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AIRFOIL 3024 9.84% (s3024-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: AIRFOIL 3024 9.84% (s3024-il)
Reynolds number: 200,000
Max Cl/Cd: 80.9 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s3024-il-200000.txt
Download as CSV file: xf-s3024-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3538   0.09294   0.08974  -0.0403   1.0000   0.0444
  -8.250  -0.3785   0.09246   0.08936  -0.0366   1.0000   0.0446
  -8.000  -0.4012   0.09182   0.08881  -0.0331   1.0000   0.0446
  -7.750  -0.3959   0.08681   0.08381  -0.0432   0.9943   0.0449
  -7.500  -0.3846   0.07943   0.07644  -0.0493   0.9889   0.0457
  -7.250  -0.3673   0.07688   0.07388  -0.0470   0.9868   0.0470
  -7.000  -0.3464   0.07305   0.07003  -0.0513   0.9824   0.0485
  -6.750  -0.3255   0.06842   0.06535  -0.0579   0.9763   0.0510
  -6.250  -0.2803   0.05343   0.04987  -0.0794   0.9621   0.0582
  -6.000  -0.2518   0.05114   0.04764  -0.0813   0.9600   0.0610
  -5.750  -0.2319   0.04785   0.04416  -0.0837   0.9525   0.0663
  -5.500  -0.2046   0.04283   0.03883  -0.0886   0.9481   0.0728
  -5.250  -0.1709   0.03993   0.03574  -0.0919   0.9456   0.0794
  -5.000  -0.1561   0.03682   0.03232  -0.0918   0.9368   0.0864
  -4.750  -0.1252   0.02701   0.02118  -0.0918   0.9326   0.0415
  -4.500  -0.1004   0.02453   0.01787  -0.0901   0.9260   0.0351
  -4.250  -0.0725   0.02183   0.01486  -0.0902   0.9213   0.0342
  -4.000  -0.0393   0.02005   0.01278  -0.0909   0.9181   0.0341
  -3.750  -0.0138   0.01901   0.01154  -0.0901   0.9121   0.0348
  -3.500   0.0129   0.01759   0.01011  -0.0899   0.9067   0.0379
  -3.250   0.0442   0.01677   0.00925  -0.0902   0.9031   0.0415
  -3.000   0.0672   0.01618   0.00859  -0.0890   0.8960   0.0445
  -2.750   0.0937   0.01530   0.00772  -0.0885   0.8907   0.0536
  -2.500   0.1202   0.01399   0.00691  -0.0881   0.8869   0.1578
  -2.250   0.1404   0.01347   0.00682  -0.0869   0.8784   0.2754
  -2.000   0.1634   0.01255   0.00668  -0.0860   0.8738   0.4762
  -1.750   0.1783   0.01182   0.00675  -0.0830   0.8662   0.6902
  -1.500   0.2316   0.01122   0.00662  -0.0863   0.8637   0.9372
  -1.250   0.3121   0.01091   0.00607  -0.0967   0.8627   1.0000
  -1.000   0.3356   0.01082   0.00582  -0.0954   0.8572   1.0000
  -0.750   0.3558   0.01088   0.00578  -0.0940   0.8477   1.0000
  -0.500   0.3799   0.01080   0.00555  -0.0928   0.8421   1.0000
  -0.250   0.4014   0.01084   0.00551  -0.0915   0.8327   1.0000
   0.000   0.4256   0.01078   0.00534  -0.0904   0.8261   1.0000
   0.250   0.4485   0.01078   0.00526  -0.0892   0.8172   1.0000
   0.500   0.4724   0.01075   0.00514  -0.0881   0.8093   1.0000
   0.750   0.4968   0.01069   0.00499  -0.0870   0.8010   1.0000
   1.000   0.5206   0.01069   0.00494  -0.0860   0.7916   1.0000
   1.250   0.5464   0.01059   0.00474  -0.0851   0.7842   1.0000
   1.500   0.5702   0.01061   0.00473  -0.0842   0.7735   1.0000
   1.750   0.5953   0.01059   0.00466  -0.0833   0.7639   1.0000
   2.000   0.6214   0.01053   0.00453  -0.0826   0.7551   1.0000
   2.250   0.6459   0.01055   0.00453  -0.0817   0.7435   1.0000
   2.500   0.6710   0.01055   0.00451  -0.0809   0.7320   1.0000
   2.750   0.6966   0.01055   0.00447  -0.0802   0.7205   1.0000
   3.000   0.7223   0.01055   0.00443  -0.0795   0.7085   1.0000
   3.250   0.7479   0.01058   0.00442  -0.0788   0.6955   1.0000
   3.500   0.7731   0.01062   0.00443  -0.0781   0.6810   1.0000
   3.750   0.7980   0.01069   0.00448  -0.0773   0.6653   1.0000
   4.000   0.8228   0.01078   0.00458  -0.0765   0.6483   1.0000
   4.250   0.8474   0.01089   0.00466  -0.0758   0.6302   1.0000
   4.500   0.8721   0.01102   0.00474  -0.0750   0.6114   1.0000
   4.750   0.8962   0.01120   0.00487  -0.0741   0.5911   1.0000
   5.000   0.9199   0.01141   0.00505  -0.0733   0.5691   1.0000
   5.250   0.9433   0.01166   0.00524  -0.0723   0.5465   1.0000
   5.500   0.9661   0.01195   0.00547  -0.0714   0.5225   1.0000
   5.750   0.9883   0.01227   0.00574  -0.0703   0.4970   1.0000
   6.000   1.0101   0.01264   0.00606  -0.0692   0.4712   1.0000
   6.250   1.0312   0.01305   0.00639  -0.0681   0.4449   1.0000
   6.500   1.0516   0.01350   0.00676  -0.0668   0.4184   1.0000
   6.750   1.0716   0.01397   0.00719  -0.0656   0.3912   1.0000
   7.000   1.0911   0.01448   0.00764  -0.0643   0.3646   1.0000
   7.250   1.1098   0.01504   0.00812  -0.0629   0.3381   1.0000
   7.500   1.1273   0.01563   0.00863  -0.0613   0.3100   1.0000
   7.750   1.1439   0.01627   0.00917  -0.0597   0.2816   1.0000
   8.000   1.1600   0.01693   0.00977  -0.0580   0.2546   1.0000
   8.250   1.1754   0.01763   0.01039  -0.0563   0.2305   1.0000
   8.500   1.1909   0.01832   0.01102  -0.0546   0.2056   1.0000
   8.750   1.2050   0.01906   0.01170  -0.0528   0.1815   1.0000
   9.000   1.2167   0.01987   0.01242  -0.0506   0.1577   1.0000
   9.250   1.2282   0.02067   0.01319  -0.0484   0.1369   1.0000
   9.500   1.2386   0.02158   0.01405  -0.0461   0.1169   1.0000
   9.750   1.2466   0.02272   0.01508  -0.0437   0.0895   1.0000
  10.000   1.2444   0.02471   0.01676  -0.0403   0.0520   1.0000
  10.250   1.2411   0.02684   0.01876  -0.0369   0.0385   1.0000
  10.500   1.2458   0.02840   0.02041  -0.0346   0.0330   1.0000
  10.750   1.2447   0.03044   0.02249  -0.0320   0.0298   1.0000
  11.000   1.2498   0.03210   0.02428  -0.0301   0.0280   1.0000
  11.250   1.2534   0.03393   0.02625  -0.0283   0.0265   1.0000
  11.500   1.2566   0.03589   0.02829  -0.0266   0.0255   1.0000
  11.750   1.2587   0.03803   0.03051  -0.0250   0.0246   1.0000
  12.000   1.2602   0.04037   0.03292  -0.0235   0.0239   1.0000
  12.250   1.2620   0.04301   0.03562  -0.0220   0.0232   1.0000
  12.500   1.2696   0.04519   0.03792  -0.0207   0.0228   1.0000
  12.750   1.2780   0.04735   0.04024  -0.0196   0.0224   1.0000
  13.000   1.2867   0.04964   0.04268  -0.0185   0.0221   1.0000
  13.250   1.2932   0.05213   0.04537  -0.0176   0.0217   1.0000
  13.500   1.2976   0.05488   0.04834  -0.0168   0.0213   1.0000
  13.750   1.2986   0.05770   0.05136  -0.0162   0.0207   1.0000
  14.000   1.2984   0.06087   0.05473  -0.0158   0.0203   1.0000
  14.250   1.2960   0.06435   0.05841  -0.0157   0.0201   1.0000
  14.500   1.2909   0.06822   0.06251  -0.0158   0.0199   1.0000
  14.750   1.2824   0.07271   0.06725  -0.0163   0.0200   1.0000
  15.000   1.2710   0.07767   0.07246  -0.0173   0.0199   1.0000
  15.250   1.2568   0.08326   0.07830  -0.0190   0.0200   1.0000
  15.500   1.2401   0.08953   0.08483  -0.0214   0.0201   1.0000
  15.750   1.2215   0.09643   0.09197  -0.0246   0.0203   1.0000
  16.000   1.2014   0.10405   0.09983  -0.0286   0.0205   1.0000
  16.250   1.1788   0.11272   0.10873  -0.0336   0.0207   1.0000
  16.500   1.1564   0.12190   0.11811  -0.0394   0.0209   1.0000
  16.750   1.1319   0.13226   0.12866  -0.0462   0.0212   1.0000
  17.000   1.1048   0.14411   0.14067  -0.0540   0.0216   1.0000
  17.250   1.0752   0.15780   0.15447  -0.0630   0.0222   1.0000
  17.500   1.0503   0.17083   0.16753  -0.0707   0.0229   1.0000
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