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SD7032-099-88 (sd7032-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: SD7032-099-88 (sd7032-il)
Reynolds number: 200,000
Max Cl/Cd: 75.15 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sd7032-il-200000-n5.txt
Download as CSV file: xf-sd7032-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3375   0.08589   0.08257  -0.0374   1.0000   0.0174
  -8.000  -0.3462   0.08403   0.08078  -0.0354   1.0000   0.0171
  -7.750  -0.3414   0.08047   0.07726  -0.0379   0.9961   0.0165
  -7.500  -0.3301   0.07516   0.07196  -0.0443   0.9878   0.0158
  -7.000  -0.2967   0.04927   0.04579  -0.0790   0.9677   0.0132
  -6.750  -0.2777   0.04057   0.03669  -0.0874   0.9598   0.0130
  -6.500  -0.2588   0.03334   0.02884  -0.0923   0.9518   0.0130
  -6.250  -0.2347   0.02776   0.02244  -0.0952   0.9455   0.0132
  -6.000  -0.2091   0.02460   0.01879  -0.0965   0.9397   0.0136
  -5.750  -0.1828   0.02296   0.01691  -0.0971   0.9333   0.0143
  -5.500  -0.1524   0.02181   0.01555  -0.0981   0.9290   0.0156
  -5.250  -0.1269   0.02034   0.01369  -0.0978   0.9217   0.0172
  -5.000  -0.0978   0.01884   0.01179  -0.0979   0.9161   0.0180
  -4.750  -0.0716   0.01739   0.01023  -0.0979   0.9096   0.0191
  -4.500  -0.0445   0.01648   0.00923  -0.0977   0.9027   0.0205
  -4.250  -0.0165   0.01578   0.00839  -0.0976   0.8964   0.0229
  -4.000   0.0096   0.01494   0.00748  -0.0972   0.8885   0.0255
  -3.750   0.0371   0.01429   0.00677  -0.0971   0.8816   0.0278
  -3.500   0.0640   0.01384   0.00622  -0.0967   0.8732   0.0313
  -3.250   0.0910   0.01323   0.00557  -0.0965   0.8652   0.0352
  -3.000   0.1186   0.01284   0.00509  -0.0963   0.8568   0.0400
  -2.750   0.1456   0.01241   0.00465  -0.0960   0.8473   0.0481
  -2.500   0.1735   0.01200   0.00422  -0.0957   0.8387   0.0656
  -2.250   0.2004   0.01152   0.00392  -0.0956   0.8285   0.1167
  -2.000   0.2273   0.01110   0.00371  -0.0955   0.8179   0.1880
  -1.750   0.2542   0.01066   0.00353  -0.0954   0.8074   0.2788
  -1.500   0.2803   0.01009   0.00342  -0.0951   0.7965   0.4239
  -1.250   0.3054   0.00969   0.00338  -0.0945   0.7842   0.5498
  -1.000   0.3304   0.00944   0.00335  -0.0935   0.7717   0.6384
  -0.750   0.3544   0.00925   0.00331  -0.0923   0.7587   0.7157
  -0.500   0.3781   0.00913   0.00325  -0.0908   0.7452   0.7768
  -0.250   0.4010   0.00903   0.00318  -0.0892   0.7313   0.8323
   0.000   0.4251   0.00893   0.00308  -0.0878   0.7169   0.8908
   0.250   0.4620   0.00884   0.00291  -0.0893   0.7014   0.9727
   0.500   0.4912   0.00892   0.00284  -0.0895   0.6855   1.0000
   0.750   0.5184   0.00903   0.00281  -0.0893   0.6696   1.0000
   1.000   0.5454   0.00917   0.00280  -0.0890   0.6534   1.0000
   1.250   0.5723   0.00931   0.00281  -0.0888   0.6373   1.0000
   1.500   0.5991   0.00947   0.00283  -0.0885   0.6210   1.0000
   1.750   0.6259   0.00963   0.00289  -0.0883   0.6043   1.0000
   2.000   0.6525   0.00980   0.00295  -0.0880   0.5877   1.0000
   2.250   0.6790   0.00999   0.00303  -0.0877   0.5706   1.0000
   2.500   0.7053   0.01019   0.00314  -0.0874   0.5535   1.0000
   2.750   0.7314   0.01040   0.00325  -0.0870   0.5360   1.0000
   3.000   0.7573   0.01063   0.00338  -0.0867   0.5185   1.0000
   3.250   0.7832   0.01086   0.00352  -0.0863   0.5007   1.0000
   3.500   0.8090   0.01110   0.00370  -0.0859   0.4834   1.0000
   3.750   0.8346   0.01135   0.00388  -0.0856   0.4664   1.0000
   4.000   0.8601   0.01162   0.00407  -0.0852   0.4499   1.0000
   4.250   0.8855   0.01189   0.00430  -0.0848   0.4336   1.0000
   4.500   0.9106   0.01218   0.00453  -0.0844   0.4176   1.0000
   4.750   0.9356   0.01248   0.00478  -0.0839   0.4021   1.0000
   5.000   0.9605   0.01279   0.00505  -0.0835   0.3869   1.0000
   5.250   0.9852   0.01311   0.00535  -0.0830   0.3716   1.0000
   5.500   1.0097   0.01344   0.00565  -0.0825   0.3567   1.0000
   5.750   1.0341   0.01378   0.00597  -0.0820   0.3420   1.0000
   6.000   1.0581   0.01414   0.00631  -0.0815   0.3270   1.0000
   6.250   1.0819   0.01452   0.00669  -0.0809   0.3121   1.0000
   6.500   1.1053   0.01492   0.00707  -0.0803   0.2966   1.0000
   6.750   1.1284   0.01533   0.00747  -0.0796   0.2813   1.0000
   7.000   1.1511   0.01577   0.00790  -0.0789   0.2662   1.0000
   7.250   1.1734   0.01622   0.00837  -0.0782   0.2508   1.0000
   7.500   1.1953   0.01671   0.00884  -0.0774   0.2353   1.0000
   7.750   1.2166   0.01722   0.00934  -0.0765   0.2198   1.0000
   8.000   1.2374   0.01776   0.00987  -0.0756   0.2044   1.0000
   8.250   1.2577   0.01832   0.01046  -0.0746   0.1902   1.0000
   8.500   1.2776   0.01891   0.01105  -0.0736   0.1770   1.0000
   8.750   1.2967   0.01953   0.01168  -0.0725   0.1639   1.0000
   9.000   1.3150   0.02018   0.01236  -0.0713   0.1507   1.0000
   9.250   1.3324   0.02088   0.01307  -0.0700   0.1377   1.0000
   9.500   1.3487   0.02162   0.01385  -0.0685   0.1251   1.0000
   9.750   1.3630   0.02241   0.01464  -0.0667   0.1126   1.0000
  10.000   1.3755   0.02325   0.01550  -0.0648   0.1010   1.0000
  10.250   1.3866   0.02418   0.01644  -0.0627   0.0905   1.0000
  10.750   1.4064   0.02626   0.01858  -0.0585   0.0726   1.0000
  11.000   1.4149   0.02743   0.01980  -0.0565   0.0661   1.0000
  11.250   1.4224   0.02871   0.02115  -0.0545   0.0599   1.0000
  11.500   1.4293   0.03006   0.02259  -0.0526   0.0551   1.0000
  11.750   1.4359   0.03150   0.02413  -0.0509   0.0506   1.0000
  12.000   1.4383   0.03333   0.02599  -0.0490   0.0469   1.0000
  12.250   1.4450   0.03487   0.02770  -0.0476   0.0437   1.0000
  12.500   1.4486   0.03675   0.02968  -0.0463   0.0402   1.0000
  12.750   1.4482   0.03909   0.03207  -0.0450   0.0371   1.0000
  13.000   1.4535   0.04100   0.03414  -0.0441   0.0336   1.0000
  13.250   1.4542   0.04344   0.03665  -0.0434   0.0305   1.0000
  13.500   1.4530   0.04621   0.03951  -0.0429   0.0280   1.0000
  13.750   1.4548   0.04879   0.04227  -0.0426   0.0254   1.0000
  14.000   1.4527   0.05193   0.04552  -0.0427   0.0233   1.0000
  14.250   1.4464   0.05574   0.04944  -0.0431   0.0219   1.0000
  14.500   1.4438   0.05926   0.05313  -0.0435   0.0205   1.0000
  14.750   1.4391   0.06320   0.05724  -0.0444   0.0192   1.0000
  15.000   1.4326   0.06759   0.06177  -0.0456   0.0179   1.0000
  15.250   1.4234   0.07258   0.06689  -0.0472   0.0170   1.0000
  15.500   1.4121   0.07812   0.07256  -0.0493   0.0162   1.0000
  15.750   1.4035   0.08341   0.07803  -0.0513   0.0153   1.0000
  16.000   1.3937   0.08908   0.08388  -0.0537   0.0143   1.0000
  16.250   1.3824   0.09517   0.09012  -0.0564   0.0137   1.0000
  16.500   1.3704   0.10158   0.09668  -0.0594   0.0132   1.0000
  16.750   1.3567   0.10850   0.10373  -0.0629   0.0127   1.0000
  17.000   1.3426   0.11567   0.11104  -0.0665   0.0123   1.0000
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