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SD8020-010-88 (sd8020-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: SD8020-010-88 (sd8020-il)
Reynolds number: 100,000
Max Cl/Cd: 36.9 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sd8020-il-100000.txt
Download as CSV file: xf-sd8020-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD8020-010-88                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.7179   0.09382   0.08875  -0.0202   1.0000   0.0673
 -11.250  -0.7252   0.08734   0.08230  -0.0227   1.0000   0.0667
 -11.000  -0.7390   0.08039   0.07535  -0.0263   1.0000   0.0657
 -10.750  -0.7570   0.07366   0.06861  -0.0301   1.0000   0.0637
 -10.500  -0.7886   0.06691   0.06176  -0.0335   1.0000   0.0619
 -10.250  -0.8757   0.05903   0.05314  -0.0309   1.0000   0.0558
 -10.000  -0.8861   0.05554   0.04931  -0.0286   1.0000   0.0555
  -9.750  -0.8935   0.05100   0.04445  -0.0264   1.0000   0.0558
  -9.500  -0.8852   0.04772   0.04119  -0.0254   1.0000   0.0581
  -9.250  -0.8759   0.04548   0.03884  -0.0238   1.0000   0.0607
  -9.000  -0.8737   0.04204   0.03499  -0.0213   1.0000   0.0619
  -8.750  -0.8679   0.03869   0.03116  -0.0188   1.0000   0.0632
  -8.500  -0.8584   0.03576   0.02772  -0.0163   1.0000   0.0652
  -8.250  -0.8464   0.03308   0.02460  -0.0141   1.0000   0.0687
  -8.000  -0.8284   0.03124   0.02272  -0.0129   1.0000   0.0736
  -7.750  -0.8104   0.02920   0.02030  -0.0110   1.0000   0.0786
  -7.500  -0.7913   0.02731   0.01841  -0.0097   1.0000   0.0860
  -7.250  -0.7721   0.02560   0.01653  -0.0081   1.0000   0.0956
  -7.000  -0.7528   0.02416   0.01499  -0.0064   1.0000   0.1079
  -6.750  -0.7342   0.02290   0.01381  -0.0049   1.0000   0.1234
  -6.500  -0.7157   0.02185   0.01280  -0.0033   1.0000   0.1413
  -6.250  -0.6972   0.02097   0.01183  -0.0016   1.0000   0.1624
  -6.000  -0.6785   0.01998   0.01103  -0.0001   1.0000   0.1836
  -5.750  -0.6596   0.01910   0.01022   0.0015   1.0000   0.2084
  -5.500  -0.6407   0.01827   0.00949   0.0032   1.0000   0.2360
  -5.250  -0.6221   0.01747   0.00884   0.0049   1.0000   0.2670
  -5.000  -0.6038   0.01673   0.00827   0.0066   1.0000   0.3025
  -4.750  -0.5856   0.01605   0.00779   0.0085   1.0000   0.3419
  -4.500  -0.5674   0.01544   0.00738   0.0103   1.0000   0.3850
  -4.250  -0.5494   0.01489   0.00704   0.0123   1.0000   0.4305
  -4.000  -0.5313   0.01440   0.00675   0.0144   1.0000   0.4783
  -3.750  -0.5131   0.01399   0.00652   0.0165   1.0000   0.5278
  -3.500  -0.4949   0.01363   0.00639   0.0187   1.0000   0.5760
  -3.250  -0.4766   0.01335   0.00630   0.0210   1.0000   0.6245
  -3.000  -0.4582   0.01313   0.00623   0.0234   1.0000   0.6727
  -2.750  -0.4396   0.01298   0.00622   0.0259   1.0000   0.7196
  -2.500  -0.4204   0.01291   0.00627   0.0284   1.0000   0.7650
  -2.250  -0.3993   0.01292   0.00638   0.0306   1.0000   0.8092
  -2.000  -0.3722   0.01306   0.00656   0.0317   1.0000   0.8515
  -1.750  -0.3325   0.01340   0.00688   0.0305   1.0000   0.8895
  -1.500  -0.2789   0.01385   0.00723   0.0264   1.0000   0.9200
  -1.250  -0.2166   0.01427   0.00754   0.0203   1.0000   0.9436
  -1.000  -0.1453   0.01453   0.00767   0.0120   1.0000   0.9609
  -0.750  -0.0773   0.01457   0.00763   0.0040   1.0000   0.9784
  -0.500  -0.0075   0.01442   0.00742  -0.0047   1.0000   0.9942
  -0.250   0.0172   0.01417   0.00718  -0.0059   1.0000   1.0000
   0.000  -0.0001   0.01411   0.00713   0.0000   1.0000   1.0000
   0.250  -0.0172   0.01417   0.00718   0.0060   1.0000   1.0000
   0.500   0.0075   0.01442   0.00742   0.0047   0.9942   1.0000
   0.750   0.0770   0.01457   0.00763  -0.0039   0.9784   1.0000
   1.000   0.1454   0.01453   0.00767  -0.0120   0.9609   1.0000
   1.250   0.2167   0.01427   0.00754  -0.0203   0.9436   1.0000
   1.500   0.2789   0.01385   0.00723  -0.0264   0.9200   1.0000
   1.750   0.3324   0.01340   0.00688  -0.0305   0.8896   1.0000
   2.000   0.3723   0.01306   0.00656  -0.0317   0.8516   1.0000
   2.250   0.3992   0.01292   0.00638  -0.0306   0.8094   1.0000
   2.500   0.4204   0.01291   0.00627  -0.0283   0.7651   1.0000
   2.750   0.4396   0.01298   0.00622  -0.0259   0.7198   1.0000
   3.000   0.4582   0.01313   0.00623  -0.0234   0.6728   1.0000
   3.250   0.4766   0.01335   0.00630  -0.0210   0.6247   1.0000
   3.500   0.4949   0.01363   0.00639  -0.0187   0.5761   1.0000
   3.750   0.5131   0.01399   0.00652  -0.0165   0.5278   1.0000
   4.000   0.5313   0.01441   0.00675  -0.0143   0.4784   1.0000
   4.250   0.5494   0.01489   0.00704  -0.0123   0.4307   1.0000
   4.500   0.5674   0.01544   0.00738  -0.0103   0.3849   1.0000
   4.750   0.5855   0.01605   0.00779  -0.0084   0.3417   1.0000
   5.000   0.6037   0.01673   0.00827  -0.0066   0.3025   1.0000
   5.250   0.6221   0.01746   0.00884  -0.0049   0.2670   1.0000
   5.500   0.6407   0.01827   0.00948  -0.0032   0.2359   1.0000
   5.750   0.6595   0.01910   0.01021  -0.0015   0.2082   1.0000
   6.000   0.6784   0.01997   0.01103   0.0001   0.1833   1.0000
   6.250   0.6971   0.02097   0.01183   0.0016   0.1621   1.0000
   6.500   0.7157   0.02186   0.01281   0.0033   0.1411   1.0000
   6.750   0.7342   0.02292   0.01383   0.0049   0.1233   1.0000
   7.000   0.7529   0.02418   0.01501   0.0064   0.1079   1.0000
   7.250   0.7722   0.02561   0.01653   0.0080   0.0956   1.0000
   7.500   0.7913   0.02731   0.01842   0.0097   0.0860   1.0000
   7.750   0.8106   0.02922   0.02030   0.0109   0.0788   1.0000
   8.000   0.8284   0.03127   0.02275   0.0129   0.0738   1.0000
   8.250   0.8464   0.03309   0.02466   0.0142   0.0691   1.0000
   8.500   0.8586   0.03578   0.02773   0.0163   0.0653   1.0000
   8.750   0.8680   0.03870   0.03118   0.0188   0.0633   1.0000
   9.000   0.8737   0.04206   0.03501   0.0213   0.0620   1.0000
   9.250   0.8757   0.04553   0.03891   0.0238   0.0609   1.0000
   9.500   0.8851   0.04771   0.04120   0.0254   0.0582   1.0000
   9.750   0.8934   0.05111   0.04456   0.0264   0.0558   1.0000
  10.000   0.8865   0.05546   0.04923   0.0286   0.0556   1.0000
  10.250   0.8758   0.05903   0.05315   0.0309   0.0558   1.0000
  10.500   0.7900   0.06673   0.06157   0.0335   0.0615   1.0000
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