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SD7032-099-88 (sd7032-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: SD7032-099-88 (sd7032-il)
Reynolds number: 500,000
Max Cl/Cd: 97.81 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sd7032-il-500000-n5.txt
Download as CSV file: xf-sd7032-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD7032-099-88                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3392   0.09119   0.08894  -0.0372   1.0000   0.0063
  -9.000  -0.3431   0.08743   0.08521  -0.0379   1.0000   0.0063
  -8.750  -0.3443   0.08254   0.08036  -0.0405   0.9973   0.0065
  -8.500  -0.3359   0.07742   0.07525  -0.0456   0.9881   0.0064
  -8.250  -0.3277   0.07037   0.06821  -0.0537   0.9810   0.0065
  -8.000  -0.3196   0.06138   0.05922  -0.0664   0.9694   0.0065
  -7.750  -0.3635   0.02654   0.02315  -0.0970   0.9366   0.0064
  -7.500  -0.3497   0.02181   0.01770  -0.0974   0.9287   0.0066
  -7.250  -0.3304   0.01917   0.01464  -0.0974   0.9212   0.0070
  -7.000  -0.3066   0.01802   0.01327  -0.0972   0.9152   0.0072
  -6.750  -0.2822   0.01691   0.01196  -0.0970   0.9089   0.0075
  -6.500  -0.2573   0.01592   0.01077  -0.0967   0.9024   0.0077
  -6.250  -0.2319   0.01499   0.00964  -0.0964   0.8965   0.0081
  -6.000  -0.2061   0.01409   0.00856  -0.0961   0.8896   0.0086
  -5.750  -0.1801   0.01331   0.00759  -0.0958   0.8835   0.0091
  -5.500  -0.1536   0.01266   0.00680  -0.0955   0.8760   0.0096
  -5.250  -0.1274   0.01202   0.00605  -0.0953   0.8694   0.0102
  -5.000  -0.1002   0.01168   0.00567  -0.0951   0.8614   0.0110
  -4.750  -0.0731   0.01139   0.00529  -0.0949   0.8541   0.0122
  -4.500  -0.0457   0.01108   0.00490  -0.0947   0.8455   0.0133
  -4.250  -0.0187   0.01059   0.00435  -0.0946   0.8371   0.0146
  -4.000   0.0087   0.01029   0.00398  -0.0944   0.8278   0.0162
  -3.750   0.0363   0.01003   0.00364  -0.0943   0.8180   0.0177
  -3.500   0.0636   0.00971   0.00325  -0.0941   0.8080   0.0200
  -3.250   0.0912   0.00950   0.00297  -0.0940   0.7971   0.0223
  -3.000   0.1189   0.00932   0.00271  -0.0938   0.7854   0.0243
  -2.750   0.1465   0.00909   0.00243  -0.0937   0.7732   0.0278
  -2.500   0.1743   0.00895   0.00221  -0.0936   0.7606   0.0311
  -2.250   0.2019   0.00877   0.00201  -0.0934   0.7472   0.0416
  -2.000   0.2294   0.00858   0.00185  -0.0933   0.7334   0.0702
  -1.750   0.2568   0.00841   0.00173  -0.0933   0.7188   0.1071
  -1.500   0.2843   0.00824   0.00163  -0.0932   0.7038   0.1522
  -1.250   0.3115   0.00800   0.00156  -0.0932   0.6885   0.2263
  -1.000   0.3387   0.00781   0.00151  -0.0932   0.6730   0.2995
  -0.750   0.3659   0.00764   0.00148  -0.0932   0.6570   0.3755
  -0.500   0.3929   0.00743   0.00148  -0.0931   0.6413   0.4739
  -0.250   0.4194   0.00722   0.00153  -0.0929   0.6254   0.5831
   0.000   0.4459   0.00714   0.00157  -0.0926   0.6098   0.6523
   0.250   0.4724   0.00712   0.00161  -0.0922   0.5942   0.7025
   0.500   0.4984   0.00711   0.00166  -0.0917   0.5787   0.7517
   0.750   0.5238   0.00712   0.00172  -0.0910   0.5631   0.7977
   1.000   0.5485   0.00714   0.00177  -0.0901   0.5478   0.8411
   1.250   0.5719   0.00715   0.00181  -0.0890   0.5324   0.8855
   1.500   0.5982   0.00714   0.00183  -0.0884   0.5164   0.9482
   1.750   0.6305   0.00727   0.00186  -0.0894   0.4985   1.0000
   2.000   0.6575   0.00745   0.00194  -0.0892   0.4807   1.0000
   2.250   0.6844   0.00763   0.00202  -0.0891   0.4636   1.0000
   2.500   0.7114   0.00782   0.00212  -0.0889   0.4477   1.0000
   2.750   0.7382   0.00801   0.00222  -0.0888   0.4318   1.0000
   3.250   0.7917   0.00841   0.00246  -0.0885   0.4014   1.0000
   3.500   0.8183   0.00862   0.00261  -0.0883   0.3865   1.0000
   4.000   0.8713   0.00904   0.00291  -0.0879   0.3587   1.0000
   4.250   0.8976   0.00927   0.00309  -0.0877   0.3444   1.0000
   4.500   0.9239   0.00949   0.00327  -0.0875   0.3316   1.0000
   4.750   0.9500   0.00973   0.00346  -0.0873   0.3180   1.0000
   5.000   0.9759   0.00998   0.00367  -0.0870   0.3044   1.0000
   5.250   1.0016   0.01024   0.00389  -0.0867   0.2909   1.0000
   5.500   1.0270   0.01053   0.00412  -0.0864   0.2760   1.0000
   5.750   1.0523   0.01082   0.00437  -0.0861   0.2622   1.0000
   6.000   1.0774   0.01112   0.00464  -0.0857   0.2486   1.0000
   6.250   1.1022   0.01145   0.00492  -0.0853   0.2339   1.0000
   6.500   1.1266   0.01180   0.00522  -0.0849   0.2185   1.0000
   6.750   1.1505   0.01220   0.00554  -0.0843   0.2020   1.0000
   7.000   1.1743   0.01259   0.00589  -0.0838   0.1873   1.0000
   7.250   1.1983   0.01294   0.00623  -0.0833   0.1758   1.0000
   7.500   1.2218   0.01333   0.00659  -0.0828   0.1641   1.0000
   7.750   1.2448   0.01376   0.00698  -0.0821   0.1515   1.0000
   8.000   1.2676   0.01419   0.00741  -0.0815   0.1402   1.0000
   8.250   1.2896   0.01466   0.00785  -0.0807   0.1278   1.0000
   8.500   1.3112   0.01516   0.00832  -0.0799   0.1155   1.0000
   8.750   1.3320   0.01570   0.00882  -0.0790   0.1029   1.0000
   9.000   1.3521   0.01628   0.00936  -0.0780   0.0903   1.0000
   9.250   1.3714   0.01689   0.00995  -0.0769   0.0789   1.0000
   9.500   1.3897   0.01755   0.01057  -0.0756   0.0686   1.0000
   9.750   1.4078   0.01817   0.01120  -0.0743   0.0602   1.0000
  10.000   1.4247   0.01885   0.01187  -0.0729   0.0520   1.0000
  10.250   1.4395   0.01955   0.01256  -0.0711   0.0457   1.0000
  10.500   1.4530   0.02023   0.01327  -0.0691   0.0405   1.0000
  10.750   1.4655   0.02097   0.01403  -0.0670   0.0360   1.0000
  11.000   1.4776   0.02174   0.01484  -0.0650   0.0319   1.0000
  11.250   1.4885   0.02260   0.01572  -0.0629   0.0281   1.0000
  11.500   1.5002   0.02343   0.01661  -0.0610   0.0252   1.0000
  11.750   1.5091   0.02449   0.01769  -0.0590   0.0219   1.0000
  12.000   1.5198   0.02543   0.01871  -0.0572   0.0200   1.0000
  12.250   1.5276   0.02662   0.01993  -0.0553   0.0172   1.0000
  12.500   1.5357   0.02784   0.02122  -0.0535   0.0154   1.0000
  12.750   1.5425   0.02920   0.02266  -0.0518   0.0133   1.0000
  13.000   1.5479   0.03074   0.02426  -0.0502   0.0118   1.0000
  13.250   1.5536   0.03232   0.02593  -0.0488   0.0104   1.0000
  13.500   1.5560   0.03426   0.02794  -0.0474   0.0088   1.0000
  13.750   1.5593   0.03623   0.03001  -0.0462   0.0077   1.0000
  14.000   1.5594   0.03860   0.03247  -0.0452   0.0065   1.0000
  14.250   1.5599   0.04105   0.03503  -0.0444   0.0058   1.0000
  14.500   1.5589   0.04380   0.03789  -0.0439   0.0051   1.0000
  14.750   1.5567   0.04683   0.04103  -0.0437   0.0047   1.0000
  15.000   1.5518   0.05033   0.04465  -0.0438   0.0042   1.0000
  15.250   1.5483   0.05386   0.04832  -0.0441   0.0039   1.0000
  15.500   1.5431   0.05780   0.05239  -0.0449   0.0036   1.0000
  15.750   1.5368   0.06205   0.05677  -0.0459   0.0035   1.0000
  16.000   1.5282   0.06686   0.06173  -0.0473   0.0033   1.0000
  16.250   1.5190   0.07195   0.06696  -0.0490   0.0031   1.0000
  16.500   1.5084   0.07743   0.07258  -0.0511   0.0030   1.0000
  16.750   1.4956   0.08353   0.07882  -0.0536   0.0029   1.0000
  17.000   1.4827   0.08984   0.08528  -0.0563   0.0028   1.0000
  17.250   1.4698   0.09630   0.09189  -0.0593   0.0028   1.0000
  17.500   1.4564   0.10302   0.09876  -0.0625   0.0027   1.0000
  17.750   1.4426   0.10999   0.10588  -0.0659   0.0027   1.0000
  18.000   1.4277   0.11727   0.11331  -0.0696   0.0027   1.0000
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