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SD2030-086-88 (sd2030-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: SD2030-086-88 (sd2030-il)
Reynolds number: 500,000
Max Cl/Cd: 80.98 at α=2.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sd2030-il-500000-n5.txt
Download as CSV file: xf-sd2030-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4648   0.08500   0.08273  -0.0348   1.0000   0.0095
  -9.000  -0.4744   0.08097   0.07874  -0.0354   1.0000   0.0095
  -8.750  -0.4880   0.07713   0.07496  -0.0356   1.0000   0.0097
  -8.500  -0.4995   0.07248   0.07035  -0.0383   0.9987   0.0097
  -8.250  -0.4950   0.06204   0.05984  -0.0533   0.9917   0.0096
  -8.000  -0.4892   0.05110   0.04869  -0.0640   0.9858   0.0096
  -7.750  -0.4842   0.03948   0.03661  -0.0703   0.9806   0.0098
  -7.500  -0.4802   0.02892   0.02527  -0.0723   0.9743   0.0100
  -7.250  -0.4577   0.02473   0.02055  -0.0736   0.9720   0.0105
  -7.000  -0.4311   0.02205   0.01745  -0.0746   0.9703   0.0109
  -6.750  -0.4116   0.02011   0.01518  -0.0737   0.9651   0.0111
  -6.500  -0.3860   0.01851   0.01329  -0.0737   0.9619   0.0113
  -6.250  -0.3577   0.01735   0.01189  -0.0742   0.9595   0.0116
  -6.000  -0.3283   0.01639   0.01074  -0.0748   0.9575   0.0117
  -5.750  -0.3054   0.01471   0.00883  -0.0741   0.9534   0.0122
  -5.500  -0.2807   0.01374   0.00773  -0.0737   0.9489   0.0126
  -5.250  -0.2532   0.01298   0.00689  -0.0738   0.9457   0.0130
  -5.000  -0.2247   0.01233   0.00615  -0.0741   0.9432   0.0133
  -4.750  -0.2001   0.01188   0.00566  -0.0735   0.9381   0.0139
  -4.500  -0.1737   0.01144   0.00518  -0.0733   0.9335   0.0146
  -4.250  -0.1459   0.01095   0.00463  -0.0733   0.9300   0.0150
  -4.000  -0.1199   0.01052   0.00414  -0.0729   0.9251   0.0154
  -3.750  -0.0937   0.01014   0.00369  -0.0726   0.9198   0.0159
  -3.500  -0.0655   0.00980   0.00329  -0.0726   0.9158   0.0164
  -3.250  -0.0391   0.00954   0.00298  -0.0722   0.9100   0.0171
  -3.000  -0.0119   0.00927   0.00266  -0.0720   0.9046   0.0183
  -2.750   0.0160   0.00902   0.00238  -0.0720   0.8995   0.0210
  -2.500   0.0427   0.00882   0.00218  -0.0717   0.8927   0.0257
  -2.250   0.0703   0.00851   0.00198  -0.0716   0.8869   0.0558
  -2.000   0.0965   0.00825   0.00184  -0.0714   0.8793   0.0920
  -1.750   0.1237   0.00797   0.00169  -0.0713   0.8723   0.1400
  -1.500   0.1495   0.00761   0.00158  -0.0710   0.8631   0.2182
  -1.250   0.1757   0.00730   0.00148  -0.0708   0.8538   0.2966
  -1.000   0.2008   0.00681   0.00139  -0.0705   0.8442   0.4318
  -0.750   0.2234   0.00617   0.00134  -0.0696   0.8336   0.6204
  -0.500   0.2456   0.00579   0.00140  -0.0682   0.8227   0.7596
  -0.250   0.2696   0.00569   0.00144  -0.0670   0.8117   0.8203
   0.000   0.2943   0.00568   0.00146  -0.0660   0.7997   0.8562
   0.250   0.3189   0.00569   0.00147  -0.0650   0.7869   0.8817
   0.500   0.3436   0.00572   0.00149  -0.0640   0.7732   0.9020
   0.750   0.3681   0.00576   0.00150  -0.0630   0.7577   0.9192
   1.000   0.3929   0.00582   0.00151  -0.0621   0.7394   0.9350
   1.250   0.4190   0.00590   0.00152  -0.0615   0.7186   0.9487
   1.500   0.4471   0.00600   0.00153  -0.0614   0.6933   0.9603
   1.750   0.4761   0.00615   0.00156  -0.0616   0.6617   0.9706
   2.000   0.5078   0.00637   0.00161  -0.0624   0.6213   0.9780
   2.250   0.5380   0.00665   0.00168  -0.0630   0.5733   0.9848
   2.500   0.5685   0.00702   0.00180  -0.0639   0.5169   0.9904
   2.750   0.5980   0.00744   0.00196  -0.0646   0.4571   0.9964
   3.000   0.6226   0.00785   0.00213  -0.0642   0.4030   1.0000
   3.250   0.6417   0.00819   0.00229  -0.0626   0.3634   1.0000
   3.500   0.6620   0.00854   0.00246  -0.0613   0.3237   1.0000
   3.750   0.6836   0.00889   0.00266  -0.0602   0.2871   1.0000
   4.250   0.7289   0.00956   0.00307  -0.0585   0.2262   1.0000
   4.500   0.7519   0.00992   0.00330  -0.0577   0.1976   1.0000
   4.750   0.7750   0.01028   0.00354  -0.0569   0.1707   1.0000
   5.000   0.7983   0.01064   0.00382  -0.0562   0.1466   1.0000
   5.250   0.8218   0.01100   0.00409  -0.0556   0.1274   1.0000
   5.500   0.8456   0.01133   0.00437  -0.0550   0.1116   1.0000
   5.750   0.8693   0.01167   0.00466  -0.0543   0.0972   1.0000
   6.000   0.8928   0.01204   0.00498  -0.0537   0.0837   1.0000
   6.250   0.9161   0.01242   0.00534  -0.0530   0.0722   1.0000
   6.500   0.9393   0.01282   0.00570  -0.0523   0.0618   1.0000
   6.750   0.9623   0.01322   0.00607  -0.0516   0.0526   1.0000
   7.000   0.9855   0.01361   0.00645  -0.0509   0.0449   1.0000
   7.250   1.0082   0.01403   0.00686  -0.0502   0.0386   1.0000
   7.500   1.0313   0.01442   0.00728  -0.0495   0.0342   1.0000
   7.750   1.0535   0.01487   0.00774  -0.0487   0.0293   1.0000
   8.000   1.0762   0.01527   0.00818  -0.0479   0.0262   1.0000
   8.250   1.0976   0.01579   0.00868  -0.0470   0.0210   1.0000
   8.500   1.1187   0.01632   0.00921  -0.0461   0.0155   1.0000
   8.750   1.1385   0.01698   0.00984  -0.0449   0.0104   1.0000
   9.000   1.1584   0.01761   0.01054  -0.0438   0.0082   1.0000
   9.250   1.1772   0.01835   0.01133  -0.0425   0.0068   1.0000
   9.500   1.1965   0.01900   0.01207  -0.0412   0.0063   1.0000
   9.750   1.2150   0.01968   0.01286  -0.0399   0.0059   1.0000
  10.000   1.2326   0.02042   0.01369  -0.0385   0.0056   1.0000
  10.250   1.2486   0.02122   0.01460  -0.0368   0.0052   1.0000
  10.500   1.2628   0.02205   0.01553  -0.0348   0.0050   1.0000
  10.750   1.2748   0.02300   0.01659  -0.0325   0.0047   1.0000
  11.000   1.2846   0.02409   0.01782  -0.0301   0.0045   1.0000
  11.250   1.2902   0.02548   0.01936  -0.0271   0.0043   1.0000
  11.500   1.2998   0.02655   0.02054  -0.0248   0.0041   1.0000
  11.750   1.3089   0.02766   0.02179  -0.0226   0.0040   1.0000
  12.000   1.3166   0.02887   0.02313  -0.0204   0.0039   1.0000
  12.250   1.3235   0.03018   0.02457  -0.0183   0.0038   1.0000
  12.500   1.3275   0.03172   0.02627  -0.0160   0.0037   1.0000
  12.750   1.3297   0.03346   0.02815  -0.0139   0.0037   1.0000
  13.000   1.3300   0.03544   0.03029  -0.0118   0.0036   1.0000
  13.250   1.3292   0.03758   0.03260  -0.0101   0.0035   1.0000
  13.500   1.3271   0.03998   0.03515  -0.0086   0.0035   1.0000
  13.750   1.3238   0.04263   0.03796  -0.0075   0.0034   1.0000
  14.000   1.3182   0.04570   0.04121  -0.0068   0.0034   1.0000
  14.250   1.3113   0.04917   0.04486  -0.0067   0.0033   1.0000
  14.500   1.3004   0.05341   0.04929  -0.0072   0.0033   1.0000
  14.750   1.2900   0.05801   0.05405  -0.0084   0.0033   1.0000
  15.000   1.2784   0.06323   0.05945  -0.0106   0.0032   1.0000
  15.250   1.2614   0.06991   0.06631  -0.0138   0.0033   1.0000
  15.500   1.2423   0.07767   0.07426  -0.0182   0.0033   1.0000
  15.750   1.2228   0.08614   0.08291  -0.0232   0.0033   1.0000
  16.000   1.2016   0.09547   0.09241  -0.0288   0.0033   1.0000
  16.250   1.1785   0.10543   0.10250  -0.0346   0.0034   1.0000
  16.500   1.1532   0.11615   0.11337  -0.0407   0.0034   1.0000
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