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SA7026 (sa7026-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: SA7026 (sa7026-il)
Reynolds number: 50,000
Max Cl/Cd: 40.58 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sa7026-il-50000-n5.txt
Download as CSV file: xf-sa7026-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SA7026                                          
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3600   0.10357   0.09726  -0.0348   1.0000   0.1106
  -7.750  -0.3798   0.10288   0.09672  -0.0334   1.0000   0.1112
  -7.500  -0.3956   0.10162   0.09560  -0.0324   1.0000   0.1115
  -7.250  -0.3806   0.09708   0.09108  -0.0289   1.0000   0.1150
  -7.000  -0.3865   0.09505   0.08913  -0.0268   1.0000   0.1171
  -6.500  -0.4100   0.09140   0.08568  -0.0276   1.0000   0.1244
  -6.000  -0.4053   0.07875   0.07288  -0.0364   1.0000   0.0564
  -5.750  -0.4034   0.07587   0.07004  -0.0348   1.0000   0.0547
  -5.500  -0.3996   0.07243   0.06660  -0.0353   1.0000   0.0526
  -5.250  -0.3926   0.06814   0.06225  -0.0375   1.0000   0.0499
  -5.000  -0.3599   0.05980   0.05335  -0.0479   0.9959   0.0440
  -4.750  -0.3339   0.05542   0.04880  -0.0516   0.9909   0.0430
  -4.500  -0.3036   0.05068   0.04372  -0.0562   0.9858   0.0420
  -4.250  -0.2708   0.04621   0.03879  -0.0605   0.9812   0.0411
  -4.000  -0.2382   0.04215   0.03419  -0.0638   0.9762   0.0405
  -3.750  -0.2024   0.03857   0.02994  -0.0669   0.9720   0.0402
  -3.500  -0.1682   0.03568   0.02644  -0.0690   0.9675   0.0402
  -3.250  -0.1348   0.03326   0.02344  -0.0704   0.9626   0.0407
  -3.000  -0.0990   0.03132   0.02097  -0.0719   0.9583   0.0416
  -2.750  -0.0663   0.02993   0.01909  -0.0726   0.9532   0.0442
  -2.500  -0.0350   0.02874   0.01781  -0.0737   0.9476   0.0499
  -2.250   0.0012   0.02779   0.01652  -0.0750   0.9431   0.0562
  -2.000   0.0301   0.02690   0.01545  -0.0753   0.9364   0.0638
  -1.750   0.0670   0.02589   0.01444  -0.0771   0.9314   0.0990
  -1.500   0.0982   0.02360   0.01421  -0.0789   0.9272   0.4792
  -1.250   0.1266   0.02226   0.01392  -0.0772   0.9205   1.0000
  -1.000   0.1635   0.02255   0.01358  -0.0792   0.9143   1.0000
  -0.750   0.1929   0.02281   0.01343  -0.0798   0.9057   1.0000
  -0.500   0.2254   0.02309   0.01335  -0.0810   0.8983   1.0000
  -0.250   0.2581   0.02336   0.01330  -0.0822   0.8905   1.0000
   0.000   0.2868   0.02364   0.01330  -0.0826   0.8815   1.0000
   0.250   0.3241   0.02386   0.01328  -0.0845   0.8749   1.0000
   0.750   0.3801   0.02438   0.01346  -0.0849   0.8558   1.0000
   1.000   0.4153   0.02455   0.01348  -0.0863   0.8482   1.0000
   1.250   0.4412   0.02482   0.01365  -0.0861   0.8377   1.0000
   1.500   0.4711   0.02503   0.01377  -0.0866   0.8284   1.0000
   1.750   0.5064   0.02512   0.01381  -0.0878   0.8206   1.0000
   2.000   0.5318   0.02536   0.01400  -0.0874   0.8094   1.0000
   2.250   0.5593   0.02554   0.01416  -0.0873   0.7987   1.0000
   2.500   0.5910   0.02558   0.01420  -0.0876   0.7892   1.0000
   2.750   0.6229   0.02557   0.01424  -0.0880   0.7795   1.0000
   3.250   0.6760   0.02579   0.01452  -0.0871   0.7553   1.0000
   3.500   0.7037   0.02583   0.01463  -0.0867   0.7433   1.0000
   3.750   0.7322   0.02583   0.01476  -0.0863   0.7313   1.0000
   4.000   0.7612   0.02579   0.01480  -0.0860   0.7190   1.0000
   4.250   0.7898   0.02572   0.01484  -0.0856   0.7059   1.0000
   4.500   0.8174   0.02568   0.01491  -0.0849   0.6917   1.0000
   4.750   0.8446   0.02563   0.01506  -0.0842   0.6765   1.0000
   5.000   0.8723   0.02555   0.01511  -0.0834   0.6605   1.0000
   5.250   0.9011   0.02541   0.01510  -0.0828   0.6440   1.0000
   5.500   0.9303   0.02527   0.01509  -0.0821   0.6267   1.0000
   5.750   0.9534   0.02543   0.01540  -0.0808   0.6060   1.0000
   6.000   0.9822   0.02534   0.01552  -0.0801   0.5859   1.0000
   6.250   1.0045   0.02558   0.01590  -0.0787   0.5622   1.0000
   6.500   1.0282   0.02577   0.01620  -0.0773   0.5373   1.0000
   6.750   1.0511   0.02603   0.01656  -0.0759   0.5109   1.0000
   7.000   1.0721   0.02642   0.01703  -0.0743   0.4828   1.0000
   7.250   1.0913   0.02693   0.01769  -0.0725   0.4537   1.0000
   7.500   1.1090   0.02754   0.01836  -0.0705   0.4239   1.0000
   7.750   1.1246   0.02827   0.01911  -0.0684   0.3931   1.0000
   8.000   1.1370   0.02914   0.02002  -0.0660   0.3608   1.0000
   8.250   1.1470   0.03013   0.02103  -0.0633   0.3277   1.0000
   8.500   1.1547   0.03124   0.02211  -0.0605   0.2958   1.0000
   8.750   1.1597   0.03250   0.02338  -0.0575   0.2639   1.0000
   9.000   1.1626   0.03397   0.02482  -0.0546   0.2313   1.0000
   9.250   1.1629   0.03572   0.02645  -0.0517   0.1992   1.0000
   9.500   1.1617   0.03778   0.02850  -0.0491   0.1638   1.0000
   9.750   1.1580   0.04025   0.03077  -0.0467   0.1317   1.0000
  10.250   1.1484   0.04620   0.03636  -0.0429   0.0756   1.0000
  10.500   1.1443   0.04937   0.03943  -0.0415   0.0595   1.0000
  10.750   1.1413   0.05262   0.04272  -0.0402   0.0496   1.0000
  11.000   1.1382   0.05597   0.04610  -0.0391   0.0446   1.0000
  11.250   1.1393   0.05911   0.04948  -0.0380   0.0392   1.0000
  11.500   1.1381   0.06240   0.05286  -0.0374   0.0360   1.0000
  11.750   1.1393   0.06571   0.05635  -0.0367   0.0331   1.0000
  12.000   1.1432   0.06888   0.05984  -0.0360   0.0307   1.0000
  12.250   1.1454   0.07232   0.06354  -0.0356   0.0289   1.0000
  12.500   1.1472   0.07592   0.06739  -0.0353   0.0279   1.0000
  12.750   1.1463   0.07990   0.07159  -0.0354   0.0270   1.0000
  13.000   1.1435   0.08425   0.07616  -0.0359   0.0264   1.0000
  13.250   1.1383   0.08901   0.08115  -0.0368   0.0260   1.0000
  13.500   1.1308   0.09425   0.08662  -0.0383   0.0257   1.0000
  13.750   1.1210   0.10003   0.09263  -0.0404   0.0255   1.0000
  14.000   1.1089   0.10645   0.09929  -0.0433   0.0255   1.0000
  14.250   1.0950   0.11363   0.10672  -0.0472   0.0256   1.0000
  14.500   1.0788   0.12198   0.11532  -0.0521   0.0259   1.0000
  14.750   1.0595   0.13201   0.12559  -0.0584   0.0264   1.0000
  15.000   1.0358   0.14479   0.13855  -0.0665   0.0274   1.0000
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