4492   1.0000
  13.250   1.6897   0.02651   0.02250  -0.0795   0.4397   1.0000
  13.500   1.6773   0.02917   0.02521  -0.0767   0.4290   1.0000
  13.750   1.6668   0.03179   0.02785  -0.0742   0.4175   1.0000
  14.000   1.6528   0.03482   0.03087  -0.0717   0.4037   1.0000
  14.250   1.6361   0.03817   0.03420  -0.0692   0.3879   1.0000
  14.500   1.6207   0.04154   0.03753  -0.0669   0.3720   1.0000
  14.750   1.6007   0.04538   0.04129  -0.0644   0.3530   1.0000
  15.000   1.5825   0.04919   0.04501  -0.0623   0.3353   1.0000
  15.250   1.5660   0.05298   0.04874  -0.0604   0.3167   1.0000
  15.500   1.5506   0.05678   0.05246  -0.0588   0.2979   1.0000
  15.750   1.5336   0.06085   0.05645  -0.0573   0.2802   1.0000
  16.000   1.5188   0.06480   0.06032  -0.0559   0.2630   1.0000
  16.250   1.5101   0.06820   0.06367  -0.0550   0.2480   1.0000
  16.500   1.4963   0.07227   0.06765  -0.0540   0.2298   1.0000
  16.750   1.4875   0.07585   0.07117  -0.0533   0.2137   1.0000
  17.000   1.4778   0.07961   0.07487  -0.0527   0.1974   1.0000
  17.250   1.4682   0.08344   0.07863  -0.0522   0.1809   1.0000
  17.500   1.4609   0.08708   0.08220  -0.0519   0.1661   1.0000
  17.750   1.4555   0.09055   0.08562  -0.0518   0.1532   1.0000
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