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AIRFOIL 3024 9.84% (s3024-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: AIRFOIL 3024 9.84% (s3024-il)
Reynolds number: 100,000
Max Cl/Cd: 57.8 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s3024-il-100000.txt
Download as CSV file: xf-s3024-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AIRFOIL 3024    9.84%                           
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2552   0.09723   0.09287  -0.0364   1.0000   0.0914
  -9.000  -0.2646   0.09540   0.09112  -0.0354   1.0000   0.0940
  -8.750  -0.2822   0.09427   0.09009  -0.0345   1.0000   0.0957
  -8.500  -0.3039   0.09352   0.08944  -0.0335   1.0000   0.0965
  -8.250  -0.3287   0.09284   0.08886  -0.0325   1.0000   0.0969
  -8.000  -0.3518   0.09196   0.08808  -0.0311   1.0000   0.0971
  -7.750  -0.3189   0.08574   0.08184  -0.0268   1.0000   0.1004
  -7.500  -0.3235   0.08376   0.07991  -0.0244   1.0000   0.1028
  -7.250  -0.3343   0.08199   0.07820  -0.0225   1.0000   0.1049
  -7.000  -0.3496   0.08031   0.07660  -0.0208   1.0000   0.1068
  -6.750  -0.4350   0.08603   0.08207  -0.0232   1.0000   0.1008
  -6.500  -0.4397   0.08396   0.08003  -0.0215   1.0000   0.1029
  -6.250  -0.4467   0.08156   0.07768  -0.0212   1.0000   0.1062
  -6.000  -0.4645   0.07838   0.07421  -0.0331   1.0000   0.1117
  -5.750  -0.4588   0.07444   0.07049  -0.0276   1.0000   0.1132
  -5.500  -0.4547   0.07221   0.06832  -0.0242   1.0000   0.1157
  -5.250  -0.4504   0.06955   0.06563  -0.0240   1.0000   0.1208
  -5.000  -0.4234   0.06435   0.06029  -0.0313   0.9949   0.1300
  -4.750  -0.3939   0.05984   0.05556  -0.0379   0.9887   0.1430
  -4.500  -0.3628   0.05607   0.05160  -0.0429   0.9831   0.1574
  -4.250  -0.3357   0.05276   0.04816  -0.0458   0.9768   0.1723
  -4.000  -0.2780   0.03975   0.03355  -0.0548   0.9736   0.0814
  -3.750  -0.2443   0.03446   0.02754  -0.0563   0.9689   0.0655
  -3.500  -0.2096   0.03166   0.02418  -0.0579   0.9635   0.0647
  -3.250  -0.1682   0.02927   0.02121  -0.0603   0.9594   0.0643
  -3.000  -0.1383   0.02744   0.01894  -0.0603   0.9527   0.0640
  -2.750  -0.0992   0.02596   0.01711  -0.0620   0.9476   0.0658
  -2.500  -0.0654   0.02501   0.01589  -0.0628   0.9412   0.0696
  -2.250  -0.0312   0.02396   0.01491  -0.0640   0.9348   0.0826
  -2.000   0.0058   0.02263   0.01384  -0.0656   0.9296   0.1241
  -1.750   0.0305   0.02085   0.01345  -0.0656   0.9222   0.3674
  -1.500   0.0936   0.01916   0.01343  -0.0708   0.9202   1.0000
  -1.250   0.1278   0.01945   0.01334  -0.0723   0.9122   1.0000
  -1.000   0.1655   0.01969   0.01327  -0.0743   0.9045   1.0000
  -0.750   0.1947   0.01996   0.01332  -0.0748   0.8953   1.0000
  -0.500   0.2381   0.02014   0.01325  -0.0778   0.8888   1.0000
  -0.250   0.2638   0.02040   0.01335  -0.0776   0.8784   1.0000
   0.000   0.3131   0.02045   0.01323  -0.0814   0.8731   1.0000
   0.250   0.3363   0.02071   0.01337  -0.0807   0.8620   1.0000
   0.500   0.3877   0.02059   0.01312  -0.0846   0.8575   1.0000
   0.750   0.4093   0.02082   0.01328  -0.0835   0.8456   1.0000
   1.000   0.4373   0.02095   0.01334  -0.0833   0.8352   1.0000
   1.250   0.4798   0.02071   0.01303  -0.0853   0.8292   1.0000
   1.500   0.5039   0.02083   0.01311  -0.0844   0.8175   1.0000
   1.750   0.5345   0.02076   0.01301  -0.0843   0.8080   1.0000
   2.000   0.5712   0.02042   0.01264  -0.0850   0.8004   1.0000
   2.250   0.5962   0.02043   0.01264  -0.0840   0.7887   1.0000
   2.500   0.6260   0.02024   0.01245  -0.0836   0.7789   1.0000
   2.750   0.6602   0.01979   0.01200  -0.0836   0.7707   1.0000
   3.000   0.6856   0.01970   0.01192  -0.0826   0.7584   1.0000
   3.250   0.7128   0.01951   0.01175  -0.0817   0.7468   1.0000
   3.500   0.7433   0.01913   0.01140  -0.0811   0.7363   1.0000
   3.750   0.7750   0.01864   0.01092  -0.0806   0.7259   1.0000
   4.000   0.8016   0.01842   0.01073  -0.0796   0.7121   1.0000
   4.250   0.8287   0.01817   0.01053  -0.0786   0.6979   1.0000
   4.500   0.8562   0.01791   0.01028  -0.0776   0.6829   1.0000
   4.750   0.8838   0.01766   0.01003  -0.0767   0.6670   1.0000
   5.000   0.9072   0.01764   0.01006  -0.0753   0.6472   1.0000
   5.250   0.9332   0.01752   0.00997  -0.0742   0.6277   1.0000
   5.500   0.9594   0.01744   0.00986  -0.0732   0.6072   1.0000
   5.750   0.9830   0.01752   0.00995  -0.0719   0.5835   1.0000
   6.000   1.0064   0.01767   0.01010  -0.0706   0.5589   1.0000
   6.250   1.0297   0.01788   0.01025  -0.0693   0.5334   1.0000
   6.500   1.0520   0.01820   0.01049  -0.0680   0.5067   1.0000
   6.750   1.0724   0.01861   0.01087  -0.0665   0.4785   1.0000
   7.000   1.0922   0.01910   0.01134  -0.0649   0.4502   1.0000
   7.250   1.1112   0.01965   0.01184  -0.0633   0.4219   1.0000
   7.500   1.1295   0.02028   0.01242  -0.0616   0.3940   1.0000
   7.750   1.1470   0.02098   0.01306  -0.0599   0.3664   1.0000
   8.000   1.1636   0.02174   0.01378  -0.0581   0.3396   1.0000
   8.250   1.1796   0.02258   0.01453  -0.0563   0.3138   1.0000
   8.500   1.1944   0.02346   0.01535  -0.0544   0.2885   1.0000
   8.750   1.2070   0.02435   0.01625  -0.0522   0.2632   1.0000
   9.000   1.2170   0.02524   0.01711  -0.0498   0.2385   1.0000
   9.250   1.2246   0.02616   0.01795  -0.0471   0.2152   1.0000
   9.500   1.2294   0.02704   0.01890  -0.0441   0.1920   1.0000
   9.750   1.2317   0.02806   0.01987  -0.0409   0.1713   1.0000
  10.000   1.2347   0.02925   0.02110  -0.0380   0.1505   1.0000
  10.250   1.2354   0.03078   0.02258  -0.0352   0.1295   1.0000
  10.500   1.2309   0.03282   0.02451  -0.0321   0.1041   1.0000
  10.750   1.2227   0.03547   0.02696  -0.0292   0.0817   1.0000
  11.000   1.2197   0.03813   0.02959  -0.0266   0.0660   1.0000
  11.250   1.2202   0.04075   0.03206  -0.0246   0.0585   1.0000
  11.500   1.2297   0.04291   0.03445  -0.0229   0.0532   1.0000
  11.750   1.2409   0.04512   0.03663  -0.0215   0.0495   1.0000
  12.000   1.2614   0.04780   0.03941  -0.0205   0.0466   1.0000
  12.250   1.2719   0.05024   0.04212  -0.0192   0.0443   1.0000
  12.500   1.2782   0.05278   0.04487  -0.0180   0.0421   1.0000
  12.750   1.2858   0.05544   0.04765  -0.0170   0.0404   1.0000
  13.000   1.2965   0.05875   0.05113  -0.0162   0.0394   1.0000
  13.250   1.3018   0.06301   0.05563  -0.0154   0.0387   1.0000
  13.500   1.2967   0.06747   0.06038  -0.0145   0.0385   1.0000
  13.750   1.2861   0.07171   0.06492  -0.0138   0.0385   1.0000
  14.000   1.2719   0.07619   0.06968  -0.0135   0.0385   1.0000
  14.250   1.2557   0.08071   0.07451  -0.0138   0.0386   1.0000
  14.500   1.2367   0.08570   0.07977  -0.0149   0.0388   1.0000
  14.750   1.2142   0.09135   0.08568  -0.0169   0.0391   1.0000
  15.000   1.1862   0.09831   0.09293  -0.0204   0.0395   1.0000
  15.250   1.1474   0.10817   0.10314  -0.0265   0.0404   1.0000
  15.500   1.0777   0.12709   0.12243  -0.0404   0.0428   1.0000
  15.750   1.0265   0.14630   0.14171  -0.0530   0.0460   1.0000
  16.000   1.0112   0.15667   0.15202  -0.0585   0.0473   1.0000
  16.250   1.0029   0.16532   0.16064  -0.0627   0.0479   1.0000
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