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AIRFOIL 3024 9.84% (s3024-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: AIRFOIL 3024 9.84% (s3024-il)
Reynolds number: 500,000
Max Cl/Cd: 110.05 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s3024-il-500000.txt
Download as CSV file: xf-s3024-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3309   0.09405   0.09186  -0.0392   1.0000   0.0180
  -9.000  -0.3308   0.09099   0.08884  -0.0401   1.0000   0.0187
  -8.750  -0.3359   0.08857   0.08648  -0.0397   0.9993   0.0188
  -8.500  -0.3222   0.08380   0.08171  -0.0453   0.9906   0.0193
  -8.250  -0.3050   0.07597   0.07388  -0.0577   0.9836   0.0206
  -8.000  -0.2868   0.06918   0.06708  -0.0686   0.9742   0.0207
  -7.750  -0.2728   0.06137   0.05921  -0.0804   0.9608   0.0207
  -7.500  -0.2796   0.05561   0.05339  -0.0834   0.9471   0.0214
  -7.250  -0.2739   0.05274   0.05045  -0.0843   0.9364   0.0217
  -7.000  -0.2668   0.04959   0.04719  -0.0852   0.9274   0.0220
  -6.750  -0.2578   0.04657   0.04406  -0.0859   0.9189   0.0226
  -6.500  -0.2472   0.04291   0.04024  -0.0868   0.9111   0.0233
  -6.250  -0.2354   0.03861   0.03568  -0.0874   0.9039   0.0251
  -6.000  -0.2275   0.01719   0.01385  -0.0811   0.8817   0.0278
  -5.750  -0.2094   0.01525   0.01189  -0.0809   0.8765   0.0286
  -5.500  -0.1908   0.01361   0.01013  -0.0805   0.8719   0.0298
  -5.250  -0.1699   0.01169   0.00798  -0.0804   0.8662   0.0324
  -5.000  -0.1521   0.01799   0.01272  -0.0833   0.8742   0.0189
  -4.750  -0.1274   0.01640   0.01086  -0.0826   0.8693   0.0189
  -4.500  -0.1020   0.01502   0.00924  -0.0820   0.8639   0.0189
  -4.250  -0.0767   0.01361   0.00759  -0.0812   0.8595   0.0182
  -4.000  -0.0509   0.01262   0.00647  -0.0805   0.8547   0.0180
  -3.750  -0.0249   0.01187   0.00563  -0.0800   0.8492   0.0183
  -3.500   0.0012   0.01127   0.00494  -0.0795   0.8446   0.0190
  -3.250   0.0277   0.01079   0.00439  -0.0791   0.8395   0.0199
  -3.000   0.0545   0.01037   0.00391  -0.0788   0.8339   0.0209
  -2.750   0.0809   0.00989   0.00335  -0.0783   0.8291   0.0234
  -2.500   0.1082   0.00962   0.00306  -0.0781   0.8234   0.0280
  -2.250   0.1343   0.00898   0.00267  -0.0777   0.8176   0.0874
  -2.000   0.1607   0.00860   0.00249  -0.0775   0.8127   0.1598
  -1.750   0.1871   0.00822   0.00238  -0.0774   0.8060   0.2437
  -1.500   0.2128   0.00776   0.00228  -0.0772   0.8003   0.3595
  -1.250   0.2376   0.00725   0.00223  -0.0767   0.7939   0.5079
  -1.000   0.2604   0.00668   0.00219  -0.0757   0.7872   0.6767
  -0.750   0.2805   0.00618   0.00221  -0.0735   0.7809   0.8430
  -0.500   0.3237   0.00603   0.00219  -0.0760   0.7740   0.9636
  -0.250   0.3738   0.00601   0.00206  -0.0807   0.7674   0.9897
   0.000   0.4181   0.00598   0.00195  -0.0842   0.7590   1.0000
   0.250   0.4431   0.00600   0.00190  -0.0836   0.7508   1.0000
   0.500   0.4683   0.00603   0.00185  -0.0830   0.7419   1.0000
   0.750   0.4936   0.00606   0.00183  -0.0824   0.7326   1.0000
   1.000   0.5190   0.00611   0.00180  -0.0818   0.7234   1.0000
   1.250   0.5444   0.00616   0.00179  -0.0813   0.7131   1.0000
   1.500   0.5699   0.00621   0.00179  -0.0807   0.7021   1.0000
   1.750   0.5954   0.00628   0.00181  -0.0802   0.6910   1.0000
   2.000   0.6208   0.00636   0.00182  -0.0796   0.6790   1.0000
   2.250   0.6461   0.00645   0.00186  -0.0791   0.6661   1.0000
   2.500   0.6715   0.00655   0.00190  -0.0785   0.6520   1.0000
   2.750   0.6968   0.00665   0.00195  -0.0780   0.6370   1.0000
   3.000   0.7221   0.00678   0.00203  -0.0775   0.6208   1.0000
   3.250   0.7472   0.00692   0.00211  -0.0769   0.6033   1.0000
   3.500   0.7723   0.00708   0.00221  -0.0764   0.5851   1.0000
   3.750   0.7970   0.00727   0.00232  -0.0758   0.5660   1.0000
   4.000   0.8218   0.00747   0.00246  -0.0752   0.5459   1.0000
   4.250   0.8463   0.00769   0.00261  -0.0746   0.5250   1.0000
   4.500   0.8706   0.00793   0.00277  -0.0740   0.5031   1.0000
   4.750   0.8948   0.00819   0.00295  -0.0734   0.4804   1.0000
   5.000   0.9187   0.00846   0.00316  -0.0727   0.4571   1.0000
   5.250   0.9421   0.00878   0.00339  -0.0720   0.4327   1.0000
   5.500   0.9656   0.00909   0.00362  -0.0713   0.4078   1.0000
   5.750   0.9887   0.00943   0.00388  -0.0706   0.3829   1.0000
   6.000   1.0112   0.00982   0.00418  -0.0698   0.3559   1.0000
   6.250   1.0329   0.01026   0.00449  -0.0689   0.3253   1.0000
   6.500   1.0539   0.01076   0.00483  -0.0679   0.2928   1.0000
   6.750   1.0750   0.01125   0.00520  -0.0670   0.2636   1.0000
   7.000   1.0961   0.01173   0.00557  -0.0660   0.2376   1.0000
   7.250   1.1169   0.01222   0.00596  -0.0651   0.2141   1.0000
   7.500   1.1373   0.01274   0.00638  -0.0640   0.1897   1.0000
   7.750   1.1573   0.01327   0.00682  -0.0630   0.1663   1.0000
   8.000   1.1765   0.01384   0.00730  -0.0618   0.1456   1.0000
   8.250   1.1949   0.01445   0.00781  -0.0605   0.1224   1.0000
   8.500   1.2115   0.01517   0.00839  -0.0590   0.0973   1.0000
   8.750   1.2258   0.01602   0.00907  -0.0571   0.0709   1.0000
   9.000   1.2330   0.01727   0.01006  -0.0542   0.0343   1.0000
   9.250   1.2400   0.01836   0.01103  -0.0511   0.0193   1.0000
   9.500   1.2524   0.01912   0.01184  -0.0489   0.0165   1.0000
   9.750   1.2649   0.01991   0.01268  -0.0468   0.0150   1.0000
  10.000   1.2761   0.02080   0.01364  -0.0446   0.0141   1.0000
  10.250   1.2844   0.02191   0.01485  -0.0422   0.0133   1.0000
  10.500   1.2935   0.02299   0.01602  -0.0400   0.0130   1.0000
  10.750   1.3029   0.02407   0.01721  -0.0380   0.0125   1.0000
  11.000   1.3104   0.02531   0.01855  -0.0360   0.0122   1.0000
  11.250   1.3173   0.02664   0.01997  -0.0340   0.0117   1.0000
  11.500   1.3231   0.02810   0.02153  -0.0321   0.0116   1.0000
  11.750   1.3288   0.02961   0.02312  -0.0304   0.0111   1.0000
  12.000   1.3331   0.03129   0.02490  -0.0287   0.0108   1.0000
  12.250   1.3351   0.03325   0.02695  -0.0271   0.0107   1.0000
  12.500   1.3352   0.03548   0.02927  -0.0256   0.0105   1.0000
  12.750   1.3347   0.03786   0.03178  -0.0242   0.0103   1.0000
  13.000   1.3339   0.04037   0.03439  -0.0230   0.0102   1.0000
  13.250   1.3314   0.04318   0.03731  -0.0219   0.0100   1.0000
  13.500   1.3287   0.04618   0.04043  -0.0209   0.0099   1.0000
  13.750   1.3259   0.04934   0.04371  -0.0200   0.0098   1.0000
  14.000   1.3276   0.05202   0.04652  -0.0195   0.0097   1.0000
  14.250   1.3287   0.05484   0.04947  -0.0193   0.0097   1.0000
  14.500   1.3290   0.05786   0.05262  -0.0191   0.0097   1.0000
  14.750   1.3284   0.06112   0.05602  -0.0191   0.0097   1.0000
  15.000   1.3263   0.06464   0.05970  -0.0196   0.0096   1.0000
  15.250   1.3232   0.06842   0.06363  -0.0201   0.0096   1.0000
  15.500   1.3185   0.07260   0.06798  -0.0210   0.0095   1.0000
  15.750   1.3124   0.07710   0.07265  -0.0222   0.0095   1.0000
  16.000   1.3049   0.08196   0.07768  -0.0237   0.0095   1.0000
  16.250   1.2961   0.08722   0.08310  -0.0258   0.0095   1.0000
  16.500   1.2851   0.09308   0.08917  -0.0283   0.0095   1.0000
  16.750   1.2736   0.09920   0.09545  -0.0311   0.0095   1.0000
  17.000   1.2618   0.10562   0.10204  -0.0344   0.0095   1.0000
  17.250   1.2473   0.11277   0.10937  -0.0382   0.0095   1.0000
  17.500   1.2337   0.12005   0.11682  -0.0424   0.0095   1.0000
  17.750   1.2179   0.12795   0.12487  -0.0469   0.0096   1.0000
  18.000   1.2043   0.13582   0.13290  -0.0519   0.0095   1.0000
  18.250   1.1871   0.14474   0.14198  -0.0575   0.0096   1.0000
  18.500   1.1668   0.15457   0.15194  -0.0636   0.0097   1.0000
  18.750   0.8282   0.19365   0.19194  -0.0858   0.0129   1.0000
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