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CURTISS CR-1 AIRFOIL (cr1-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: CURTISS CR-1 AIRFOIL (cr1-il)
Reynolds number: 200,000
Max Cl/Cd: 72.87 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-cr1-il-200000-n5.txt
Download as CSV file: xf-cr1-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: CURTISS CR-1 AIRFOIL                            
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4970   0.03298   0.02794  -0.1120   0.9275   0.0410
  -9.500  -0.4853   0.02971   0.02418  -0.1126   0.9186   0.0416
  -9.250  -0.4626   0.02826   0.02258  -0.1130   0.9114   0.0423
  -9.000  -0.4393   0.02703   0.02122  -0.1133   0.9045   0.0430
  -8.750  -0.4176   0.02602   0.02006  -0.1130   0.8964   0.0438
  -8.500  -0.3935   0.02491   0.01874  -0.1131   0.8904   0.0450
  -8.250  -0.3753   0.02378   0.01737  -0.1119   0.8816   0.0460
  -8.000  -0.3525   0.02257   0.01586  -0.1115   0.8754   0.0472
  -7.750  -0.3330   0.02157   0.01460  -0.1103   0.8669   0.0480
  -7.500  -0.3100   0.02070   0.01359  -0.1097   0.8604   0.0489
  -7.250  -0.2870   0.02008   0.01290  -0.1089   0.8541   0.0500
  -7.000  -0.2639   0.01956   0.01230  -0.1081   0.8472   0.0512
  -6.750  -0.2384   0.01901   0.01160  -0.1077   0.8419   0.0530
  -6.500  -0.2158   0.01844   0.01088  -0.1067   0.8349   0.0547
  -6.250  -0.1916   0.01785   0.01013  -0.1060   0.8292   0.0562
  -6.000  -0.1659   0.01735   0.00958  -0.1056   0.8247   0.0579
  -5.750  -0.1426   0.01699   0.00918  -0.1047   0.8181   0.0599
  -5.500  -0.1174   0.01660   0.00868  -0.1041   0.8128   0.0625
  -5.250  -0.0907   0.01619   0.00815  -0.1038   0.8087   0.0655
  -5.000  -0.0666   0.01593   0.00790  -0.1031   0.8029   0.0687
  -4.750  -0.0410   0.01566   0.00754  -0.1025   0.7977   0.0726
  -4.500  -0.0143   0.01534   0.00716  -0.1021   0.7936   0.0765
  -4.250   0.0114   0.01516   0.00695  -0.1016   0.7888   0.0810
  -4.000   0.0372   0.01497   0.00666  -0.1010   0.7836   0.0862
  -3.750   0.0635   0.01477   0.00647  -0.1007   0.7792   0.0912
  -3.500   0.0912   0.01461   0.00620  -0.1004   0.7754   0.0971
  -3.250   0.1159   0.01443   0.00603  -0.0997   0.7700   0.1019
  -3.000   0.1420   0.01430   0.00587  -0.0993   0.7651   0.1076
  -2.750   0.1695   0.01415   0.00564  -0.0990   0.7608   0.1136
  -2.500   0.1949   0.01402   0.00554  -0.0984   0.7554   0.1199
  -2.250   0.2206   0.01392   0.00538  -0.0978   0.7493   0.1262
  -2.000   0.2477   0.01375   0.00520  -0.0975   0.7441   0.1322
  -1.750   0.2729   0.01366   0.00510  -0.0968   0.7379   0.1385
  -1.500   0.2985   0.01354   0.00498  -0.0962   0.7318   0.1446
  -1.250   0.3260   0.01344   0.00485  -0.0959   0.7267   0.1518
  -1.000   0.3504   0.01337   0.00479  -0.0950   0.7200   0.1591
  -0.750   0.3761   0.01328   0.00473  -0.0944   0.7138   0.1672
  -0.500   0.4031   0.01322   0.00463  -0.0940   0.7084   0.1766
  -0.250   0.4273   0.01317   0.00462  -0.0932   0.7015   0.1865
   0.000   0.4533   0.01309   0.00455  -0.0926   0.6954   0.1964
   0.250   0.4787   0.01306   0.00452  -0.0920   0.6890   0.2081
   0.500   0.5031   0.01300   0.00451  -0.0911   0.6817   0.2197
   0.750   0.5290   0.01294   0.00445  -0.0905   0.6750   0.2316
   1.000   0.5524   0.01289   0.00445  -0.0895   0.6664   0.2433
   1.500   0.6004   0.01276   0.00439  -0.0876   0.6473   0.2745
   1.750   0.6230   0.01267   0.00437  -0.0864   0.6357   0.2959
   2.000   0.6454   0.01255   0.00434  -0.0851   0.6232   0.3283
   2.250   0.6649   0.01219   0.00434  -0.0834   0.6109   0.4512
   2.750   0.8258   0.01152   0.00463  -0.1057   0.5669   1.0000
   3.000   0.8459   0.01169   0.00467  -0.1039   0.5482   1.0000
   3.250   0.8652   0.01189   0.00475  -0.1021   0.5278   1.0000
   3.500   0.8839   0.01213   0.00486  -0.1002   0.5069   1.0000
   3.750   0.9018   0.01240   0.00500  -0.0981   0.4865   1.0000
   4.250   0.9362   0.01303   0.00538  -0.0938   0.4482   1.0000
   4.500   0.9528   0.01336   0.00561  -0.0916   0.4303   1.0000
   4.750   0.9691   0.01371   0.00585  -0.0893   0.4135   1.0000
   5.000   0.9849   0.01406   0.00612  -0.0870   0.3972   1.0000
   5.250   1.0003   0.01443   0.00640  -0.0846   0.3818   1.0000
   5.500   1.0152   0.01481   0.00670  -0.0821   0.3673   1.0000
   6.000   1.0444   0.01557   0.00734  -0.0772   0.3404   1.0000
   6.250   1.0585   0.01595   0.00767  -0.0747   0.3289   1.0000
   6.500   1.0700   0.01634   0.00801  -0.0716   0.3188   1.0000
   6.750   1.0823   0.01672   0.00836  -0.0688   0.3085   1.0000
   7.000   1.0948   0.01712   0.00874  -0.0660   0.2993   1.0000
   7.250   1.1068   0.01756   0.00915  -0.0633   0.2902   1.0000
   7.500   1.1207   0.01799   0.00956  -0.0610   0.2819   1.0000
   7.750   1.1332   0.01848   0.01003  -0.0585   0.2742   1.0000
   8.000   1.1477   0.01894   0.01051  -0.0564   0.2670   1.0000
   8.250   1.1610   0.01947   0.01103  -0.0542   0.2601   1.0000
   8.500   1.1750   0.02001   0.01156  -0.0521   0.2541   1.0000
   8.750   1.1892   0.02055   0.01212  -0.0502   0.2474   1.0000
   9.000   1.2011   0.02122   0.01276  -0.0480   0.2412   1.0000
   9.250   1.2164   0.02176   0.01335  -0.0463   0.2350   1.0000
   9.500   1.2297   0.02241   0.01400  -0.0444   0.2295   1.0000
   9.750   1.2427   0.02311   0.01470  -0.0426   0.2250   1.0000
  10.000   1.2583   0.02370   0.01537  -0.0411   0.2206   1.0000
  10.250   1.2723   0.02438   0.01609  -0.0395   0.2163   1.0000
  10.500   1.2848   0.02517   0.01688  -0.0378   0.2123   1.0000
  10.750   1.2984   0.02589   0.01766  -0.0363   0.2070   1.0000
  11.000   1.3109   0.02668   0.01850  -0.0347   0.2010   1.0000
  11.500   1.3343   0.02843   0.02034  -0.0317   0.1899   1.0000
  11.750   1.3453   0.02938   0.02132  -0.0302   0.1847   1.0000
  12.000   1.3550   0.03044   0.02239  -0.0286   0.1803   1.0000
  12.250   1.3676   0.03134   0.02342  -0.0274   0.1743   1.0000
  12.500   1.3767   0.03249   0.02460  -0.0260   0.1691   1.0000
  12.750   1.3862   0.03365   0.02582  -0.0247   0.1634   1.0000
  13.000   1.3963   0.03479   0.02705  -0.0235   0.1575   1.0000
  13.250   1.4025   0.03625   0.02853  -0.0222   0.1517   1.0000
  13.500   1.4133   0.03741   0.02982  -0.0212   0.1451   1.0000
  13.750   1.4183   0.03904   0.03148  -0.0200   0.1379   1.0000
  14.000   1.4241   0.04069   0.03318  -0.0190   0.1263   1.0000
  14.250   1.4276   0.04258   0.03508  -0.0179   0.1126   1.0000
  14.500   1.4246   0.04513   0.03756  -0.0168   0.0958   1.0000
  14.750   1.4175   0.04819   0.04056  -0.0158   0.0824   1.0000
  15.000   1.4084   0.05159   0.04392  -0.0149   0.0683   1.0000
  15.250   1.3945   0.05568   0.04794  -0.0143   0.0460   1.0000
  15.500   1.3774   0.06035   0.05256  -0.0140   0.0355   1.0000
  15.750   1.3650   0.06471   0.05697  -0.0140   0.0311   1.0000
  16.000   1.3558   0.06886   0.06123  -0.0143   0.0288   1.0000
  16.250   1.3443   0.07349   0.06597  -0.0149   0.0269   1.0000
  16.500   1.3348   0.07799   0.07061  -0.0157   0.0259   1.0000
  16.750   1.3245   0.08277   0.07553  -0.0167   0.0248   1.0000
  17.000   1.3122   0.08797   0.08088  -0.0181   0.0240   1.0000
  17.250   1.2993   0.09341   0.08646  -0.0196   0.0234   1.0000
  17.500   1.2827   0.09956   0.09275  -0.0216   0.0227   1.0000
  17.750   1.2671   0.10571   0.09904  -0.0238   0.0224   1.0000
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