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cr001sm (cr001sm-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: cr001sm (cr001sm-il)
Reynolds number: 100,000
Max Cl/Cd: 64.26 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-cr001sm-il-100000-n5.txt
Download as CSV file: xf-cr001sm-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: cr001sm                                         
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3560   0.10379   0.09886  -0.0321   1.0000   0.0415
  -8.000  -0.3631   0.10218   0.09736  -0.0322   1.0000   0.0417
  -7.750  -0.3711   0.10057   0.09584  -0.0317   1.0000   0.0419
  -7.500  -0.3750   0.09835   0.09371  -0.0326   1.0000   0.0420
  -7.250  -0.3759   0.09575   0.09117  -0.0340   1.0000   0.0421
  -7.000  -0.3677   0.09052   0.08595  -0.0260   1.0000   0.0447
  -6.750  -0.3681   0.08823   0.08372  -0.0246   1.0000   0.0464
  -6.500  -0.3703   0.08595   0.08150  -0.0240   1.0000   0.0477
  -6.250  -0.3719   0.08353   0.07915  -0.0241   1.0000   0.0486
  -6.000  -0.3721   0.08091   0.07658  -0.0248   1.0000   0.0500
  -5.750  -0.3698   0.07800   0.07370  -0.0267   1.0000   0.0516
  -5.500  -0.3224   0.07150   0.06694  -0.0478   0.9950   0.0551
  -5.000  -0.2779   0.06145   0.05689  -0.0541   0.9863   0.0571
  -4.750  -0.2498   0.05725   0.05261  -0.0585   0.9810   0.0585
  -4.500  -0.1944   0.04626   0.04098  -0.0707   0.9764   0.0296
  -4.250  -0.1580   0.04149   0.03595  -0.0762   0.9728   0.0285
  -4.000  -0.1239   0.03701   0.03109  -0.0803   0.9671   0.0277
  -3.750  -0.0850   0.03278   0.02630  -0.0844   0.9627   0.0276
  -3.500  -0.0434   0.02961   0.02241  -0.0879   0.9595   0.0298
  -3.250  -0.0107   0.02737   0.01959  -0.0892   0.9533   0.0304
  -3.000   0.0249   0.02480   0.01655  -0.0911   0.9490   0.0307
  -2.750   0.0623   0.02257   0.01394  -0.0932   0.9458   0.0316
  -2.500   0.0920   0.02119   0.01233  -0.0936   0.9389   0.0330
  -2.250   0.1276   0.02025   0.01123  -0.0951   0.9340   0.0381
  -2.000   0.1610   0.01923   0.01004  -0.0960   0.9284   0.0406
  -1.750   0.1934   0.01825   0.00898  -0.0967   0.9221   0.0432
  -1.500   0.2312   0.01747   0.00816  -0.0986   0.9181   0.0512
  -1.250   0.2603   0.01690   0.00752  -0.0987   0.9094   0.0595
  -1.000   0.2987   0.01613   0.00682  -0.1006   0.9049   0.0914
  -0.750   0.3286   0.01493   0.00670  -0.1016   0.8971   0.3950
  -0.500   0.3655   0.01333   0.00648  -0.1025   0.8925   1.0000
  -0.250   0.3974   0.01332   0.00624  -0.1031   0.8837   1.0000
   0.000   0.4339   0.01325   0.00596  -0.1045   0.8768   1.0000
   0.250   0.4638   0.01325   0.00580  -0.1047   0.8662   1.0000
   0.500   0.4958   0.01323   0.00564  -0.1053   0.8564   1.0000
   0.750   0.5312   0.01315   0.00544  -0.1064   0.8480   1.0000
   1.000   0.5607   0.01317   0.00537  -0.1065   0.8359   1.0000
   1.250   0.5909   0.01317   0.00530  -0.1067   0.8237   1.0000
   1.500   0.6213   0.01318   0.00524  -0.1069   0.8109   1.0000
   1.750   0.6516   0.01319   0.00519  -0.1070   0.7972   1.0000
   2.000   0.6817   0.01320   0.00516  -0.1071   0.7820   1.0000
   2.250   0.7118   0.01322   0.00512  -0.1071   0.7656   1.0000
   2.500   0.7404   0.01327   0.00512  -0.1069   0.7469   1.0000
   2.750   0.7681   0.01335   0.00515  -0.1064   0.7268   1.0000
   3.000   0.7963   0.01345   0.00522  -0.1061   0.7068   1.0000
   3.250   0.8223   0.01361   0.00534  -0.1054   0.6850   1.0000
   3.500   0.8489   0.01378   0.00545  -0.1048   0.6634   1.0000
   3.750   0.8744   0.01399   0.00562  -0.1041   0.6403   1.0000
   4.000   0.8995   0.01422   0.00586  -0.1033   0.6167   1.0000
   4.250   0.9242   0.01449   0.00608  -0.1024   0.5925   1.0000
   4.500   0.9482   0.01479   0.00634  -0.1014   0.5668   1.0000
   4.750   0.9716   0.01512   0.00664  -0.1004   0.5400   1.0000
   5.000   0.9945   0.01549   0.00696  -0.0993   0.5116   1.0000
   5.250   1.0166   0.01590   0.00736  -0.0980   0.4817   1.0000
   5.500   1.0381   0.01635   0.00777  -0.0967   0.4498   1.0000
   5.750   1.0589   0.01686   0.00821  -0.0953   0.4154   1.0000
   6.000   1.0787   0.01744   0.00870  -0.0938   0.3795   1.0000
   6.250   1.0979   0.01808   0.00928  -0.0923   0.3421   1.0000
   6.500   1.1164   0.01879   0.00989  -0.0907   0.3057   1.0000
   6.750   1.1344   0.01957   0.01056  -0.0891   0.2714   1.0000
   7.000   1.1520   0.02040   0.01130  -0.0875   0.2394   1.0000
   7.250   1.1694   0.02126   0.01209  -0.0860   0.2089   1.0000
   7.500   1.1864   0.02217   0.01293  -0.0844   0.1794   1.0000
   7.750   1.2028   0.02312   0.01387  -0.0828   0.1505   1.0000
   8.000   1.2182   0.02418   0.01484  -0.0810   0.1213   1.0000
   8.250   1.2323   0.02537   0.01593  -0.0792   0.0943   1.0000
   8.500   1.2453   0.02668   0.01717  -0.0772   0.0723   1.0000
   8.750   1.2562   0.02816   0.01859  -0.0749   0.0573   1.0000
   9.000   1.2666   0.02963   0.02014  -0.0725   0.0478   1.0000
   9.250   1.2747   0.03116   0.02173  -0.0698   0.0410   1.0000
   9.500   1.2818   0.03265   0.02338  -0.0670   0.0361   1.0000
   9.750   1.2848   0.03452   0.02533  -0.0638   0.0335   1.0000
  10.000   1.2912   0.03626   0.02729  -0.0611   0.0312   1.0000
  10.250   1.2972   0.03805   0.02925  -0.0586   0.0288   1.0000
  10.500   1.3016   0.03988   0.03119  -0.0563   0.0266   1.0000
  10.750   1.3029   0.04230   0.03367  -0.0539   0.0248   1.0000
  11.000   1.3097   0.04444   0.03609  -0.0519   0.0235   1.0000
  11.250   1.3152   0.04692   0.03883  -0.0500   0.0225   1.0000
  11.500   1.3193   0.04960   0.04176  -0.0482   0.0216   1.0000
  11.750   1.3210   0.05244   0.04485  -0.0465   0.0207   1.0000
  12.000   1.3202   0.05532   0.04796  -0.0450   0.0199   1.0000
  12.250   1.3171   0.05830   0.05117  -0.0439   0.0191   1.0000
  12.500   1.3123   0.06157   0.05460  -0.0431   0.0184   1.0000
  12.750   1.3050   0.06548   0.05868  -0.0426   0.0178   1.0000
  13.000   1.2941   0.07013   0.06354  -0.0426   0.0174   1.0000
  13.250   1.2824   0.07481   0.06853  -0.0432   0.0172   1.0000
  13.500   1.2690   0.08004   0.07403  -0.0445   0.0170   1.0000
  13.750   1.2536   0.08589   0.08016  -0.0466   0.0169   1.0000
  14.000   1.2369   0.09236   0.08687  -0.0495   0.0169   1.0000
  14.250   1.2195   0.09943   0.09416  -0.0532   0.0169   1.0000
  14.500   1.2015   0.10711   0.10204  -0.0576   0.0170   1.0000
  14.750   1.1832   0.11551   0.11063  -0.0628   0.0171   1.0000
  15.000   1.1650   0.12450   0.11977  -0.0686   0.0172   1.0000
  15.250   1.1476   0.13391   0.12929  -0.0746   0.0174   1.0000
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