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SD2030-086-88 (sd2030-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: SD2030-086-88 (sd2030-il)
Reynolds number: 100,000
Max Cl/Cd: 52.8 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sd2030-il-100000-n5.txt
Download as CSV file: xf-sd2030-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD2030-086-88                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4463   0.10360   0.09849  -0.0360   1.0000   0.0581
  -9.250  -0.4514   0.10025   0.09521  -0.0379   1.0000   0.0583
  -9.000  -0.4573   0.09677   0.09181  -0.0395   1.0000   0.0584
  -8.750  -0.3805   0.07799   0.07329  -0.0395   1.0000   0.0334
  -8.500  -0.4629   0.08370   0.07879  -0.0403   1.0000   0.0336
  -8.250  -0.4680   0.08092   0.07607  -0.0391   1.0000   0.0329
  -8.000  -0.4790   0.07792   0.07316  -0.0387   1.0000   0.0325
  -7.750  -0.4874   0.07435   0.06963  -0.0390   1.0000   0.0319
  -7.500  -0.4955   0.07067   0.06595  -0.0391   1.0000   0.0313
  -7.250  -0.5026   0.06682   0.06209  -0.0390   1.0000   0.0308
  -7.000  -0.5080   0.06280   0.05800  -0.0388   1.0000   0.0302
  -6.750  -0.5114   0.05854   0.05363  -0.0384   1.0000   0.0296
  -6.500  -0.5121   0.05408   0.04899  -0.0379   1.0000   0.0290
  -6.250  -0.5098   0.04948   0.04412  -0.0373   1.0000   0.0284
  -6.000  -0.5039   0.04497   0.03928  -0.0365   1.0000   0.0279
  -5.750  -0.4944   0.04081   0.03471  -0.0356   1.0000   0.0277
  -5.500  -0.4744   0.03713   0.03058  -0.0362   0.9981   0.0281
  -5.250  -0.4459   0.03414   0.02711  -0.0378   0.9946   0.0301
  -5.000  -0.4177   0.03115   0.02356  -0.0388   0.9912   0.0310
  -4.750  -0.3884   0.02841   0.02028  -0.0397   0.9878   0.0312
  -4.500  -0.3574   0.02621   0.01761  -0.0405   0.9849   0.0315
  -4.250  -0.3260   0.02444   0.01541  -0.0413   0.9822   0.0320
  -4.000  -0.2970   0.02300   0.01369  -0.0416   0.9784   0.0328
  -3.750  -0.2664   0.02184   0.01232  -0.0421   0.9750   0.0338
  -3.500  -0.2352   0.02062   0.01104  -0.0430   0.9720   0.0356
  -3.250  -0.2047   0.01998   0.01039  -0.0439   0.9683   0.0401
  -3.000  -0.1763   0.01938   0.00963  -0.0442   0.9635   0.0449
  -2.750  -0.1452   0.01859   0.00882  -0.0450   0.9597   0.0514
  -2.500  -0.1115   0.01793   0.00816  -0.0463   0.9566   0.0685
  -2.250  -0.0859   0.01731   0.00774  -0.0462   0.9508   0.1146
  -2.000  -0.0585   0.01609   0.00757  -0.0470   0.9467   0.3254
  -1.750  -0.0342   0.01486   0.00768  -0.0462   0.9434   0.6512
  -1.500  -0.0141   0.01465   0.00791  -0.0431   0.9377   0.8422
  -1.250   0.0404   0.01469   0.00789  -0.0475   0.9370   0.9596
  -1.000   0.0970   0.01471   0.00768  -0.0535   0.9356   1.0000
  -0.750   0.1314   0.01473   0.00753  -0.0551   0.9304   1.0000
  -0.500   0.1577   0.01475   0.00741  -0.0550   0.9225   1.0000
  -0.250   0.1923   0.01475   0.00729  -0.0566   0.9169   1.0000
   0.000   0.2201   0.01476   0.00720  -0.0567   0.9088   1.0000
   0.250   0.2567   0.01471   0.00707  -0.0584   0.9030   1.0000
   0.500   0.2852   0.01468   0.00698  -0.0585   0.8940   1.0000
   1.000   0.3511   0.01448   0.00671  -0.0603   0.8777   1.0000
   1.250   0.3829   0.01437   0.00658  -0.0608   0.8686   1.0000
   1.500   0.4186   0.01418   0.00638  -0.0619   0.8601   1.0000
   1.750   0.4464   0.01407   0.00628  -0.0616   0.8480   1.0000
   2.000   0.4754   0.01395   0.00619  -0.0614   0.8354   1.0000
   2.250   0.5046   0.01382   0.00608  -0.0613   0.8219   1.0000
   2.500   0.5338   0.01370   0.00598  -0.0610   0.8070   1.0000
   2.750   0.5634   0.01357   0.00587  -0.0609   0.7904   1.0000
   3.000   0.5896   0.01351   0.00588  -0.0601   0.7701   1.0000
   3.250   0.6180   0.01343   0.00581  -0.0597   0.7477   1.0000
   3.500   0.6442   0.01341   0.00580  -0.0588   0.7203   1.0000
   3.750   0.6704   0.01342   0.00582  -0.0580   0.6863   1.0000
   4.000   0.6970   0.01348   0.00580  -0.0571   0.6428   1.0000
   4.250   0.7220   0.01369   0.00582  -0.0560   0.5879   1.0000
   4.500   0.7439   0.01409   0.00595  -0.0545   0.5247   1.0000
   4.750   0.7633   0.01466   0.00621  -0.0527   0.4614   1.0000
   5.000   0.7816   0.01531   0.00662  -0.0510   0.4022   1.0000
   5.250   0.7999   0.01600   0.00706  -0.0493   0.3490   1.0000
   5.500   0.8186   0.01669   0.00756  -0.0478   0.3015   1.0000
   5.750   0.8375   0.01741   0.00809  -0.0464   0.2593   1.0000
   6.000   0.8566   0.01814   0.00867  -0.0451   0.2223   1.0000
   6.250   0.8761   0.01887   0.00930  -0.0439   0.1906   1.0000
   6.500   0.8954   0.01964   0.01003  -0.0426   0.1624   1.0000
   6.750   0.9144   0.02046   0.01076  -0.0414   0.1396   1.0000
   7.000   0.9337   0.02127   0.01157  -0.0401   0.1214   1.0000
   7.250   0.9525   0.02213   0.01243  -0.0388   0.1061   1.0000
   7.500   0.9709   0.02304   0.01336  -0.0375   0.0941   1.0000
   7.750   0.9885   0.02407   0.01441  -0.0361   0.0857   1.0000
   8.000   1.0064   0.02505   0.01551  -0.0347   0.0774   1.0000
   8.250   1.0244   0.02611   0.01669  -0.0333   0.0698   1.0000
   8.500   1.0409   0.02729   0.01791  -0.0319   0.0640   1.0000
   8.750   1.0587   0.02848   0.01928  -0.0305   0.0574   1.0000
   9.000   1.0734   0.02971   0.02053  -0.0290   0.0513   1.0000
   9.250   1.0899   0.03065   0.02170  -0.0276   0.0435   1.0000
   9.500   1.1029   0.03194   0.02310  -0.0259   0.0377   1.0000
   9.750   1.1157   0.03334   0.02474  -0.0240   0.0327   1.0000
  10.000   1.1233   0.03496   0.02641  -0.0218   0.0291   1.0000
  10.250   1.1342   0.03662   0.02838  -0.0198   0.0252   1.0000
  10.500   1.1415   0.03835   0.03028  -0.0176   0.0231   1.0000
  10.750   1.1457   0.04035   0.03240  -0.0153   0.0218   1.0000
  11.000   1.1479   0.04301   0.03525  -0.0130   0.0207   1.0000
  11.250   1.1497   0.04581   0.03842  -0.0108   0.0198   1.0000
  11.500   1.1476   0.04884   0.04179  -0.0087   0.0192   1.0000
  11.750   1.1415   0.05213   0.04540  -0.0067   0.0186   1.0000
  12.000   1.1326   0.05569   0.04926  -0.0053   0.0183   1.0000
  12.250   1.1204   0.05964   0.05350  -0.0044   0.0180   1.0000
  12.500   1.1058   0.06406   0.05819  -0.0044   0.0178   1.0000
  12.750   1.0885   0.06916   0.06355  -0.0054   0.0178   1.0000
  13.000   1.0682   0.07527   0.06990  -0.0078   0.0177   1.0000
  13.250   1.0451   0.08266   0.07751  -0.0118   0.0179   1.0000
  13.500   1.0191   0.09178   0.08685  -0.0177   0.0183   1.0000
  13.750   0.9913   0.10275   0.09797  -0.0252   0.0189   1.0000
  14.000   0.9621   0.11549   0.11082  -0.0335   0.0196   1.0000
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