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CURTISS CR-1 AIRFOIL (cr1-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: CURTISS CR-1 AIRFOIL (cr1-il)
Reynolds number: 200,000
Max Cl/Cd: 79.14 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-cr1-il-200000.txt
Download as CSV file: xf-cr1-il-200000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.2863   0.11715   0.11363  -0.0392   1.0000   0.0722
 -10.250  -0.3168   0.11737   0.11397  -0.0366   1.0000   0.0739
 -10.000  -0.3310   0.11325   0.10988  -0.0480   0.9948   0.0748
  -9.750  -0.3015   0.10793   0.10453  -0.0461   0.9937   0.0758
  -9.500  -0.2728   0.10478   0.10135  -0.0465   0.9910   0.0775
  -9.250  -0.2521   0.10136   0.09792  -0.0499   0.9868   0.0798
  -9.000  -0.2355   0.09731   0.09385  -0.0559   0.9829   0.0833
  -8.750  -0.2519   0.09049   0.08706  -0.0762   0.9699   0.0862
  -8.500  -0.2209   0.08647   0.08301  -0.0725   0.9698   0.0873
  -8.250  -0.1941   0.08407   0.08059  -0.0720   0.9655   0.0888
  -8.000  -0.1721   0.08108   0.07758  -0.0748   0.9604   0.0912
  -7.750  -0.1524   0.07691   0.07338  -0.0817   0.9561   0.0948
  -7.250  -0.1904   0.04655   0.04240  -0.1146   0.9266   0.0743
  -7.000  -0.1892   0.04069   0.03627  -0.1156   0.9171   0.0736
  -6.750  -0.1917   0.03309   0.02800  -0.1161   0.9093   0.0730
  -6.500  -0.1917   0.02907   0.02338  -0.1133   0.8995   0.0734
  -6.250  -0.1749   0.02633   0.02004  -0.1123   0.8941   0.0745
  -6.000  -0.1528   0.02449   0.01799  -0.1120   0.8897   0.0765
  -5.750  -0.1344   0.02411   0.01759  -0.1104   0.8822   0.0784
  -5.500  -0.1079   0.02319   0.01650  -0.1102   0.8779   0.0808
  -5.250  -0.0800   0.02197   0.01497  -0.1102   0.8748   0.0837
  -5.000  -0.0652   0.02143   0.01415  -0.1077   0.8669   0.0859
  -4.750  -0.0394   0.02046   0.01319  -0.1074   0.8624   0.0895
  -4.500  -0.0096   0.02004   0.01268  -0.1076   0.8592   0.0943
  -4.250   0.0106   0.01980   0.01220  -0.1059   0.8530   0.0986
  -4.000   0.0344   0.01906   0.01152  -0.1053   0.8478   0.1038
  -3.750   0.0635   0.01871   0.01104  -0.1052   0.8440   0.1107
  -3.500   0.0922   0.01821   0.01052  -0.1052   0.8406   0.1180
  -3.250   0.1109   0.01818   0.01045  -0.1034   0.8335   0.1246
  -3.000   0.1387   0.01771   0.00995  -0.1032   0.8290   0.1316
  -2.750   0.1700   0.01748   0.00964  -0.1035   0.8255   0.1400
  -2.500   0.1899   0.01732   0.00950  -0.1020   0.8184   0.1465
  -2.250   0.2175   0.01718   0.00933  -0.1016   0.8131   0.1547
  -2.000   0.2489   0.01680   0.00891  -0.1019   0.8093   0.1626
  -1.750   0.2700   0.01679   0.00891  -0.1005   0.8022   0.1696
  -1.500   0.2979   0.01647   0.00855  -0.1001   0.7967   0.1772
  -1.250   0.3297   0.01617   0.00823  -0.1005   0.7926   0.1857
  -1.000   0.3507   0.01607   0.00813  -0.0990   0.7850   0.1933
  -0.750   0.3792   0.01581   0.00788  -0.0988   0.7795   0.2029
  -0.500   0.4093   0.01549   0.00756  -0.0989   0.7747   0.2134
  -0.250   0.4310   0.01542   0.00751  -0.0975   0.7670   0.2251
   0.000   0.4605   0.01513   0.00722  -0.0974   0.7616   0.2396
   0.250   0.4850   0.01494   0.00712  -0.0966   0.7549   0.2550
   0.500   0.5105   0.01473   0.00696  -0.0958   0.7478   0.2729
   0.750   0.5407   0.01440   0.00668  -0.0959   0.7423   0.2940
   1.000   0.5606   0.01425   0.00668  -0.0942   0.7333   0.3146
   1.250   0.5898   0.01387   0.00639  -0.0941   0.7268   0.3489
   1.500   0.6058   0.01341   0.00639  -0.0916   0.7167   0.4494
   1.750   0.7595   0.01202   0.00601  -0.1174   0.7038   1.0000
   2.000   0.7844   0.01202   0.00590  -0.1164   0.6949   1.0000
   2.250   0.8056   0.01209   0.00593  -0.1148   0.6846   1.0000
   2.500   0.8314   0.01208   0.00581  -0.1140   0.6758   1.0000
   2.750   0.8513   0.01213   0.00584  -0.1122   0.6639   1.0000
   3.000   0.8729   0.01216   0.00584  -0.1107   0.6524   1.0000
   3.250   0.8955   0.01217   0.00579  -0.1093   0.6406   1.0000
   3.500   0.9172   0.01220   0.00576  -0.1078   0.6277   1.0000
   3.750   0.9372   0.01226   0.00579  -0.1060   0.6127   1.0000
   4.000   0.9574   0.01233   0.00581  -0.1042   0.5964   1.0000
   4.250   0.9771   0.01243   0.00583  -0.1023   0.5787   1.0000
   4.500   0.9953   0.01259   0.00592  -0.1002   0.5583   1.0000
   4.750   1.0130   0.01280   0.00602  -0.0980   0.5365   1.0000
   5.000   1.0297   0.01308   0.00615  -0.0956   0.5141   1.0000
   5.250   1.0452   0.01341   0.00636  -0.0931   0.4907   1.0000
   5.500   1.0599   0.01381   0.00661  -0.0905   0.4686   1.0000
   5.750   1.0742   0.01424   0.00691  -0.0878   0.4476   1.0000
   6.000   1.0881   0.01468   0.00724  -0.0851   0.4279   1.0000
   6.250   1.1015   0.01514   0.00760  -0.0824   0.4096   1.0000
   6.500   1.1147   0.01562   0.00798  -0.0797   0.3929   1.0000
   6.750   1.1276   0.01611   0.00839  -0.0769   0.3771   1.0000
   7.000   1.1403   0.01662   0.00882  -0.0742   0.3626   1.0000
   7.250   1.1522   0.01715   0.00926  -0.0713   0.3496   1.0000
   7.500   1.1633   0.01768   0.00969  -0.0683   0.3378   1.0000
   7.750   1.1752   0.01815   0.01017  -0.0654   0.3265   1.0000
   8.000   1.1885   0.01871   0.01066  -0.0629   0.3167   1.0000
   8.250   1.2018   0.01924   0.01115  -0.0605   0.3073   1.0000
   8.500   1.2164   0.01978   0.01168  -0.0584   0.2988   1.0000
   8.750   1.2309   0.02034   0.01219  -0.0563   0.2909   1.0000
   9.000   1.2462   0.02090   0.01277  -0.0543   0.2834   1.0000
   9.250   1.2613   0.02145   0.01332  -0.0524   0.2766   1.0000
   9.500   1.2798   0.02208   0.01390  -0.0511   0.2708   1.0000
   9.750   1.2953   0.02262   0.01454  -0.0493   0.2652   1.0000
  10.000   1.3124   0.02321   0.01511  -0.0479   0.2600   1.0000
  10.250   1.3293   0.02385   0.01576  -0.0464   0.2545   1.0000
  10.500   1.3414   0.02442   0.01642  -0.0443   0.2489   1.0000
  10.750   1.3561   0.02506   0.01702  -0.0427   0.2431   1.0000
  11.000   1.3677   0.02574   0.01779  -0.0406   0.2375   1.0000
  11.250   1.3784   0.02640   0.01853  -0.0386   0.2320   1.0000
  11.500   1.3942   0.02712   0.01917  -0.0372   0.2264   1.0000
  11.750   1.4021   0.02789   0.02012  -0.0350   0.2215   1.0000
  12.000   1.4118   0.02867   0.02098  -0.0331   0.2164   1.0000
  12.250   1.4257   0.02948   0.02171  -0.0317   0.2109   1.0000
  12.500   1.4316   0.03043   0.02286  -0.0295   0.2062   1.0000
  12.750   1.4382   0.03141   0.02393  -0.0276   0.2006   1.0000
  13.000   1.4504   0.03234   0.02480  -0.0262   0.1957   1.0000
  13.250   1.4545   0.03352   0.02621  -0.0243   0.1907   1.0000
  13.500   1.4596   0.03475   0.02753  -0.0227   0.1851   1.0000
  13.750   1.4648   0.03607   0.02887  -0.0211   0.1794   1.0000
  14.000   1.4676   0.03757   0.03056  -0.0196   0.1727   1.0000
  14.250   1.4699   0.03922   0.03219  -0.0182   0.1665   1.0000
  14.500   1.4727   0.04094   0.03414  -0.0171   0.1584   1.0000
  14.750   1.4725   0.04302   0.03629  -0.0160   0.1491   1.0000
  15.000   1.4711   0.04539   0.03876  -0.0152   0.1342   1.0000
  15.250   1.4645   0.04844   0.04176  -0.0144   0.1095   1.0000
  15.500   1.4451   0.05294   0.04605  -0.0137   0.0852   1.0000
  15.750   1.4256   0.05773   0.05076  -0.0131   0.0674   1.0000
  16.000   1.4086   0.06250   0.05550  -0.0130   0.0529   1.0000
  16.250   1.3906   0.06764   0.06063  -0.0133   0.0458   1.0000
  16.500   1.3757   0.07267   0.06573  -0.0139   0.0426   1.0000
  16.750   1.3600   0.07799   0.07116  -0.0149   0.0404   1.0000
  17.000   1.3435   0.08365   0.07694  -0.0162   0.0389   1.0000
  17.250   1.3263   0.08961   0.08302  -0.0178   0.0380   1.0000
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