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SD7032-099-88 (sd7032-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: SD7032-099-88 (sd7032-il)
Reynolds number: 100,000
Max Cl/Cd: 58.02 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sd7032-il-100000-n5.txt
Download as CSV file: xf-sd7032-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3276   0.09961   0.09480  -0.0385   1.0000   0.0516
  -8.500  -0.3331   0.09708   0.09237  -0.0394   1.0000   0.0519
  -8.250  -0.3364   0.09001   0.08532  -0.0394   1.0000   0.0309
  -8.000  -0.3365   0.08776   0.08313  -0.0374   1.0000   0.0299
  -7.750  -0.3436   0.08562   0.08107  -0.0358   1.0000   0.0291
  -7.500  -0.3568   0.08364   0.07920  -0.0336   1.0000   0.0285
  -7.250  -0.3729   0.08194   0.07761  -0.0312   1.0000   0.0279
  -6.750  -0.3733   0.06694   0.06260  -0.0478   0.9912   0.0237
  -6.500  -0.3500   0.06025   0.05577  -0.0563   0.9843   0.0235
  -6.250  -0.3276   0.05212   0.04730  -0.0652   0.9759   0.0237
  -6.000  -0.3016   0.04555   0.04034  -0.0722   0.9697   0.0244
  -5.750  -0.2767   0.04342   0.03813  -0.0746   0.9628   0.0258
  -5.500  -0.2442   0.03729   0.03135  -0.0800   0.9579   0.0257
  -5.250  -0.2168   0.03310   0.02655  -0.0822   0.9507   0.0258
  -5.000  -0.1829   0.02977   0.02265  -0.0848   0.9458   0.0265
  -4.750  -0.1472   0.02714   0.01949  -0.0870   0.9417   0.0279
  -4.500  -0.1170   0.02534   0.01716  -0.0876   0.9345   0.0309
  -4.250  -0.0814   0.02334   0.01490  -0.0894   0.9304   0.0331
  -4.000  -0.0504   0.02203   0.01341  -0.0900   0.9240   0.0354
  -3.750  -0.0177   0.02107   0.01223  -0.0908   0.9177   0.0402
  -3.500   0.0181   0.01979   0.01092  -0.0923   0.9136   0.0443
  -3.250   0.0446   0.01911   0.01017  -0.0920   0.9044   0.0502
  -3.000   0.0795   0.01823   0.00922  -0.0932   0.8993   0.0578
  -2.750   0.1064   0.01759   0.00853  -0.0929   0.8899   0.0682
  -2.500   0.1405   0.01675   0.00783  -0.0940   0.8843   0.1040
  -2.250   0.1664   0.01606   0.00743  -0.0937   0.8743   0.1825
  -2.000   0.1951   0.01512   0.00720  -0.0942   0.8666   0.3575
  -1.750   0.2203   0.01441   0.00713  -0.0934   0.8576   0.5386
  -1.500   0.2436   0.01403   0.00705  -0.0917   0.8477   0.6581
  -1.250   0.2678   0.01368   0.00687  -0.0898   0.8395   0.7579
  -1.000   0.2890   0.01343   0.00670  -0.0873   0.8285   0.8399
  -0.750   0.3243   0.01313   0.00638  -0.0879   0.8184   0.9363
  -0.500   0.3628   0.01297   0.00602  -0.0897   0.8081   1.0000
  -0.250   0.3920   0.01293   0.00579  -0.0898   0.7971   1.0000
   0.000   0.4195   0.01294   0.00564  -0.0895   0.7841   1.0000
   0.250   0.4472   0.01295   0.00549  -0.0893   0.7710   1.0000
   0.500   0.4751   0.01297   0.00537  -0.0890   0.7575   1.0000
   0.750   0.5029   0.01301   0.00527  -0.0888   0.7437   1.0000
   1.000   0.5306   0.01305   0.00518  -0.0885   0.7293   1.0000
   1.250   0.5582   0.01312   0.00512  -0.0882   0.7145   1.0000
   1.500   0.5856   0.01320   0.00509  -0.0879   0.6993   1.0000
   1.750   0.6129   0.01330   0.00508  -0.0876   0.6837   1.0000
   2.000   0.6400   0.01342   0.00509  -0.0872   0.6678   1.0000
   2.250   0.6669   0.01357   0.00513  -0.0868   0.6517   1.0000
   2.500   0.6935   0.01373   0.00520  -0.0864   0.6351   1.0000
   2.750   0.7198   0.01392   0.00532  -0.0860   0.6180   1.0000
   3.000   0.7459   0.01412   0.00544  -0.0855   0.6007   1.0000
   3.250   0.7719   0.01435   0.00558  -0.0850   0.5834   1.0000
   3.500   0.7977   0.01459   0.00576  -0.0846   0.5659   1.0000
   3.750   0.8233   0.01485   0.00594  -0.0840   0.5484   1.0000
   4.000   0.8485   0.01512   0.00616  -0.0835   0.5303   1.0000
   4.250   0.8735   0.01542   0.00640  -0.0830   0.5121   1.0000
   4.500   0.8984   0.01573   0.00669  -0.0824   0.4946   1.0000
   4.750   0.9230   0.01606   0.00698  -0.0818   0.4773   1.0000
   5.000   0.9475   0.01642   0.00728  -0.0812   0.4604   1.0000
   5.250   0.9717   0.01679   0.00766  -0.0806   0.4435   1.0000
   5.500   0.9957   0.01717   0.00803  -0.0800   0.4266   1.0000
   5.750   1.0194   0.01757   0.00843  -0.0793   0.4102   1.0000
   6.000   1.0428   0.01800   0.00886  -0.0786   0.3939   1.0000
   6.250   1.0660   0.01845   0.00933  -0.0779   0.3780   1.0000
   6.500   1.0887   0.01892   0.00981  -0.0771   0.3621   1.0000
   6.750   1.1111   0.01941   0.01032  -0.0763   0.3466   1.0000
   7.000   1.1330   0.01993   0.01085  -0.0755   0.3309   1.0000
   7.250   1.1543   0.02047   0.01144  -0.0746   0.3152   1.0000
   7.500   1.1750   0.02105   0.01202  -0.0736   0.2996   1.0000
   7.750   1.1955   0.02164   0.01266  -0.0726   0.2838   1.0000
   8.000   1.2152   0.02226   0.01333  -0.0715   0.2680   1.0000
   8.250   1.2342   0.02292   0.01404  -0.0704   0.2523   1.0000
   8.500   1.2525   0.02361   0.01481  -0.0691   0.2368   1.0000
   8.750   1.2698   0.02434   0.01559  -0.0678   0.2215   1.0000
   9.000   1.2861   0.02512   0.01643  -0.0664   0.2064   1.0000
   9.250   1.3013   0.02596   0.01731  -0.0648   0.1917   1.0000
   9.500   1.3154   0.02685   0.01826  -0.0632   0.1777   1.0000
   9.750   1.3278   0.02779   0.01929  -0.0613   0.1644   1.0000
  10.000   1.3380   0.02880   0.02036  -0.0592   0.1521   1.0000
  10.250   1.3468   0.02992   0.02154  -0.0570   0.1400   1.0000
  10.500   1.3541   0.03117   0.02283  -0.0548   0.1284   1.0000
  10.750   1.3596   0.03257   0.02426  -0.0527   0.1181   1.0000
  11.000   1.3658   0.03402   0.02583  -0.0507   0.1078   1.0000
  11.250   1.3705   0.03564   0.02754  -0.0488   0.0988   1.0000
  11.500   1.3723   0.03753   0.02946  -0.0470   0.0915   1.0000
  11.750   1.3753   0.03945   0.03155  -0.0454   0.0844   1.0000
  12.000   1.3749   0.04172   0.03388  -0.0439   0.0790   1.0000
  12.250   1.3764   0.04398   0.03630  -0.0427   0.0733   1.0000
  12.500   1.3727   0.04677   0.03912  -0.0417   0.0693   1.0000
  12.750   1.3733   0.04939   0.04193  -0.0410   0.0649   1.0000
  13.000   1.3711   0.05235   0.04504  -0.0405   0.0610   1.0000
  13.250   1.3654   0.05581   0.04855  -0.0404   0.0581   1.0000
  13.500   1.3632   0.05911   0.05205  -0.0404   0.0550   1.0000
  13.750   1.3595   0.06269   0.05581  -0.0407   0.0519   1.0000
  14.000   1.3538   0.06666   0.05991  -0.0414   0.0495   1.0000
  14.250   1.3459   0.07099   0.06430  -0.0424   0.0474   1.0000
  14.500   1.3407   0.07526   0.06878  -0.0434   0.0452   1.0000
  14.750   1.3345   0.07985   0.07358  -0.0448   0.0429   1.0000
  15.000   1.3271   0.08474   0.07864  -0.0465   0.0410   1.0000
  15.250   1.3185   0.08995   0.08397  -0.0487   0.0393   1.0000
  15.500   1.3101   0.09514   0.08921  -0.0508   0.0377   1.0000
  15.750   1.3008   0.10091   0.09523  -0.0533   0.0362   1.0000
  16.000   1.2903   0.10712   0.10167  -0.0563   0.0347   1.0000
  16.250   1.2797   0.11348   0.10823  -0.0595   0.0333   1.0000
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