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S2048 (s2048-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: S2048 (s2048-il)
Reynolds number: 200,000
Max Cl/Cd: 75.75 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s2048-il-200000.txt
Download as CSV file: xf-s2048-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S2048                                           
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.4596   0.11059   0.10687  -0.0281   1.0000   0.0411
 -10.000  -0.4636   0.10704   0.10338  -0.0319   1.0000   0.0416
  -9.750  -0.4646   0.10337   0.09975  -0.0344   1.0000   0.0418
  -9.500  -0.4656   0.09960   0.09602  -0.0365   1.0000   0.0419
  -9.250  -0.4686   0.09549   0.09196  -0.0390   1.0000   0.0419
  -9.000  -0.4625   0.09068   0.08717  -0.0339   1.0000   0.0439
  -8.750  -0.4586   0.08799   0.08450  -0.0331   1.0000   0.0452
  -8.500  -0.4593   0.08490   0.08145  -0.0335   1.0000   0.0461
  -8.250  -0.4631   0.08170   0.07830  -0.0340   1.0000   0.0475
  -8.000  -0.4715   0.07847   0.07514  -0.0345   1.0000   0.0479
  -7.750  -0.4858   0.07526   0.07201  -0.0348   1.0000   0.0486
  -7.500  -0.4961   0.07085   0.06764  -0.0379   1.0000   0.0493
  -7.250  -0.5045   0.06670   0.06346  -0.0395   1.0000   0.0502
  -7.000  -0.5119   0.06232   0.05897  -0.0412   1.0000   0.0523
  -6.750  -0.5190   0.06004   0.05615  -0.0423   1.0000   0.0544
  -6.500  -0.5229   0.05319   0.04925  -0.0421   1.0000   0.0556
  -6.250  -0.4907   0.03957   0.03622  -0.0373   1.0000   0.0577
  -6.000  -0.4864   0.03688   0.03347  -0.0361   1.0000   0.0598
  -5.750  -0.4804   0.03392   0.03032  -0.0356   1.0000   0.0638
  -5.500  -0.4745   0.02970   0.02572  -0.0359   1.0000   0.0703
  -5.250  -0.4625   0.02757   0.02360  -0.0349   1.0000   0.0741
  -5.000  -0.4435   0.02394   0.01947  -0.0362   0.9989   0.0836
  -4.750  -0.4226   0.02632   0.02012  -0.0360   1.0000   0.0399
  -4.500  -0.3987   0.02324   0.01660  -0.0355   1.0000   0.0384
  -4.250  -0.3746   0.02154   0.01452  -0.0348   1.0000   0.0393
  -4.000  -0.3482   0.02025   0.01292  -0.0345   0.9995   0.0407
  -3.750  -0.3127   0.01870   0.01111  -0.0358   0.9968   0.0413
  -3.500  -0.2773   0.01729   0.00954  -0.0372   0.9944   0.0426
  -3.250  -0.2441   0.01608   0.00836  -0.0386   0.9909   0.0467
  -3.000  -0.2086   0.01547   0.00770  -0.0403   0.9870   0.0521
  -2.750  -0.1714   0.01467   0.00690  -0.0425   0.9839   0.0608
  -2.500  -0.1382   0.01350   0.00614  -0.0440   0.9799   0.1447
  -2.250  -0.1098   0.01183   0.00612  -0.0454   0.9758   0.5328
  -2.000  -0.0765   0.01170   0.00637  -0.0463   0.9716   0.6731
  -1.750  -0.0477   0.01167   0.00650  -0.0462   0.9657   0.7380
  -1.500  -0.0171   0.01167   0.00659  -0.0463   0.9600   0.7897
  -1.250   0.0199   0.01169   0.00662  -0.0478   0.9563   0.8229
  -1.000   0.0432   0.01160   0.00658  -0.0464   0.9479   0.8583
  -0.750   0.0765   0.01151   0.00657  -0.0466   0.9436   0.9080
  -0.500   0.1233   0.01143   0.00650  -0.0499   0.9395   0.9597
  -0.250   0.1808   0.01129   0.00629  -0.0561   0.9353   0.9915
   0.000   0.2342   0.01107   0.00600  -0.0613   0.9308   1.0000
   0.250   0.2743   0.01080   0.00568  -0.0639   0.9219   1.0000
   0.500   0.3223   0.01045   0.00528  -0.0677   0.9164   1.0000
   0.750   0.3539   0.01024   0.00504  -0.0684   0.9065   1.0000
   1.000   0.3951   0.00995   0.00473  -0.0708   0.9011   1.0000
   1.250   0.4228   0.00981   0.00457  -0.0706   0.8901   1.0000
   1.500   0.4526   0.00966   0.00442  -0.0707   0.8797   1.0000
   1.750   0.4839   0.00949   0.00425  -0.0710   0.8697   1.0000
   2.000   0.5147   0.00933   0.00410  -0.0712   0.8585   1.0000
   2.250   0.5431   0.00923   0.00400  -0.0709   0.8450   1.0000
   2.500   0.5698   0.00918   0.00396  -0.0702   0.8293   1.0000
   2.750   0.5962   0.00916   0.00394  -0.0695   0.8114   1.0000
   3.000   0.6231   0.00914   0.00393  -0.0689   0.7919   1.0000
   3.250   0.6488   0.00917   0.00395  -0.0680   0.7686   1.0000
   3.500   0.6741   0.00922   0.00397  -0.0670   0.7403   1.0000
   3.750   0.6980   0.00931   0.00398  -0.0657   0.7009   1.0000
   4.000   0.7204   0.00951   0.00402  -0.0641   0.6433   1.0000
   4.250   0.7404   0.00994   0.00411  -0.0622   0.5661   1.0000
   4.500   0.7583   0.01060   0.00435  -0.0602   0.4831   1.0000
   4.750   0.7768   0.01131   0.00472  -0.0585   0.4143   1.0000
   5.000   0.7967   0.01198   0.00513  -0.0571   0.3602   1.0000
   5.250   0.8176   0.01260   0.00559  -0.0560   0.3169   1.0000
   5.500   0.8392   0.01318   0.00604  -0.0551   0.2799   1.0000
   5.750   0.8610   0.01375   0.00650  -0.0541   0.2444   1.0000
   6.000   0.8822   0.01438   0.00699  -0.0532   0.2019   1.0000
   6.250   0.9017   0.01526   0.00759  -0.0520   0.1440   1.0000
   6.500   0.9194   0.01646   0.00849  -0.0505   0.0988   1.0000
   6.750   0.9369   0.01769   0.00961  -0.0489   0.0784   1.0000
   7.000   0.9555   0.01885   0.01076  -0.0474   0.0654   1.0000
   7.250   0.9735   0.02013   0.01200  -0.0460   0.0543   1.0000
   7.500   0.9944   0.02098   0.01295  -0.0449   0.0452   1.0000
   7.750   1.0132   0.02229   0.01435  -0.0435   0.0370   1.0000
   8.000   1.0299   0.02453   0.01659  -0.0419   0.0314   1.0000
   8.250   1.0514   0.02610   0.01840  -0.0407   0.0283   1.0000
   8.500   1.0714   0.02771   0.02015  -0.0395   0.0255   1.0000
   8.750   1.0885   0.03126   0.02384  -0.0386   0.0227   1.0000
   9.000   1.1059   0.03283   0.02573  -0.0369   0.0216   1.0000
   9.250   1.1208   0.03547   0.02876  -0.0351   0.0209   1.0000
   9.500   1.1312   0.03862   0.03233  -0.0329   0.0204   1.0000
   9.750   1.1362   0.04217   0.03631  -0.0302   0.0203   1.0000
  10.000   1.1351   0.04597   0.04054  -0.0272   0.0203   1.0000
  10.250   1.1289   0.04986   0.04480  -0.0241   0.0206   1.0000
  10.500   1.1161   0.05345   0.04870  -0.0204   0.0208   1.0000
  10.750   1.0989   0.05708   0.05258  -0.0170   0.0211   1.0000
  11.000   1.0796   0.06095   0.05668  -0.0146   0.0213   1.0000
  11.250   1.0595   0.06521   0.06115  -0.0136   0.0214   1.0000
  11.500   1.0384   0.07008   0.06621  -0.0140   0.0216   1.0000
  11.750   1.0169   0.07575   0.07203  -0.0160   0.0218   1.0000
  12.000   0.9944   0.08241   0.07884  -0.0196   0.0220   1.0000
  12.250   0.9718   0.09038   0.08693  -0.0246   0.0223   1.0000
  12.500   0.8525   0.09697   0.09386  -0.0270   0.0224   1.0000
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