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SD2083 (9.0%) (sd2083-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: SD2083 (9.0%) (sd2083-il)
Reynolds number: 50,000
Max Cl/Cd: 37.42 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sd2083-il-50000.txt
Download as CSV file: xf-sd2083-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD2083 (9.0%)                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3762   0.09629   0.08975  -0.0233   1.0000   0.2522
  -7.750  -0.3863   0.09440   0.08801  -0.0229   1.0000   0.2620
  -7.500  -0.3981   0.09315   0.08690  -0.0215   1.0000   0.2735
  -7.250  -0.3918   0.08992   0.08370  -0.0196   1.0000   0.2867
  -7.000  -0.3903   0.08716   0.08102  -0.0173   1.0000   0.2996
  -6.750  -0.3932   0.08486   0.07882  -0.0147   1.0000   0.3114
  -6.500  -0.4030   0.08302   0.07710  -0.0114   1.0000   0.3242
  -6.250  -0.4122   0.08122   0.07541  -0.0083   1.0000   0.3376
  -6.000  -0.4185   0.07923   0.07351  -0.0049   1.0000   0.3544
  -5.750  -0.4305   0.07767   0.07206  -0.0015   1.0000   0.3725
  -5.500  -0.4364   0.07550   0.06998   0.0022   1.0000   0.3929
  -4.250  -0.4203   0.05330   0.04712  -0.0243   1.0000   0.2484
  -4.000  -0.4279   0.05422   0.04847  -0.0130   1.0000   0.3252
  -3.750  -0.3462   0.03930   0.03073  -0.0354   1.0000   0.1292
  -3.500  -0.3240   0.03647   0.02756  -0.0350   1.0000   0.1259
  -3.250  -0.2989   0.03380   0.02432  -0.0347   1.0000   0.1218
  -3.000  -0.2733   0.03158   0.02157  -0.0341   1.0000   0.1205
  -2.750  -0.2485   0.02981   0.01939  -0.0334   1.0000   0.1219
  -2.500  -0.2240   0.02839   0.01762  -0.0326   1.0000   0.1280
  -2.250  -0.2004   0.02710   0.01621  -0.0318   1.0000   0.1398
  -2.000  -0.1758   0.02585   0.01485  -0.0308   1.0000   0.1549
  -1.750  -0.1495   0.02452   0.01363  -0.0301   1.0000   0.1955
  -1.500  -0.1091   0.01976   0.01204  -0.0297   1.0000   1.0000
  -1.250  -0.0885   0.02003   0.01168  -0.0289   1.0000   1.0000
  -1.000  -0.0685   0.02033   0.01154  -0.0282   1.0000   1.0000
  -0.750  -0.0488   0.02067   0.01151  -0.0276   1.0000   1.0000
  -0.500  -0.0291   0.02104   0.01157  -0.0270   1.0000   1.0000
  -0.250  -0.0096   0.02145   0.01167  -0.0264   1.0000   1.0000
   0.000   0.0098   0.02189   0.01187  -0.0259   1.0000   1.0000
   0.250   0.0291   0.02237   0.01214  -0.0255   1.0000   1.0000
   0.500   0.0481   0.02289   0.01247  -0.0250   1.0000   1.0000
   0.750   0.0670   0.02344   0.01285  -0.0246   1.0000   1.0000
   1.000   0.0856   0.02404   0.01330  -0.0243   1.0000   1.0000
   1.250   0.1041   0.02468   0.01382  -0.0239   1.0000   1.0000
   1.500   0.1222   0.02537   0.01440  -0.0237   1.0000   1.0000
   1.750   0.1401   0.02611   0.01504  -0.0234   1.0000   1.0000
   2.000   0.1729   0.02730   0.01616  -0.0262   0.9932   1.0000
   2.250   0.2210   0.02883   0.01764  -0.0317   0.9765   1.0000
   2.500   0.2691   0.03034   0.01912  -0.0370   0.9593   1.0000
   2.750   0.3139   0.03168   0.02046  -0.0415   0.9411   1.0000
   3.000   0.3532   0.03280   0.02161  -0.0447   0.9217   1.0000
   3.250   0.4000   0.03397   0.02287  -0.0490   0.9023   1.0000
   3.500   0.4358   0.03487   0.02385  -0.0511   0.8812   1.0000
   3.750   0.4813   0.03571   0.02481  -0.0545   0.8602   1.0000
   4.000   0.5168   0.03639   0.02564  -0.0560   0.8376   1.0000
   4.250   0.5682   0.03677   0.02621  -0.0594   0.8162   1.0000
   4.500   0.6007   0.03713   0.02673  -0.0599   0.7919   1.0000
   4.750   0.6433   0.03713   0.02700  -0.0613   0.7684   1.0000
   5.000   0.7007   0.03632   0.02650  -0.0637   0.7459   1.0000
   5.250   0.7419   0.03564   0.02609  -0.0638   0.7202   1.0000
   5.500   0.7866   0.03432   0.02512  -0.0633   0.6946   1.0000
   5.750   0.8357   0.03231   0.02344  -0.0625   0.6676   1.0000
   6.000   0.8849   0.02993   0.02136  -0.0611   0.6362   1.0000
   6.250   0.9255   0.02806   0.01971  -0.0588   0.5976   1.0000
   6.500   0.9596   0.02684   0.01850  -0.0562   0.5514   1.0000
   6.750   0.9855   0.02656   0.01810  -0.0533   0.5007   1.0000
   7.000   1.0078   0.02693   0.01820  -0.0506   0.4486   1.0000
   7.250   1.0246   0.02795   0.01908  -0.0478   0.3977   1.0000
   7.500   1.0426   0.02922   0.02001  -0.0454   0.3484   1.0000
   7.750   1.0565   0.03082   0.02145  -0.0428   0.3021   1.0000
   8.000   1.0704   0.03260   0.02306  -0.0402   0.2584   1.0000
   8.250   1.0833   0.03460   0.02486  -0.0377   0.2172   1.0000
   8.500   1.0944   0.03674   0.02673  -0.0351   0.1782   1.0000
   8.750   1.1002   0.03882   0.02883  -0.0321   0.1450   1.0000
   9.000   1.1104   0.04140   0.03135  -0.0297   0.1189   1.0000
   9.250   1.1259   0.04431   0.03426  -0.0281   0.1018   1.0000
   9.500   1.1405   0.04823   0.03862  -0.0262   0.0939   1.0000
   9.750   1.1608   0.05216   0.04250  -0.0256   0.0868   1.0000
  10.000   1.1592   0.05577   0.04677  -0.0225   0.0843   1.0000
  10.250   1.1555   0.05961   0.05113  -0.0197   0.0825   1.0000
  10.500   1.1480   0.06356   0.05550  -0.0170   0.0814   1.0000
  10.750   1.1352   0.06753   0.05982  -0.0144   0.0808   1.0000
  11.000   1.1168   0.07143   0.06400  -0.0116   0.0811   1.0000
  11.250   1.0958   0.07569   0.06849  -0.0098   0.0820   1.0000
  11.500   1.0725   0.08044   0.07344  -0.0092   0.0828   1.0000
  11.750   1.0490   0.08581   0.07896  -0.0097   0.0837   1.0000
  12.000   1.0277   0.09171   0.08497  -0.0114   0.0848   1.0000
  12.250   1.0090   0.09814   0.09147  -0.0137   0.0858   1.0000
  12.500   0.9969   0.10467   0.09804  -0.0160   0.0865   1.0000
  12.750   0.9006   0.13105   0.12428  -0.0382   0.1099   1.0000
  13.000   0.9011   0.13737   0.13059  -0.0399   0.1117   1.0000
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