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SD8040 (10%) (sd8040-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: SD8040 (10%) (sd8040-il)
Reynolds number: 500,000
Max Cl/Cd: 91.6 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sd8040-il-500000.txt
Download as CSV file: xf-sd8040-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD8040 (10%)                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4087   0.09660   0.09421  -0.0283   1.0000   0.0225
  -9.500  -0.4049   0.09345   0.09108  -0.0294   1.0000   0.0229
  -9.250  -0.4028   0.09003   0.08769  -0.0308   1.0000   0.0235
  -9.000  -0.3505   0.06889   0.06677  -0.0397   1.0000   0.0262
  -8.750  -0.3476   0.06621   0.06411  -0.0395   1.0000   0.0265
  -8.500  -0.3473   0.06320   0.06113  -0.0397   1.0000   0.0268
  -8.250  -0.3501   0.06030   0.05827  -0.0396   1.0000   0.0272
  -8.000  -0.3671   0.05688   0.05490  -0.0388   1.0000   0.0273
  -7.750  -0.3950   0.05210   0.05018  -0.0403   0.9980   0.0271
  -7.500  -0.3941   0.04175   0.03970  -0.0549   0.9911   0.0274
  -7.250  -0.3833   0.03410   0.03186  -0.0627   0.9864   0.0281
  -7.000  -0.4420   0.02816   0.02409  -0.0686   0.9811   0.0220
  -6.750  -0.4144   0.02432   0.01997  -0.0701   0.9775   0.0196
  -6.500  -0.3838   0.02026   0.01526  -0.0719   0.9750   0.0190
  -6.250  -0.3495   0.01809   0.01275  -0.0737   0.9732   0.0191
  -6.000  -0.3209   0.01647   0.01087  -0.0739   0.9684   0.0191
  -5.750  -0.2899   0.01531   0.00955  -0.0746   0.9643   0.0195
  -5.500  -0.2575   0.01432   0.00845  -0.0755   0.9609   0.0201
  -5.250  -0.2301   0.01357   0.00760  -0.0753   0.9552   0.0207
  -5.000  -0.2027   0.01297   0.00690  -0.0749   0.9492   0.0213
  -4.750  -0.1766   0.01205   0.00595  -0.0745   0.9438   0.0223
  -4.500  -0.1525   0.01159   0.00548  -0.0736   0.9358   0.0235
  -4.250  -0.1263   0.01123   0.00508  -0.0730   0.9299   0.0253
  -4.000  -0.1024   0.01068   0.00451  -0.0720   0.9214   0.0273
  -3.750  -0.0768   0.01031   0.00410  -0.0712   0.9147   0.0301
  -3.500  -0.0516   0.00987   0.00366  -0.0705   0.9061   0.0346
  -3.250  -0.0258   0.00949   0.00326  -0.0698   0.8988   0.0442
  -3.000  -0.0002   0.00904   0.00294  -0.0692   0.8896   0.0693
  -2.750   0.0257   0.00866   0.00269  -0.0686   0.8818   0.1093
  -2.500   0.0516   0.00831   0.00251  -0.0681   0.8715   0.1599
  -2.250   0.0777   0.00794   0.00234  -0.0677   0.8622   0.2254
  -2.000   0.1034   0.00751   0.00220  -0.0673   0.8517   0.3168
  -1.750   0.1290   0.00709   0.00210  -0.0669   0.8403   0.4192
  -1.500   0.1546   0.00673   0.00201  -0.0663   0.8289   0.5181
  -1.250   0.1800   0.00642   0.00196  -0.0656   0.8169   0.6110
  -1.000   0.2052   0.00620   0.00193  -0.0648   0.8036   0.6898
  -0.750   0.2302   0.00603   0.00191  -0.0638   0.7896   0.7559
  -0.500   0.2547   0.00591   0.00190  -0.0626   0.7748   0.8106
  -0.250   0.2786   0.00584   0.00189  -0.0612   0.7594   0.8597
   0.000   0.3022   0.00580   0.00188  -0.0598   0.7432   0.9033
   0.250   0.3295   0.00582   0.00185  -0.0591   0.7261   0.9427
   0.500   0.3662   0.00587   0.00180  -0.0606   0.7077   0.9719
   0.750   0.4090   0.00593   0.00175  -0.0637   0.6874   0.9904
   1.000   0.4455   0.00602   0.00172  -0.0655   0.6664   1.0000
   1.250   0.4693   0.00615   0.00173  -0.0646   0.6461   1.0000
   1.500   0.4937   0.00628   0.00175  -0.0638   0.6261   1.0000
   1.750   0.5186   0.00642   0.00179  -0.0631   0.6049   1.0000
   2.000   0.5437   0.00659   0.00184  -0.0625   0.5835   1.0000
   2.250   0.5691   0.00676   0.00190  -0.0620   0.5624   1.0000
   2.500   0.5948   0.00693   0.00197  -0.0615   0.5399   1.0000
   2.750   0.6203   0.00713   0.00206  -0.0609   0.5181   1.0000
   3.000   0.6461   0.00733   0.00216  -0.0605   0.4958   1.0000
   3.250   0.6718   0.00754   0.00227  -0.0600   0.4731   1.0000
   3.500   0.6975   0.00776   0.00239  -0.0596   0.4511   1.0000
   3.750   0.7233   0.00799   0.00253  -0.0592   0.4289   1.0000
   4.000   0.7488   0.00824   0.00268  -0.0588   0.4074   1.0000
   4.250   0.7746   0.00848   0.00284  -0.0584   0.3860   1.0000
   4.500   0.8001   0.00874   0.00302  -0.0580   0.3646   1.0000
   5.000   0.8510   0.00929   0.00340  -0.0571   0.3247   1.0000
   5.250   0.8764   0.00958   0.00362  -0.0567   0.3049   1.0000
   5.500   0.9016   0.00988   0.00384  -0.0563   0.2858   1.0000
   5.750   0.9264   0.01022   0.00409  -0.0558   0.2670   1.0000
   6.000   0.9514   0.01053   0.00434  -0.0554   0.2489   1.0000
   6.250   0.9762   0.01086   0.00462  -0.0549   0.2306   1.0000
   6.500   1.0007   0.01122   0.00490  -0.0545   0.2128   1.0000
   6.750   1.0249   0.01160   0.00521  -0.0539   0.1957   1.0000
   7.000   1.0490   0.01199   0.00554  -0.0534   0.1801   1.0000
   7.250   1.0728   0.01239   0.00588  -0.0528   0.1655   1.0000
   7.500   1.0965   0.01279   0.00624  -0.0522   0.1517   1.0000
   7.750   1.1200   0.01321   0.00663  -0.0516   0.1389   1.0000
   8.000   1.1432   0.01364   0.00703  -0.0510   0.1270   1.0000
   8.250   1.1660   0.01409   0.00745  -0.0503   0.1160   1.0000
   8.500   1.1883   0.01458   0.00791  -0.0495   0.1058   1.0000
   9.000   1.2321   0.01558   0.00886  -0.0479   0.0872   1.0000
   9.250   1.2533   0.01610   0.00939  -0.0470   0.0792   1.0000
   9.500   1.2730   0.01674   0.00999  -0.0459   0.0713   1.0000
   9.750   1.2933   0.01729   0.01055  -0.0449   0.0646   1.0000
  10.000   1.3123   0.01792   0.01120  -0.0437   0.0589   1.0000
  10.250   1.3296   0.01865   0.01192  -0.0423   0.0534   1.0000
  10.500   1.3475   0.01928   0.01260  -0.0410   0.0494   1.0000
  10.750   1.3631   0.02003   0.01335  -0.0394   0.0457   1.0000
  11.000   1.3751   0.02084   0.01422  -0.0372   0.0428   1.0000
  11.250   1.3887   0.02150   0.01495  -0.0352   0.0405   1.0000
  11.500   1.3984   0.02240   0.01586  -0.0328   0.0381   1.0000
  11.750   1.4051   0.02350   0.01703  -0.0302   0.0362   1.0000
  12.000   1.4171   0.02431   0.01793  -0.0284   0.0346   1.0000
  12.250   1.4269   0.02528   0.01897  -0.0265   0.0331   1.0000
  12.500   1.4327   0.02655   0.02028  -0.0244   0.0318   1.0000
  12.750   1.4317   0.02839   0.02219  -0.0219   0.0304   1.0000
  13.000   1.4417   0.02951   0.02343  -0.0206   0.0295   1.0000
  13.250   1.4488   0.03089   0.02491  -0.0191   0.0284   1.0000
  13.500   1.4542   0.03249   0.02660  -0.0178   0.0274   1.0000
  13.750   1.4572   0.03436   0.02854  -0.0167   0.0267   1.0000
  14.000   1.4551   0.03683   0.03108  -0.0156   0.0259   1.0000
  14.250   1.4477   0.03998   0.03432  -0.0147   0.0252   1.0000
  14.500   1.4520   0.04214   0.03662  -0.0144   0.0247   1.0000
  14.750   1.4538   0.04464   0.03925  -0.0143   0.0241   1.0000
  15.000   1.4540   0.04746   0.04219  -0.0144   0.0234   1.0000
  15.250   1.4530   0.05054   0.04538  -0.0148   0.0228   1.0000
  15.500   1.4504   0.05393   0.04887  -0.0155   0.0223   1.0000
  15.750   1.4469   0.05761   0.05264  -0.0165   0.0219   1.0000
  16.000   1.4399   0.06188   0.05700  -0.0178   0.0214   1.0000
  16.250   1.4301   0.06662   0.06183  -0.0193   0.0210   1.0000
  16.500   1.4201   0.07153   0.06686  -0.0209   0.0207   1.0000
  16.750   1.4152   0.07607   0.07154  -0.0229   0.0204   1.0000
  17.000   1.4088   0.08093   0.07655  -0.0251   0.0201   1.0000
  17.250   1.4013   0.08612   0.08188  -0.0275   0.0198   1.0000
  17.500   1.3930   0.09153   0.08743  -0.0301   0.0195   1.0000
  17.750   1.3844   0.09710   0.09313  -0.0329   0.0193   1.0000
  18.000   1.3758   0.10283   0.09898  -0.0359   0.0190   1.0000
  18.250   1.3675   0.10862   0.10488  -0.0390   0.0187   1.0000
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