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SD7032-099-88 (sd7032-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: SD7032-099-88 (sd7032-il)
Reynolds number: 100,000
Max Cl/Cd: 56.3 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sd7032-il-100000.txt
Download as CSV file: xf-sd7032-il-100000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3225   0.10437   0.09952  -0.0353   1.0000   0.0817
  -8.750  -0.3161   0.10156   0.09675  -0.0345   1.0000   0.0842
  -8.500  -0.3159   0.09904   0.09429  -0.0344   1.0000   0.0873
  -8.250  -0.3219   0.09701   0.09236  -0.0349   1.0000   0.0901
  -8.000  -0.3423   0.09618   0.09167  -0.0355   1.0000   0.0918
  -7.750  -0.3671   0.09568   0.09133  -0.0341   1.0000   0.0922
  -7.500  -0.3902   0.09447   0.09024  -0.0351   1.0000   0.0926
  -7.250  -0.3727   0.08950   0.08530  -0.0291   1.0000   0.0949
  -7.000  -0.3716   0.08735   0.08318  -0.0261   1.0000   0.0971
  -6.750  -0.3794   0.08555   0.08145  -0.0241   1.0000   0.0992
  -6.500  -0.3900   0.08352   0.07950  -0.0234   1.0000   0.1020
  -6.250  -0.4036   0.08105   0.07709  -0.0268   1.0000   0.1053
  -6.000  -0.4145   0.07672   0.07273  -0.0348   1.0000   0.1077
  -5.750  -0.4106   0.07444   0.07055  -0.0285   1.0000   0.1097
  -5.500  -0.4081   0.07229   0.06844  -0.0260   1.0000   0.1130
  -5.250  -0.4025   0.06738   0.06328  -0.0367   1.0000   0.1223
  -5.000  -0.3987   0.06505   0.06111  -0.0319   1.0000   0.1246
  -4.750  -0.3860   0.06134   0.05720  -0.0371   1.0000   0.1373
  -4.500  -0.3734   0.05928   0.05530  -0.0340   0.9981   0.1430
  -4.250  -0.3303   0.05430   0.05003  -0.0440   0.9910   0.1676
  -4.000  -0.2941   0.05071   0.04640  -0.0481   0.9846   0.1843
  -3.750  -0.2115   0.03482   0.02836  -0.0637   0.9832   0.0761
  -3.500  -0.1683   0.03018   0.02284  -0.0668   0.9776   0.0680
  -3.250  -0.1234   0.02812   0.02040  -0.0704   0.9718   0.0718
  -3.000  -0.0832   0.02605   0.01783  -0.0724   0.9645   0.0725
  -2.750  -0.0372   0.02477   0.01609  -0.0753   0.9582   0.0784
  -2.500  -0.0009   0.02327   0.01461  -0.0769   0.9499   0.0856
  -2.250   0.0444   0.02218   0.01353  -0.0800   0.9435   0.1007
  -2.000   0.0791   0.02116   0.01265  -0.0811   0.9338   0.1264
  -1.750   0.1206   0.01870   0.01207  -0.0841   0.9288   0.4970
  -1.500   0.1386   0.01802   0.01231  -0.0805   0.9179   0.7739
  -1.250   0.1872   0.01758   0.01192  -0.0830   0.9103   1.0000
  -1.000   0.2312   0.01760   0.01161  -0.0861   0.9009   1.0000
  -0.750   0.2689   0.01764   0.01139  -0.0880   0.8898   1.0000
  -0.500   0.3221   0.01747   0.01096  -0.0923   0.8841   1.0000
  -0.250   0.3553   0.01745   0.01077  -0.0931   0.8720   1.0000
   0.000   0.3898   0.01739   0.01055  -0.0941   0.8606   1.0000
   0.250   0.4282   0.01720   0.01023  -0.0954   0.8512   1.0000
   0.500   0.4659   0.01695   0.00985  -0.0965   0.8416   1.0000
   0.750   0.4964   0.01683   0.00964  -0.0965   0.8290   1.0000
   1.000   0.5275   0.01668   0.00940  -0.0964   0.8167   1.0000
   1.250   0.5590   0.01649   0.00913  -0.0963   0.8047   1.0000
   1.500   0.5908   0.01627   0.00883  -0.0962   0.7930   1.0000
   1.750   0.6229   0.01601   0.00849  -0.0961   0.7813   1.0000
   2.000   0.6521   0.01586   0.00827  -0.0955   0.7675   1.0000
   2.250   0.6804   0.01577   0.00811  -0.0949   0.7529   1.0000
   2.500   0.7077   0.01575   0.00802  -0.0942   0.7370   1.0000
   2.750   0.7344   0.01577   0.00801  -0.0934   0.7202   1.0000
   3.000   0.7613   0.01581   0.00799  -0.0927   0.7030   1.0000
   3.250   0.7883   0.01587   0.00797  -0.0920   0.6856   1.0000
   3.500   0.8155   0.01595   0.00797  -0.0913   0.6681   1.0000
   3.750   0.8429   0.01605   0.00800  -0.0907   0.6507   1.0000
   4.000   0.8678   0.01629   0.00820  -0.0898   0.6308   1.0000
   4.250   0.8935   0.01651   0.00835  -0.0891   0.6116   1.0000
   4.500   0.9197   0.01674   0.00852  -0.0884   0.5932   1.0000
   4.750   0.9447   0.01705   0.00879  -0.0876   0.5737   1.0000
   5.000   0.9694   0.01738   0.00909  -0.0868   0.5542   1.0000
   5.250   0.9946   0.01772   0.00936  -0.0861   0.5354   1.0000
   5.500   1.0196   0.01811   0.00971  -0.0854   0.5170   1.0000
   5.750   1.0431   0.01854   0.01016  -0.0845   0.4972   1.0000
   6.000   1.0674   0.01897   0.01056  -0.0838   0.4785   1.0000
   6.250   1.0918   0.01944   0.01095  -0.0830   0.4605   1.0000
   6.500   1.1148   0.01995   0.01150  -0.0822   0.4415   1.0000
   6.750   1.1375   0.02047   0.01204  -0.0812   0.4225   1.0000
   7.000   1.1605   0.02100   0.01254  -0.0804   0.4042   1.0000
   7.250   1.1836   0.02157   0.01306  -0.0795   0.3863   1.0000
   7.500   1.2043   0.02217   0.01375  -0.0784   0.3672   1.0000
   7.750   1.2253   0.02278   0.01439  -0.0773   0.3486   1.0000
   8.000   1.2463   0.02341   0.01499  -0.0762   0.3307   1.0000
   8.250   1.2669   0.02410   0.01563  -0.0751   0.3132   1.0000
   8.500   1.2849   0.02479   0.01647  -0.0737   0.2947   1.0000
   8.750   1.3028   0.02552   0.01725  -0.0723   0.2768   1.0000
   9.000   1.3202   0.02627   0.01801  -0.0708   0.2593   1.0000
   9.250   1.3371   0.02712   0.01881  -0.0693   0.2422   1.0000
   9.500   1.3508   0.02804   0.01983  -0.0674   0.2244   1.0000
   9.750   1.3636   0.02904   0.02093  -0.0654   0.2067   1.0000
  10.000   1.3749   0.03011   0.02200  -0.0633   0.1895   1.0000
  10.250   1.3853   0.03133   0.02318  -0.0612   0.1733   1.0000
  10.500   1.3957   0.03277   0.02454  -0.0591   0.1580   1.0000
  10.750   1.4035   0.03425   0.02602  -0.0568   0.1441   1.0000
  11.000   1.4080   0.03567   0.02755  -0.0540   0.1324   1.0000
  11.250   1.4128   0.03733   0.02935  -0.0513   0.1218   1.0000
  11.500   1.4184   0.03914   0.03127  -0.0491   0.1125   1.0000
  11.750   1.4282   0.04106   0.03310  -0.0475   0.1037   1.0000
  12.000   1.4284   0.04294   0.03525  -0.0449   0.0968   1.0000
  12.250   1.4355   0.04518   0.03751  -0.0433   0.0898   1.0000
  12.500   1.4358   0.04735   0.03987  -0.0413   0.0840   1.0000
  12.750   1.4422   0.04994   0.04250  -0.0399   0.0780   1.0000
  13.000   1.4370   0.05263   0.04549  -0.0380   0.0737   1.0000
  13.250   1.4474   0.05544   0.04817  -0.0372   0.0676   1.0000
  13.500   1.4346   0.05868   0.05181  -0.0355   0.0651   1.0000
  13.750   1.4250   0.06212   0.05553  -0.0345   0.0621   1.0000
  14.000   1.4354   0.06532   0.05854  -0.0341   0.0567   1.0000
  14.250   1.4171   0.06949   0.06309  -0.0337   0.0556   1.0000
  14.500   1.3990   0.07427   0.06822  -0.0340   0.0545   1.0000
  14.750   1.3807   0.07958   0.07385  -0.0350   0.0533   1.0000
  15.000   1.3614   0.08541   0.07996  -0.0367   0.0525   1.0000
  15.250   1.3402   0.09190   0.08671  -0.0392   0.0520   1.0000
  15.500   1.3150   0.09952   0.09461  -0.0429   0.0522   1.0000
  15.750   1.2859   0.10849   0.10385  -0.0479   0.0531   1.0000
  16.000   1.2559   0.11850   0.11408  -0.0540   0.0543   1.0000
  16.250   1.2271   0.12909   0.12482  -0.0607   0.0556   1.0000
  16.500   1.2004   0.14014   0.13596  -0.0676   0.0566   1.0000
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