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RONCZ 1046 VOYAGER CANARD AIRFOIL (r1046-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: RONCZ 1046 VOYAGER CANARD AIRFOIL (r1046-il)
Reynolds number: 100,000
Max Cl/Cd: 20.53 at α=1°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-r1046-il-100000-n5.txt
Download as CSV file: xf-r1046-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250   0.0250   0.11175   0.10513  -0.1102   0.6791   0.0570
 -11.000   0.0267   0.10870   0.10209  -0.1121   0.6771   0.0571
 -10.750   0.0289   0.10551   0.09889  -0.1138   0.6752   0.0571
 -10.250   0.0519   0.09612   0.08937  -0.1142   0.6718   0.0364
  -9.750   0.0483   0.08753   0.08088  -0.1181   0.6679   0.0319
  -9.500   0.0536   0.08484   0.07822  -0.1190   0.6657   0.0315
  -9.250   0.0556   0.08168   0.07509  -0.1202   0.6636   0.0309
  -9.000   0.0547   0.07810   0.07154  -0.1218   0.6616   0.0305
  -8.750   0.0508   0.07405   0.06752  -0.1237   0.6597   0.0300
  -8.250  -0.0144   0.05678   0.05020  -0.1349   0.6569   0.0276
  -8.000  -0.0282   0.05366   0.04693  -0.1345   0.6553   0.0274
  -7.750  -0.0393   0.05043   0.04355  -0.1338   0.6531   0.0273
  -7.500  -0.0474   0.04714   0.04002  -0.1327   0.6509   0.0273
  -7.250  -0.0530   0.04368   0.03617  -0.1310   0.6489   0.0274
  -7.000  -0.0474   0.04144   0.03365  -0.1297   0.6469   0.0280
  -6.750  -0.0332   0.04033   0.03244  -0.1288   0.6449   0.0290
  -6.500  -0.0219   0.03845   0.03023  -0.1276   0.6432   0.0300
  -6.250  -0.0098   0.03625   0.02757  -0.1261   0.6416   0.0310
  -6.000   0.0055   0.03410   0.02490  -0.1247   0.6401   0.0317
  -5.750   0.0249   0.03239   0.02278  -0.1237   0.6387   0.0324
  -5.500   0.0442   0.03145   0.02173  -0.1227   0.6366   0.0334
  -5.250   0.0627   0.03062   0.02078  -0.1216   0.6341   0.0346
  -5.000   0.0826   0.02977   0.01965  -0.1204   0.6318   0.0371
  -4.750   0.1031   0.02923   0.01912  -0.1197   0.6298   0.0392
  -4.500   0.1248   0.02857   0.01830  -0.1188   0.6280   0.0419
  -4.250   0.1467   0.02793   0.01760  -0.1180   0.6264   0.0443
  -4.000   0.1693   0.02749   0.01706  -0.1173   0.6249   0.0484
  -3.750   0.1920   0.02702   0.01658  -0.1166   0.6236   0.0529
  -3.500   0.2155   0.02659   0.01607  -0.1160   0.6223   0.0591
  -3.250   0.2389   0.02623   0.01563  -0.1154   0.6211   0.0667
  -3.000   0.2516   0.02638   0.01587  -0.1134   0.6181   0.0744
  -2.750   0.2665   0.02643   0.01598  -0.1116   0.6155   0.0850
  -2.500   0.2832   0.02643   0.01604  -0.1102   0.6133   0.1016
  -2.250   0.3011   0.02634   0.01607  -0.1089   0.6115   0.1301
  -2.000   0.3197   0.02613   0.01613  -0.1078   0.6098   0.1872
  -1.750   0.3389   0.02578   0.01621  -0.1069   0.6083   0.2990
  -1.500   0.3582   0.02532   0.01635  -0.1057   0.6070   0.4640
  -1.250   0.3799   0.02504   0.01647  -0.1044   0.6058   0.6038
  -1.000   0.4034   0.02490   0.01655  -0.1030   0.6047   0.7074
  -0.750   0.3910   0.02652   0.01851  -0.0974   0.5997   0.7610
  -0.500   0.4228   0.02734   0.01955  -0.0986   0.5971   0.8743
  -0.250   0.4978   0.02785   0.01989  -0.1079   0.5958   0.9739
   0.000   0.5458   0.02837   0.02021  -0.1127   0.5942   1.0000
   0.250   0.5543   0.02887   0.02057  -0.1100   0.5921   1.0000
   0.500   0.5700   0.02920   0.02073  -0.1083   0.5905   1.0000
   0.750   0.5894   0.02947   0.02085  -0.1072   0.5893   1.0000
   1.000   0.6108   0.02975   0.02098  -0.1063   0.5883   1.0000
   2.000   0.5568   0.03711   0.02825  -0.0862   0.5716   1.0000
   3.000   0.4876   0.04971   0.04086  -0.0732   0.5442   1.0000
   3.250   0.5086   0.05037   0.04142  -0.0728   0.5426   1.0000
   3.500   0.5318   0.05090   0.04186  -0.0725   0.5413   1.0000
   3.750   0.5577   0.05124   0.04210  -0.0724   0.5404   1.0000
   4.250   0.5471   0.05619   0.04704  -0.0687   0.5282   1.0000
   4.500   0.5709   0.05666   0.04744  -0.0685   0.5266   1.0000
   4.750   0.5961   0.05704   0.04775  -0.0684   0.5254   1.0000
   5.000   0.6228   0.05733   0.04797  -0.0683   0.5244   1.0000
   5.500   0.6180   0.06198   0.05264  -0.0653   0.5120   1.0000
   5.750   0.6420   0.06247   0.05309  -0.0652   0.5106   1.0000
   6.000   0.6672   0.06289   0.05347  -0.0651   0.5095   1.0000
   6.500   0.6669   0.06741   0.05802  -0.0627   0.4974   1.0000
   6.750   0.6911   0.06785   0.05845  -0.0626   0.4959   1.0000
   7.000   0.7167   0.06819   0.05876  -0.0626   0.4948   1.0000
   7.250   0.7002   0.07167   0.06230  -0.0608   0.4845   1.0000
   7.500   0.7236   0.07210   0.06272  -0.0607   0.4824   1.0000
   7.750   0.7488   0.07238   0.06300  -0.0606   0.4809   1.0000
   8.250   0.7577   0.07635   0.06704  -0.0590   0.4691   1.0000
   8.500   0.7819   0.07664   0.06733  -0.0589   0.4672   1.0000
   8.750   0.8077   0.07683   0.06752  -0.0589   0.4659   1.0000
   9.000   0.7950   0.08031   0.07108  -0.0577   0.4556   1.0000
   9.250   0.8178   0.08070   0.07150  -0.0575   0.4534   1.0000
   9.500   0.8435   0.08079   0.07161  -0.0575   0.4519   1.0000
  10.000   0.8562   0.08446   0.07539  -0.0563   0.4394   1.0000
  10.250   0.8817   0.08449   0.07546  -0.0563   0.4378   1.0000
  10.750   0.8960   0.08807   0.07916  -0.0553   0.4251   1.0000
  11.000   0.9214   0.08800   0.07915  -0.0552   0.4234   1.0000
  11.250   0.9135   0.09140   0.08262  -0.0546   0.4127   1.0000
  11.500   0.9367   0.09152   0.08280  -0.0545   0.4104   1.0000
  11.750   0.9625   0.09130   0.08265  -0.0543   0.4088   1.0000
  12.250   0.9786   0.09475   0.08625  -0.0537   0.3955   1.0000
  12.750   0.9971   0.09800   0.08968  -0.0532   0.3823   1.0000
  13.000   1.0234   0.09747   0.08923  -0.0530   0.3804   1.0000
  13.500   1.0425   0.10058   0.09251  -0.0526   0.3668   1.0000
  13.750   1.0697   0.09978   0.09181  -0.0524   0.3650   1.0000
  14.000   1.0636   0.10346   0.09559  -0.0523   0.3533   1.0000
  14.250   1.0899   0.10271   0.09494  -0.0521   0.3512   1.0000
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