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CHEN AIRFOIL (chen-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: CHEN AIRFOIL (chen-il)
Reynolds number: 1,000,000
Max Cl/Cd: 123 at α=13°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-chen-il-1000000-n5.txt
Download as CSV file: xf-chen-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: CHEN AIRFOIL                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.0278   0.09943   0.09489  -0.0551   0.3150   0.0084
  -9.250  -0.0213   0.09604   0.09150  -0.0568   0.3149   0.0078
  -9.000  -0.0143   0.09295   0.08842  -0.0584   0.3146   0.0076
  -8.750  -0.0013   0.09112   0.08660  -0.0597   0.3144   0.0087
  -8.500   0.0067   0.08833   0.08381  -0.0612   0.3143   0.0088
  -8.250   0.0142   0.08551   0.08100  -0.0627   0.3143   0.0086
  -8.000   0.0221   0.08290   0.07840  -0.0642   0.3141   0.0089
  -7.750   0.0282   0.08001   0.07553  -0.0659   0.3141   0.0088
  -7.500   0.0343   0.07744   0.07298  -0.0673   0.3139   0.0086
  -7.250   0.0351   0.07436   0.06992  -0.0692   0.3139   0.0091
  -7.000   0.0358   0.07196   0.06754  -0.0695   0.3138   0.0091
  -6.750   0.0306   0.06967   0.06527  -0.0684   0.3137   0.0092
  -6.500   0.0353   0.06751   0.06311  -0.0684   0.3137   0.0091
  -6.250   0.0351   0.06433   0.05993  -0.0683   0.3136   0.0092
  -6.000   0.0384   0.06152   0.05710  -0.0679   0.3136   0.0092
  -5.750   0.0461   0.05931   0.05486  -0.0673   0.3135   0.0092
  -5.500   0.0441   0.05491   0.05042  -0.0661   0.3135   0.0097
  -5.250   0.0518   0.05228   0.04773  -0.0649   0.3135   0.0097
  -5.000   0.0693   0.05149   0.04693  -0.0643   0.3133   0.0100
  -4.750   0.0821   0.04961   0.04500  -0.0632   0.3132   0.0102
  -4.500   0.0944   0.04752   0.04286  -0.0618   0.3133   0.0103
  -4.250   0.1087   0.04572   0.04101  -0.0605   0.3131   0.0106
  -3.750   0.0302   0.02045   0.01404  -0.0363   0.3132   0.0136
  -3.500   0.0487   0.01727   0.01049  -0.0345   0.3132   0.0139
  -3.250   0.0764   0.01600   0.00908  -0.0344   0.3130   0.0142
  -3.000   0.1039   0.01539   0.00835  -0.0341   0.3129   0.0144
  -2.750   0.1314   0.01498   0.00787  -0.0338   0.3128   0.0147
  -2.500   0.1591   0.01463   0.00744  -0.0336   0.3128   0.0150
  -2.250   0.1865   0.01439   0.00714  -0.0332   0.3127   0.0153
  -2.000   0.2139   0.01419   0.00689  -0.0329   0.3126   0.0157
  -1.750   0.2416   0.01390   0.00656  -0.0326   0.3125   0.0161
  -1.500   0.2690   0.01371   0.00634  -0.0323   0.3124   0.0164
  -1.250   0.2962   0.01355   0.00616  -0.0319   0.3123   0.0172
  -1.000   0.3230   0.01345   0.00604  -0.0315   0.3122   0.0177
  -0.750   0.3494   0.01337   0.00594  -0.0310   0.3122   0.0183
  -0.500   0.3756   0.01330   0.00585  -0.0304   0.3121   0.0189
  -0.250   0.4015   0.01324   0.00577  -0.0297   0.3120   0.0195
   0.000   0.4269   0.01316   0.00570  -0.0290   0.3120   0.0211
   0.250   0.4521   0.01314   0.00567  -0.0283   0.3118   0.0223
   0.500   0.4771   0.01313   0.00566  -0.0274   0.3118   0.0239
   0.750   0.5018   0.01314   0.00569  -0.0266   0.3117   0.0264
   1.000   0.5265   0.01315   0.00572  -0.0258   0.3116   0.0307
   1.250   0.5512   0.01320   0.00578  -0.0249   0.3116   0.0345
   1.500   0.5759   0.01327   0.00587  -0.0241   0.3115   0.0385
   1.750   0.6006   0.01333   0.00593  -0.0233   0.3114   0.0416
   2.000   0.6253   0.01339   0.00601  -0.0225   0.3113   0.0448
   2.250   0.6500   0.01349   0.00612  -0.0218   0.3112   0.0472
   2.500   0.6746   0.01358   0.00622  -0.0210   0.3112   0.0501
   2.750   0.6993   0.01368   0.00635  -0.0203   0.3111   0.0537
   3.000   0.7240   0.01380   0.00648  -0.0195   0.3110   0.0566
   3.250   0.7487   0.01390   0.00663  -0.0188   0.3109   0.0629
   3.500   0.7735   0.01403   0.00677  -0.0181   0.3108   0.0660
   3.750   0.7981   0.01416   0.00691  -0.0174   0.3107   0.0694
   4.000   0.8226   0.01431   0.00709  -0.0167   0.3106   0.0730
   4.250   0.8472   0.01444   0.00724  -0.0160   0.3105   0.0762
   4.500   0.8717   0.01460   0.00742  -0.0154   0.3104   0.0781
   4.750   0.8961   0.01473   0.00758  -0.0147   0.3103   0.0819
   5.000   0.9204   0.01490   0.00777  -0.0140   0.3102   0.0853
   5.250   0.9447   0.01505   0.00795  -0.0133   0.3101   0.0881
   5.500   0.9688   0.01524   0.00817  -0.0127   0.3100   0.0908
   5.750   0.9930   0.01542   0.00838  -0.0120   0.3099   0.0954
   6.000   1.0170   0.01558   0.00858  -0.0114   0.3098   0.1009
   6.500   1.0653   0.01586   0.00898  -0.0101   0.3094   0.1289
   6.750   1.0893   0.01602   0.00917  -0.0095   0.3092   0.1405
   7.000   1.1130   0.01622   0.00942  -0.0088   0.3091   0.1494
   7.250   1.1368   0.01640   0.00964  -0.0082   0.3089   0.1569
   7.500   1.1604   0.01660   0.00987  -0.0076   0.3087   0.1630
   7.750   1.1840   0.01679   0.01012  -0.0070   0.3086   0.1711
   8.250   1.2323   0.01697   0.01039  -0.0059   0.3080   0.2048
   8.750   1.3687   0.01550   0.01032  -0.0242   0.3063   0.9745
   9.250   1.4284   0.01576   0.01059  -0.0256   0.3044   0.9832
   9.500   1.4710   0.01597   0.01083  -0.0292   0.3042   0.9847
   9.750   1.5057   0.01617   0.01109  -0.0311   0.3040   0.9857
  10.000   1.5378   0.01597   0.01093  -0.0322   0.3030   0.9867
  10.250   1.5664   0.01624   0.01126  -0.0329   0.3028   0.9877
  10.500   1.5942   0.01622   0.01129  -0.0333   0.3019   0.9885
  10.750   1.6250   0.01624   0.01135  -0.0343   0.3009   0.9900
  11.000   1.6532   0.01613   0.01129  -0.0347   0.2996   0.9910
  11.250   1.6786   0.01662   0.01185  -0.0349   0.2999   0.9924
  11.500   1.7050   0.01653   0.01180  -0.0349   0.2987   0.9935
  11.750   1.7350   0.01642   0.01172  -0.0358   0.2976   0.9944
  12.000   1.7681   0.01553   0.01078  -0.0366   0.2947   0.9949
  12.250   1.8006   0.01511   0.01036  -0.0378   0.2926   0.9958
  12.500   1.8272   0.01543   0.01082  -0.0383   0.2873   0.9965
  12.750   1.8610   0.01544   0.01089  -0.0401   0.2826   0.9978
  13.000   1.8880   0.01535   0.01083  -0.0404   0.2783   0.9983
  13.250   1.8782   0.01740   0.01232  -0.0358   0.2097   1.0000
  13.500   1.8051   0.02087   0.01568  -0.0204   0.1745   1.0000
  13.750   1.8063   0.02154   0.01642  -0.0167   0.1737   1.0000
  14.000   1.7438   0.02568   0.02065  -0.0075   0.1604   1.0000
  14.250   1.7546   0.02639   0.02149  -0.0065   0.1647   1.0000
  14.500   1.7380   0.03009   0.02541  -0.0064   0.1697   1.0000
  14.750   1.6261   0.04712   0.04311  -0.0105   0.1932   1.0000
  15.250   1.4638   0.06912   0.06560  -0.0124   0.2099   1.0000
  15.500   1.4691   0.07092   0.06749  -0.0124   0.2141   1.0000
  15.750   1.3690   0.08547   0.08186  -0.0152   0.1875   1.0000
  16.000   1.3697   0.08794   0.08435  -0.0153   0.1845   1.0000
  16.250   1.3503   0.09299   0.08930  -0.0162   0.1716   1.0000
  16.500   1.3372   0.09735   0.09361  -0.0169   0.1619   1.0000
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