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AIRFOIL 3024 9.84% (s3024-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: AIRFOIL 3024 9.84% (s3024-il)
Reynolds number: 1,000,000
Max Cl/Cd: 110.07 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s3024-il-1000000-n5.txt
Download as CSV file: xf-s3024-il-1000000-n5.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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3470   0.09825   0.09656  -0.0405   0.9687   0.0049
 -10.000  -0.3368   0.09226   0.09054  -0.0460   0.9579   0.0049
  -9.750  -0.3270   0.08784   0.08608  -0.0502   0.9438   0.0049
  -9.500  -0.3290   0.08219   0.08038  -0.0531   0.9273   0.0051
  -9.250  -0.3319   0.07793   0.07608  -0.0550   0.9134   0.0050
  -8.750  -0.2914   0.05902   0.05714  -0.0497   0.8600   0.0055
  -8.250  -0.4699   0.02910   0.02629  -0.0788   0.8528   0.0050
  -8.000  -0.4597   0.02514   0.02188  -0.0787   0.8466   0.0051
  -7.750  -0.4487   0.02113   0.01733  -0.0781   0.8413   0.0051
  -7.500  -0.4302   0.01875   0.01459  -0.0776   0.8362   0.0052
  -7.250  -0.4085   0.01716   0.01273  -0.0772   0.8310   0.0053
  -7.000  -0.3850   0.01600   0.01136  -0.0768   0.8264   0.0054
  -6.750  -0.3601   0.01514   0.01037  -0.0766   0.8215   0.0055
  -6.500  -0.3347   0.01441   0.00949  -0.0764   0.8163   0.0056
  -6.250  -0.3088   0.01385   0.00882  -0.0762   0.8116   0.0058
  -6.000  -0.2826   0.01322   0.00809  -0.0760   0.8067   0.0059
  -5.750  -0.2566   0.01253   0.00726  -0.0758   0.8015   0.0060
  -5.500  -0.2305   0.01189   0.00649  -0.0755   0.7968   0.0061
  -5.250  -0.2039   0.01129   0.00579  -0.0753   0.7918   0.0063
  -5.000  -0.1773   0.01078   0.00518  -0.0751   0.7866   0.0065
  -4.750  -0.1505   0.01033   0.00464  -0.0749   0.7818   0.0067
  -4.500  -0.1232   0.00994   0.00418  -0.0748   0.7766   0.0069
  -4.250  -0.0959   0.00961   0.00379  -0.0747   0.7710   0.0072
  -4.000  -0.0684   0.00935   0.00346  -0.0746   0.7658   0.0074
  -3.750  -0.0411   0.00899   0.00304  -0.0745   0.7600   0.0076
  -3.500  -0.0139   0.00865   0.00264  -0.0743   0.7540   0.0081
  -3.250   0.0139   0.00842   0.00237  -0.0743   0.7481   0.0085
  -3.000   0.0416   0.00823   0.00214  -0.0742   0.7414   0.0088
  -2.750   0.0695   0.00808   0.00195  -0.0742   0.7350   0.0096
  -2.500   0.0974   0.00794   0.00176  -0.0742   0.7276   0.0102
  -2.250   0.1253   0.00779   0.00157  -0.0741   0.7205   0.0110
  -2.000   0.1532   0.00767   0.00141  -0.0741   0.7124   0.0127
  -1.750   0.1811   0.00755   0.00128  -0.0740   0.7046   0.0173
  -1.500   0.2085   0.00734   0.00116  -0.0740   0.6954   0.0497
  -1.250   0.2359   0.00712   0.00108  -0.0740   0.6857   0.0936
  -1.000   0.2633   0.00698   0.00101  -0.0739   0.6751   0.1332
  -0.750   0.2905   0.00683   0.00096  -0.0739   0.6634   0.1849
  -0.500   0.3177   0.00669   0.00093  -0.0738   0.6508   0.2379
  -0.250   0.3446   0.00649   0.00092  -0.0738   0.6377   0.3176
   0.000   0.3711   0.00626   0.00092  -0.0737   0.6241   0.4175
   0.250   0.3977   0.00611   0.00093  -0.0735   0.6096   0.4962
   0.500   0.4242   0.00600   0.00096  -0.0734   0.5946   0.5692
   0.750   0.4500   0.00584   0.00100  -0.0730   0.5793   0.6599
   1.000   0.4744   0.00565   0.00106  -0.0723   0.5633   0.7659
   1.250   0.4967   0.00547   0.00114  -0.0710   0.5478   0.8722
   1.500   0.5246   0.00547   0.00122  -0.0707   0.5311   0.9528
   1.750   0.5609   0.00560   0.00128  -0.0727   0.5125   0.9780
   2.000   0.5965   0.00575   0.00134  -0.0745   0.4931   0.9899
   2.500   0.6606   0.00610   0.00149  -0.0766   0.4523   1.0000
   2.750   0.6853   0.00628   0.00158  -0.0760   0.4327   1.0000
   3.000   0.7099   0.00649   0.00169  -0.0754   0.4128   1.0000
   3.250   0.7348   0.00669   0.00181  -0.0749   0.3926   1.0000
   3.500   0.7595   0.00690   0.00193  -0.0744   0.3725   1.0000
   3.750   0.7842   0.00714   0.00208  -0.0739   0.3512   1.0000
   4.000   0.8091   0.00737   0.00222  -0.0734   0.3320   1.0000
   4.250   0.8339   0.00761   0.00238  -0.0729   0.3127   1.0000
   4.500   0.8586   0.00786   0.00255  -0.0725   0.2936   1.0000
   4.750   0.8830   0.00815   0.00274  -0.0720   0.2716   1.0000
   5.000   0.9068   0.00849   0.00296  -0.0714   0.2459   1.0000
   5.250   0.9308   0.00880   0.00317  -0.0708   0.2251   1.0000
   5.500   0.9547   0.00913   0.00341  -0.0703   0.2036   1.0000
   5.750   0.9775   0.00955   0.00369  -0.0696   0.1761   1.0000
   6.000   0.9997   0.01001   0.00400  -0.0688   0.1476   1.0000
   6.250   1.0220   0.01046   0.00432  -0.0680   0.1241   1.0000
   6.500   1.0448   0.01085   0.00463  -0.0673   0.1063   1.0000
   6.750   1.0667   0.01131   0.00498  -0.0665   0.0873   1.0000
   7.000   1.0883   0.01180   0.00536  -0.0657   0.0680   1.0000
   7.250   1.1080   0.01241   0.00584  -0.0645   0.0458   1.0000
   7.500   1.1271   0.01306   0.00637  -0.0633   0.0258   1.0000
   7.750   1.1449   0.01380   0.00700  -0.0618   0.0091   1.0000
   8.000   1.1664   0.01421   0.00742  -0.0609   0.0078   1.0000
   8.250   1.1877   0.01460   0.00785  -0.0600   0.0071   1.0000
   8.500   1.2088   0.01499   0.00828  -0.0591   0.0068   1.0000
   8.750   1.2292   0.01541   0.00873  -0.0581   0.0065   1.0000
   9.000   1.2489   0.01585   0.00921  -0.0569   0.0062   1.0000
   9.250   1.2676   0.01631   0.00972  -0.0556   0.0060   1.0000
   9.500   1.2838   0.01680   0.01025  -0.0539   0.0058   1.0000
   9.750   1.2986   0.01733   0.01083  -0.0519   0.0056   1.0000
  10.000   1.3124   0.01793   0.01148  -0.0499   0.0054   1.0000
  10.250   1.3251   0.01863   0.01224  -0.0478   0.0051   1.0000
  10.500   1.3362   0.01944   0.01312  -0.0456   0.0049   1.0000
  10.750   1.3476   0.02027   0.01402  -0.0436   0.0048   1.0000
  11.000   1.3620   0.02091   0.01471  -0.0420   0.0047   1.0000
  11.250   1.3741   0.02172   0.01559  -0.0403   0.0046   1.0000
  11.500   1.3858   0.02258   0.01652  -0.0385   0.0045   1.0000
  11.750   1.3965   0.02353   0.01754  -0.0368   0.0045   1.0000
  12.000   1.4062   0.02459   0.01867  -0.0351   0.0044   1.0000
  12.250   1.4160   0.02566   0.01981  -0.0335   0.0043   1.0000
  12.500   1.4228   0.02700   0.02124  -0.0318   0.0042   1.0000
  12.750   1.4295   0.02838   0.02272  -0.0302   0.0042   1.0000
  13.000   1.4363   0.02981   0.02423  -0.0287   0.0041   1.0000
  13.250   1.4409   0.03147   0.02598  -0.0273   0.0040   1.0000
  13.500   1.4459   0.03317   0.02776  -0.0260   0.0039   1.0000
  13.750   1.4495   0.03505   0.02973  -0.0249   0.0039   1.0000
  14.000   1.4528   0.03704   0.03181  -0.0239   0.0038   1.0000
  14.250   1.4548   0.03922   0.03409  -0.0231   0.0037   1.0000
  14.500   1.4540   0.04180   0.03677  -0.0224   0.0038   1.0000
  14.750   1.4526   0.04456   0.03964  -0.0219   0.0037   1.0000
  15.000   1.4508   0.04751   0.04269  -0.0217   0.0037   1.0000
  15.250   1.4496   0.05054   0.04582  -0.0218   0.0036   1.0000
  15.500   1.4494   0.05358   0.04896  -0.0220   0.0035   1.0000
  15.750   1.4411   0.05784   0.05335  -0.0227   0.0036   1.0000
  16.000   1.4379   0.06160   0.05721  -0.0236   0.0035   1.0000
  16.250   1.4320   0.06591   0.06163  -0.0248   0.0035   1.0000
  16.500   1.4235   0.07079   0.06664  -0.0264   0.0035   1.0000
  16.750   1.4146   0.07589   0.07185  -0.0283   0.0034   1.0000
  17.000   1.4043   0.08144   0.07753  -0.0305   0.0034   1.0000
  17.250   1.3931   0.08732   0.08352  -0.0330   0.0033   1.0000
  17.500   1.3817   0.09340   0.08972  -0.0358   0.0034   1.0000
  17.750   1.3667   0.10030   0.09675  -0.0390   0.0033   1.0000
  18.000   1.3548   0.10682   0.10339  -0.0422   0.0033   1.0000
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