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SD8000-089-88 (sd8000-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: SD8000-089-88 (sd8000-il)
Reynolds number: 50,000
Max Cl/Cd: 34.55 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sd8000-il-50000-n5.txt
Download as CSV file: xf-sd8000-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD8000-089-88                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.5130   0.09590   0.08868  -0.0220   1.0000   0.0525
  -9.250  -0.5163   0.09105   0.08390  -0.0246   1.0000   0.0527
  -9.000  -0.5215   0.08590   0.07884  -0.0276   1.0000   0.0531
  -8.750  -0.5284   0.08053   0.07355  -0.0310   1.0000   0.0529
  -8.500  -0.5398   0.07429   0.06740  -0.0358   1.0000   0.0527
  -8.250  -0.5514   0.06814   0.06124  -0.0399   1.0000   0.0524
  -8.000  -0.5615   0.06245   0.05544  -0.0428   1.0000   0.0525
  -7.750  -0.5682   0.05711   0.04989  -0.0447   1.0000   0.0531
  -7.500  -0.5714   0.05189   0.04430  -0.0457   1.0000   0.0542
  -7.250  -0.5701   0.04689   0.03877  -0.0459   1.0000   0.0554
  -7.000  -0.5633   0.04244   0.03374  -0.0454   1.0000   0.0567
  -6.750  -0.5485   0.04066   0.03199  -0.0444   1.0000   0.0602
  -6.500  -0.5342   0.03807   0.02903  -0.0435   1.0000   0.0649
  -6.250  -0.5182   0.03468   0.02488  -0.0425   1.0000   0.0686
  -6.000  -0.5004   0.03298   0.02319  -0.0415   1.0000   0.0735
  -5.750  -0.4810   0.03100   0.02073  -0.0405   1.0000   0.0805
  -5.500  -0.4612   0.02926   0.01887  -0.0394   1.0000   0.0862
  -5.250  -0.4402   0.02780   0.01702  -0.0382   1.0000   0.0957
  -5.000  -0.4199   0.02652   0.01577  -0.0371   1.0000   0.1039
  -4.750  -0.3989   0.02538   0.01452  -0.0360   1.0000   0.1153
  -4.500  -0.3774   0.02427   0.01326  -0.0349   1.0000   0.1271
  -4.250  -0.3562   0.02336   0.01231  -0.0338   1.0000   0.1424
  -4.000  -0.3347   0.02248   0.01139  -0.0328   1.0000   0.1593
  -3.750  -0.3124   0.02169   0.01057  -0.0319   1.0000   0.1822
  -3.500  -0.2908   0.02092   0.00984  -0.0310   1.0000   0.2086
  -3.250  -0.2692   0.02018   0.00925  -0.0302   1.0000   0.2450
  -3.000  -0.2477   0.01947   0.00876  -0.0295   1.0000   0.2961
  -2.750  -0.2268   0.01878   0.00841  -0.0285   1.0000   0.3673
  -2.500  -0.2071   0.01817   0.00822  -0.0271   1.0000   0.4583
  -2.250  -0.1892   0.01769   0.00813  -0.0250   1.0000   0.5607
  -2.000  -0.1733   0.01735   0.00814  -0.0221   1.0000   0.6605
  -1.750  -0.1586   0.01710   0.00816  -0.0185   1.0000   0.7610
  -1.500  -0.1312   0.01689   0.00811  -0.0173   1.0000   0.8876
  -1.250  -0.0905   0.01677   0.00777  -0.0205   1.0000   1.0000
  -1.000  -0.0710   0.01689   0.00764  -0.0199   1.0000   1.0000
  -0.750  -0.0456   0.01709   0.00762  -0.0204   0.9975   1.0000
  -0.500  -0.0027   0.01745   0.00774  -0.0241   0.9866   1.0000
  -0.250   0.0395   0.01779   0.00790  -0.0276   0.9754   1.0000
   0.000   0.0812   0.01810   0.00806  -0.0308   0.9634   1.0000
   0.250   0.1228   0.01839   0.00824  -0.0339   0.9509   1.0000
   0.500   0.1643   0.01864   0.00841  -0.0369   0.9378   1.0000
   0.750   0.2058   0.01884   0.00856  -0.0397   0.9240   1.0000
   1.000   0.2472   0.01899   0.00869  -0.0424   0.9096   1.0000
   1.250   0.2876   0.01910   0.00880  -0.0446   0.8943   1.0000
   1.500   0.3245   0.01916   0.00888  -0.0461   0.8776   1.0000
   1.750   0.3603   0.01916   0.00891  -0.0472   0.8598   1.0000
   2.000   0.3959   0.01911   0.00892  -0.0480   0.8415   1.0000
   2.250   0.4276   0.01906   0.00891  -0.0480   0.8205   1.0000
   2.500   0.4588   0.01897   0.00888  -0.0477   0.7982   1.0000
   2.750   0.4881   0.01890   0.00888  -0.0471   0.7735   1.0000
   3.000   0.5175   0.01882   0.00883  -0.0464   0.7475   1.0000
   3.250   0.5456   0.01877   0.00881  -0.0454   0.7182   1.0000
   3.500   0.5726   0.01878   0.00882  -0.0442   0.6855   1.0000
   3.750   0.5990   0.01884   0.00887  -0.0429   0.6503   1.0000
   4.000   0.6241   0.01902   0.00898  -0.0415   0.6115   1.0000
   4.250   0.6484   0.01928   0.00914  -0.0400   0.5706   1.0000
   4.500   0.6717   0.01966   0.00942  -0.0386   0.5281   1.0000
   4.750   0.6941   0.02014   0.00976  -0.0371   0.4850   1.0000
   5.000   0.7158   0.02072   0.01019  -0.0357   0.4421   1.0000
   5.250   0.7371   0.02138   0.01073  -0.0344   0.4008   1.0000
   5.500   0.7582   0.02212   0.01137  -0.0332   0.3623   1.0000
   5.750   0.7793   0.02293   0.01207  -0.0321   0.3274   1.0000
   6.000   0.8003   0.02380   0.01284  -0.0311   0.2956   1.0000
   6.250   0.8217   0.02472   0.01371  -0.0301   0.2670   1.0000
   6.500   0.8430   0.02568   0.01465  -0.0292   0.2405   1.0000
   6.750   0.8644   0.02672   0.01569  -0.0284   0.2178   1.0000
   7.000   0.8854   0.02779   0.01678  -0.0275   0.1967   1.0000
   7.250   0.9061   0.02894   0.01789  -0.0266   0.1789   1.0000
   7.500   0.9270   0.03015   0.01919  -0.0257   0.1617   1.0000
   7.750   0.9474   0.03143   0.02061  -0.0248   0.1463   1.0000
   8.000   0.9672   0.03282   0.02209  -0.0238   0.1325   1.0000
   8.250   0.9864   0.03429   0.02363  -0.0228   0.1202   1.0000
   8.500   1.0044   0.03579   0.02514  -0.0218   0.1091   1.0000
   8.750   1.0218   0.03749   0.02713  -0.0207   0.0984   1.0000
   9.000   1.0384   0.03946   0.02935  -0.0195   0.0893   1.0000
   9.250   1.0539   0.04124   0.03114  -0.0185   0.0822   1.0000
   9.500   1.0667   0.04361   0.03396  -0.0171   0.0751   1.0000
   9.750   1.0810   0.04559   0.03586  -0.0161   0.0703   1.0000
  10.000   1.0871   0.04867   0.03955  -0.0144   0.0656   1.0000
  10.250   1.0937   0.05123   0.04237  -0.0130   0.0619   1.0000
  10.500   1.1014   0.05379   0.04504  -0.0117   0.0595   1.0000
  10.750   1.1005   0.05729   0.04883  -0.0102   0.0578   1.0000
  11.000   1.0867   0.06119   0.05316  -0.0081   0.0567   1.0000
  11.250   1.0696   0.06538   0.05767  -0.0069   0.0560   1.0000
  11.500   1.0490   0.07019   0.06274  -0.0070   0.0557   1.0000
  11.750   1.0255   0.07593   0.06872  -0.0087   0.0559   1.0000
  12.000   0.9988   0.08305   0.07602  -0.0124   0.0563   1.0000
  12.250   0.9706   0.09174   0.08482  -0.0180   0.0570   1.0000
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