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SD8020-010-88 (sd8020-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: SD8020-010-88 (sd8020-il)
Reynolds number: 200,000
Max Cl/Cd: 47.51 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sd8020-il-200000.txt
Download as CSV file: xf-sd8020-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.8482   0.06783   0.06382  -0.0344   1.0000   0.0277
 -12.000  -0.8787   0.06108   0.05681  -0.0389   1.0000   0.0273
 -11.750  -0.8983   0.05700   0.05250  -0.0401   1.0000   0.0270
 -11.500  -0.9155   0.05368   0.04897  -0.0395   1.0000   0.0269
 -11.250  -0.9322   0.05069   0.04577  -0.0373   1.0000   0.0268
 -11.000  -0.9481   0.04779   0.04264  -0.0339   1.0000   0.0268
 -10.750  -0.9575   0.04457   0.03913  -0.0310   1.0000   0.0269
 -10.500  -0.9641   0.04083   0.03506  -0.0282   1.0000   0.0271
 -10.250  -0.9640   0.03734   0.03127  -0.0258   1.0000   0.0275
 -10.000  -0.9564   0.03484   0.02858  -0.0238   1.0000   0.0283
  -9.750  -0.9446   0.03325   0.02687  -0.0220   1.0000   0.0296
  -9.500  -0.9315   0.03177   0.02519  -0.0202   1.0000   0.0312
  -9.250  -0.9181   0.03010   0.02325  -0.0183   1.0000   0.0329
  -9.000  -0.9029   0.02849   0.02134  -0.0163   1.0000   0.0342
  -8.750  -0.8880   0.02584   0.01845  -0.0145   1.0000   0.0358
  -8.500  -0.8710   0.02450   0.01711  -0.0131   1.0000   0.0383
  -8.250  -0.8527   0.02354   0.01603  -0.0115   1.0000   0.0415
  -8.000  -0.8334   0.02258   0.01488  -0.0099   1.0000   0.0441
  -7.750  -0.8177   0.02076   0.01308  -0.0080   1.0000   0.0479
  -7.500  -0.7988   0.02000   0.01225  -0.0064   1.0000   0.0533
  -7.250  -0.7824   0.01879   0.01104  -0.0045   1.0000   0.0595
  -7.000  -0.7638   0.01796   0.01013  -0.0027   1.0000   0.0682
  -6.750  -0.7460   0.01712   0.00931  -0.0009   1.0000   0.0806
  -6.500  -0.7284   0.01629   0.00854   0.0008   1.0000   0.0952
  -6.250  -0.7098   0.01561   0.00790   0.0024   1.0000   0.1104
  -6.000  -0.6905   0.01503   0.00737   0.0039   1.0000   0.1270
  -5.750  -0.6705   0.01453   0.00689   0.0053   1.0000   0.1467
  -5.500  -0.6514   0.01396   0.00645   0.0068   1.0000   0.1688
  -5.250  -0.6319   0.01346   0.00604   0.0083   1.0000   0.1947
  -5.000  -0.6124   0.01296   0.00565   0.0098   1.0000   0.2234
  -4.750  -0.5930   0.01249   0.00531   0.0113   1.0000   0.2549
  -4.500  -0.5734   0.01207   0.00502   0.0127   1.0000   0.2901
  -4.250  -0.5540   0.01167   0.00477   0.0142   1.0000   0.3265
  -4.000  -0.5345   0.01132   0.00454   0.0158   1.0000   0.3658
  -3.750  -0.5153   0.01098   0.00438   0.0173   1.0000   0.4065
  -3.500  -0.4960   0.01069   0.00425   0.0189   1.0000   0.4483
  -3.250  -0.4770   0.01043   0.00416   0.0206   1.0000   0.4913
  -3.000  -0.4582   0.01020   0.00410   0.0223   1.0000   0.5353
  -2.750  -0.4396   0.01001   0.00408   0.0241   1.0000   0.5794
  -2.500  -0.4214   0.00985   0.00410   0.0259   1.0000   0.6232
  -2.250  -0.4035   0.00973   0.00415   0.0278   1.0000   0.6665
  -2.000  -0.3858   0.00965   0.00422   0.0298   1.0000   0.7091
  -1.750  -0.3441   0.00968   0.00442   0.0271   0.9928   0.7574
  -1.500  -0.3016   0.00970   0.00457   0.0244   0.9850   0.8011
  -1.250  -0.2599   0.00971   0.00467   0.0220   0.9768   0.8403
  -1.000  -0.2116   0.00978   0.00482   0.0183   0.9708   0.8736
  -0.750  -0.1647   0.00987   0.00493   0.0149   0.9629   0.9008
  -0.500  -0.1086   0.00999   0.00506   0.0097   0.9579   0.9193
  -0.250  -0.0559   0.01007   0.00513   0.0052   0.9502   0.9333
   0.000   0.0001   0.01009   0.00514   0.0000   0.9436   0.9436
   0.250   0.0560   0.01007   0.00513  -0.0052   0.9333   0.9502
   0.500   0.1087   0.00999   0.00506  -0.0097   0.9192   0.9579
   0.750   0.1649   0.00986   0.00492  -0.0150   0.9005   0.9629
   1.000   0.2117   0.00978   0.00482  -0.0183   0.8736   0.9709
   1.250   0.2601   0.00970   0.00467  -0.0220   0.8402   0.9768
   1.500   0.3018   0.00970   0.00457  -0.0244   0.8012   0.9850
   1.750   0.3442   0.00968   0.00442  -0.0271   0.7575   0.9929
   2.000   0.3858   0.00965   0.00422  -0.0298   0.7092   1.0000
   2.250   0.4035   0.00973   0.00415  -0.0278   0.6669   1.0000
   2.500   0.4214   0.00985   0.00410  -0.0259   0.6239   1.0000
   2.750   0.4397   0.01001   0.00408  -0.0241   0.5800   1.0000
   3.000   0.4582   0.01020   0.00410  -0.0223   0.5358   1.0000
   3.250   0.4770   0.01043   0.00416  -0.0206   0.4920   1.0000
   3.500   0.4960   0.01069   0.00425  -0.0189   0.4485   1.0000
   3.750   0.5152   0.01098   0.00438  -0.0173   0.4063   1.0000
   4.000   0.5344   0.01132   0.00454  -0.0157   0.3658   1.0000
   4.250   0.5540   0.01167   0.00477  -0.0142   0.3265   1.0000
   4.500   0.5734   0.01207   0.00502  -0.0127   0.2900   1.0000
   4.750   0.5930   0.01249   0.00531  -0.0113   0.2548   1.0000
   5.000   0.6124   0.01296   0.00565  -0.0098   0.2233   1.0000
   5.250   0.6319   0.01345   0.00603  -0.0083   0.1947   1.0000
   5.500   0.6514   0.01396   0.00645  -0.0068   0.1685   1.0000
   5.750   0.6706   0.01452   0.00689  -0.0053   0.1466   1.0000
   6.000   0.6904   0.01504   0.00738  -0.0039   0.1269   1.0000
   6.250   0.7097   0.01562   0.00790  -0.0024   0.1101   1.0000
   6.500   0.7283   0.01631   0.00855  -0.0008   0.0951   1.0000
   6.750   0.7460   0.01713   0.00932   0.0010   0.0807   1.0000
   7.000   0.7639   0.01795   0.01013   0.0027   0.0683   1.0000
   7.250   0.7824   0.01879   0.01104   0.0045   0.0595   1.0000
   7.500   0.7988   0.02003   0.01228   0.0064   0.0533   1.0000
   7.750   0.8178   0.02078   0.01309   0.0080   0.0481   1.0000
   8.000   0.8334   0.02262   0.01491   0.0099   0.0442   1.0000
   8.250   0.8528   0.02355   0.01604   0.0115   0.0416   1.0000
   8.500   0.8710   0.02448   0.01708   0.0130   0.0384   1.0000
   8.750   0.8882   0.02582   0.01843   0.0145   0.0359   1.0000
   9.000   0.9029   0.02854   0.02138   0.0163   0.0343   1.0000
   9.250   0.9182   0.03010   0.02324   0.0182   0.0330   1.0000
   9.500   0.9316   0.03178   0.02521   0.0202   0.0313   1.0000
   9.750   0.9447   0.03321   0.02682   0.0220   0.0295   1.0000
  10.000   0.9564   0.03482   0.02856   0.0238   0.0283   1.0000
  10.250   0.9640   0.03736   0.03128   0.0258   0.0275   1.0000
  10.500   0.9635   0.04098   0.03520   0.0282   0.0270   1.0000
  10.750   0.9566   0.04474   0.03931   0.0310   0.0268   1.0000
  11.000   0.9473   0.04792   0.04277   0.0339   0.0268   1.0000
  11.250   0.9283   0.05120   0.04630   0.0374   0.0267   1.0000
  11.500   0.9139   0.05395   0.04925   0.0394   0.0268   1.0000
  11.750   0.8951   0.05752   0.05302   0.0399   0.0269   1.0000
  12.000   0.8779   0.06135   0.05706   0.0388   0.0271   1.0000
  12.250   0.8524   0.06729   0.06324   0.0349   0.0275   1.0000
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