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cr001sm (cr001sm-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: cr001sm (cr001sm-il)
Reynolds number: 100,000
Max Cl/Cd: 64.83 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-cr001sm-il-100000.txt
Download as CSV file: xf-cr001sm-il-100000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3535   0.09932   0.09453  -0.0291   1.0000   0.0672
  -7.500  -0.3685   0.09876   0.09410  -0.0285   1.0000   0.0680
  -7.250  -0.3779   0.09750   0.09297  -0.0297   1.0000   0.0684
  -7.000  -0.3826   0.09587   0.09142  -0.0339   1.0000   0.0687
  -6.750  -0.3718   0.08997   0.08552  -0.0244   1.0000   0.0721
  -6.500  -0.3715   0.08762   0.08323  -0.0229   1.0000   0.0748
  -6.250  -0.3733   0.08537   0.08104  -0.0227   1.0000   0.0770
  -6.000  -0.3746   0.08303   0.07876  -0.0248   1.0000   0.0802
  -5.750  -0.3615   0.08048   0.07606  -0.0415   1.0000   0.0828
  -5.500  -0.3667   0.07632   0.07210  -0.0324   1.0000   0.0842
  -5.250  -0.3649   0.07386   0.06970  -0.0281   1.0000   0.0868
  -5.000  -0.3576   0.07117   0.06702  -0.0286   1.0000   0.0907
  -4.750  -0.3323   0.06627   0.06195  -0.0404   1.0000   0.0979
  -4.500  -0.3304   0.06387   0.05965  -0.0359   1.0000   0.1004
  -4.250  -0.2996   0.05967   0.05519  -0.0453   1.0000   0.1119
  -4.000  -0.2961   0.05722   0.05288  -0.0413   1.0000   0.1147
  -3.750  -0.2702   0.05361   0.04907  -0.0463   1.0000   0.1272
  -3.500  -0.2470   0.05067   0.04599  -0.0493   1.0000   0.1408
  -3.250  -0.2356   0.04853   0.04393  -0.0473   1.0000   0.1479
  -3.000  -0.2078   0.04559   0.04080  -0.0512   1.0000   0.1702
  -2.750  -0.1903   0.04349   0.03872  -0.0509   1.0000   0.1871
  -2.500  -0.1718   0.04171   0.03694  -0.0509   1.0000   0.2161
  -2.000  -0.0313   0.02842   0.02089  -0.0677   0.9965   0.0814
  -1.750   0.0137   0.02558   0.01749  -0.0706   0.9918   0.0734
  -1.500   0.0587   0.02408   0.01555  -0.0736   0.9862   0.0742
  -1.250   0.0999   0.02301   0.01422  -0.0759   0.9790   0.0785
  -1.000   0.1447   0.02211   0.01308  -0.0787   0.9732   0.0822
  -0.750   0.1821   0.02125   0.01229  -0.0806   0.9647   0.0948
  -0.500   0.2274   0.02051   0.01166  -0.0839   0.9588   0.1207
  -0.250   0.2664   0.01765   0.01127  -0.0856   0.9525   1.0000
   0.000   0.3136   0.01795   0.01117  -0.0895   0.9448   1.0000
   0.250   0.3520   0.01813   0.01112  -0.0917   0.9338   1.0000
   0.500   0.3900   0.01830   0.01110  -0.0938   0.9229   1.0000
   0.750   0.4307   0.01841   0.01106  -0.0963   0.9130   1.0000
   1.000   0.4770   0.01840   0.01092  -0.0997   0.9048   1.0000
   1.250   0.5136   0.01841   0.01086  -0.1012   0.8931   1.0000
   1.500   0.5522   0.01835   0.01075  -0.1031   0.8820   1.0000
   1.750   0.6057   0.01794   0.01032  -0.1073   0.8761   1.0000
   2.000   0.6432   0.01773   0.01010  -0.1086   0.8638   1.0000
   2.250   0.6811   0.01744   0.00983  -0.1098   0.8514   1.0000
   2.500   0.7194   0.01707   0.00947  -0.1109   0.8386   1.0000
   2.750   0.7568   0.01668   0.00911  -0.1117   0.8251   1.0000
   3.000   0.7926   0.01631   0.00880  -0.1122   0.8104   1.0000
   3.250   0.8271   0.01599   0.00851  -0.1124   0.7948   1.0000
   3.500   0.8608   0.01571   0.00824  -0.1125   0.7782   1.0000
   3.750   0.8875   0.01568   0.00823  -0.1115   0.7575   1.0000
   4.000   0.9175   0.01556   0.00816  -0.1109   0.7374   1.0000
   4.250   0.9437   0.01559   0.00822  -0.1099   0.7146   1.0000
   4.500   0.9711   0.01562   0.00822  -0.1089   0.6912   1.0000
   4.750   0.9966   0.01573   0.00832  -0.1077   0.6656   1.0000
   5.000   1.0206   0.01591   0.00852  -0.1063   0.6376   1.0000
   5.250   1.0438   0.01614   0.00872  -0.1048   0.6076   1.0000
   5.500   1.0651   0.01643   0.00901  -0.1030   0.5741   1.0000
   5.750   1.0862   0.01679   0.00928  -0.1011   0.5385   1.0000
   6.000   1.1054   0.01723   0.00965  -0.0991   0.4988   1.0000
   6.250   1.1235   0.01777   0.01011  -0.0969   0.4564   1.0000
   6.500   1.1405   0.01842   0.01061  -0.0946   0.4126   1.0000
   6.750   1.1565   0.01920   0.01121  -0.0923   0.3690   1.0000
   7.000   1.1719   0.02007   0.01192  -0.0901   0.3270   1.0000
   7.250   1.1867   0.02103   0.01273  -0.0878   0.2871   1.0000
   7.500   1.2006   0.02208   0.01364  -0.0856   0.2489   1.0000
   7.750   1.2129   0.02328   0.01468  -0.0832   0.2123   1.0000
   8.000   1.2236   0.02460   0.01586  -0.0806   0.1737   1.0000
   8.250   1.2326   0.02618   0.01726  -0.0778   0.1353   1.0000
   8.500   1.2401   0.02808   0.01890  -0.0749   0.1058   1.0000
   8.750   1.2515   0.03007   0.02088  -0.0723   0.0854   1.0000
   9.000   1.2643   0.03204   0.02281  -0.0702   0.0721   1.0000
   9.250   1.2826   0.03452   0.02533  -0.0688   0.0635   1.0000
   9.500   1.3048   0.03718   0.02801  -0.0681   0.0572   1.0000
   9.750   1.3245   0.04005   0.03121  -0.0668   0.0523   1.0000
  10.000   1.3401   0.04245   0.03386  -0.0652   0.0483   1.0000
  10.250   1.3589   0.04599   0.03756  -0.0643   0.0459   1.0000
  10.500   1.3727   0.05176   0.04370  -0.0633   0.0446   1.0000
  10.750   1.3719   0.05485   0.04726  -0.0599   0.0440   1.0000
  11.000   1.3655   0.05777   0.05066  -0.0561   0.0433   1.0000
  11.250   1.3544   0.06086   0.05414  -0.0521   0.0428   1.0000
  11.500   1.3393   0.06403   0.05765  -0.0481   0.0424   1.0000
  11.750   1.3216   0.06753   0.06146  -0.0449   0.0421   1.0000
  12.000   1.3027   0.07151   0.06572  -0.0427   0.0422   1.0000
  12.250   1.2820   0.07596   0.07043  -0.0414   0.0423   1.0000
  12.500   1.2603   0.08095   0.07565  -0.0412   0.0425   1.0000
  12.750   1.2381   0.08656   0.08146  -0.0422   0.0429   1.0000
  13.000   1.2156   0.09279   0.08788  -0.0443   0.0433   1.0000
  13.250   1.1942   0.09967   0.09490  -0.0473   0.0438   1.0000
  13.500   1.1748   0.10713   0.10246  -0.0508   0.0443   1.0000
  13.750   1.1568   0.11450   0.10999  -0.0551   0.0449   1.0000
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