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SD7080 (9.2%) (sd7080-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: SD7080 (9.2%) (sd7080-il)
Reynolds number: 500,000
Max Cl/Cd: 91.53 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sd7080-il-500000.txt
Download as CSV file: xf-sd7080-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD7080 (9.2%)                                   
  
 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  -0.4276   0.09601   0.09368  -0.0301   1.0000   0.0204
  -9.500  -0.4352   0.09071   0.08842  -0.0309   1.0000   0.0211
  -9.250  -0.4339   0.08721   0.08494  -0.0321   1.0000   0.0212
  -9.000  -0.4303   0.08459   0.08234  -0.0326   1.0000   0.0216
  -8.750  -0.4289   0.08163   0.07940  -0.0334   1.0000   0.0219
  -8.500  -0.4291   0.07864   0.07645  -0.0343   1.0000   0.0223
  -8.250  -0.4335   0.07549   0.07334  -0.0350   1.0000   0.0228
  -8.000  -0.4458   0.07259   0.07050  -0.0348   1.0000   0.0230
  -7.750  -0.4669   0.06975   0.06773  -0.0339   1.0000   0.0230
  -7.500  -0.4843   0.06566   0.06365  -0.0351   1.0000   0.0229
  -7.250  -0.4903   0.06116   0.05912  -0.0373   0.9995   0.0234
  -7.000  -0.4583   0.05005   0.04755  -0.0512   0.9948   0.0269
  -6.750  -0.4475   0.03950   0.03643  -0.0584   0.9890   0.0279
  -6.500  -0.4201   0.03675   0.03367  -0.0611   0.9865   0.0288
  -6.250  -0.3893   0.03436   0.03116  -0.0640   0.9845   0.0301
  -6.000  -0.3617   0.03166   0.02822  -0.0658   0.9808   0.0322
  -5.750  -0.3249   0.03207   0.02814  -0.0668   0.9771   0.0357
  -5.500  -0.3031   0.01880   0.01352  -0.0678   0.9737   0.0207
  -5.250  -0.2664   0.01752   0.01204  -0.0697   0.9723   0.0205
  -5.000  -0.2302   0.01549   0.00978  -0.0716   0.9712   0.0207
  -4.750  -0.2035   0.01414   0.00831  -0.0714   0.9659   0.0209
  -4.500  -0.1704   0.01305   0.00713  -0.0724   0.9627   0.0209
  -4.250  -0.1372   0.01194   0.00594  -0.0735   0.9598   0.0214
  -4.000  -0.1054   0.01119   0.00514  -0.0742   0.9564   0.0222
  -3.750  -0.0795   0.01068   0.00461  -0.0737   0.9497   0.0232
  -3.500  -0.0496   0.01022   0.00411  -0.0739   0.9451   0.0246
  -3.250  -0.0233   0.00987   0.00371  -0.0733   0.9387   0.0261
  -3.000   0.0033   0.00948   0.00327  -0.0728   0.9322   0.0295
  -2.750   0.0296   0.00912   0.00292  -0.0721   0.9257   0.0396
  -2.500   0.0539   0.00841   0.00259  -0.0714   0.9177   0.1344
  -2.250   0.0791   0.00795   0.00240  -0.0708   0.9100   0.2162
  -2.000   0.1040   0.00746   0.00223  -0.0702   0.9016   0.3167
  -1.750   0.1286   0.00696   0.00212  -0.0696   0.8921   0.4348
  -1.500   0.1532   0.00649   0.00202  -0.0688   0.8830   0.5579
  -1.250   0.1772   0.00611   0.00197  -0.0678   0.8720   0.6664
  -1.000   0.2013   0.00586   0.00194  -0.0666   0.8600   0.7446
  -0.750   0.2250   0.00566   0.00190  -0.0652   0.8472   0.8114
  -0.500   0.2483   0.00552   0.00186  -0.0637   0.8332   0.8632
  -0.250   0.2720   0.00544   0.00180  -0.0622   0.8174   0.9059
   0.000   0.3004   0.00541   0.00173  -0.0618   0.8000   0.9460
   0.250   0.3392   0.00541   0.00164  -0.0638   0.7798   0.9755
   0.500   0.3812   0.00546   0.00155  -0.0667   0.7567   0.9948
   0.750   0.4110   0.00555   0.00151  -0.0671   0.7320   1.0000
   1.000   0.4348   0.00568   0.00150  -0.0661   0.7074   1.0000
   1.250   0.4591   0.00584   0.00151  -0.0653   0.6823   1.0000
   1.500   0.4839   0.00599   0.00154  -0.0647   0.6567   1.0000
   1.750   0.5090   0.00617   0.00158  -0.0640   0.6312   1.0000
   2.000   0.5342   0.00635   0.00164  -0.0634   0.6060   1.0000
   2.250   0.5595   0.00655   0.00171  -0.0629   0.5800   1.0000
   2.500   0.5851   0.00674   0.00180  -0.0624   0.5546   1.0000
   2.750   0.6106   0.00695   0.00189  -0.0619   0.5294   1.0000
   3.000   0.6362   0.00717   0.00200  -0.0615   0.5043   1.0000
   3.250   0.6619   0.00739   0.00212  -0.0611   0.4795   1.0000
   3.500   0.6875   0.00762   0.00226  -0.0607   0.4550   1.0000
   3.750   0.7131   0.00787   0.00241  -0.0603   0.4311   1.0000
   4.000   0.7388   0.00811   0.00256  -0.0599   0.4076   1.0000
   4.250   0.7644   0.00837   0.00273  -0.0595   0.3848   1.0000
   4.500   0.7899   0.00864   0.00293  -0.0591   0.3625   1.0000
   4.750   0.8155   0.00891   0.00312  -0.0587   0.3405   1.0000
   5.000   0.8409   0.00919   0.00333  -0.0584   0.3197   1.0000
   5.250   0.8662   0.00949   0.00356  -0.0580   0.2993   1.0000
   5.500   0.8915   0.00979   0.00381  -0.0576   0.2788   1.0000
   5.750   0.9163   0.01014   0.00407  -0.0572   0.2578   1.0000
   6.000   0.9412   0.01047   0.00434  -0.0567   0.2360   1.0000
   6.250   0.9658   0.01085   0.00465  -0.0563   0.2163   1.0000
   6.500   0.9904   0.01120   0.00496  -0.0558   0.1979   1.0000
   6.750   1.0148   0.01159   0.00529  -0.0553   0.1789   1.0000
   7.000   1.0384   0.01205   0.00565  -0.0548   0.1594   1.0000
   7.250   1.0623   0.01247   0.00603  -0.0543   0.1402   1.0000
   7.500   1.0854   0.01297   0.00644  -0.0537   0.1211   1.0000
   8.000   1.1314   0.01396   0.00733  -0.0524   0.0903   1.0000
   8.250   1.1540   0.01449   0.00781  -0.0517   0.0767   1.0000
   8.500   1.1760   0.01505   0.00835  -0.0510   0.0635   1.0000
   8.750   1.1970   0.01571   0.00893  -0.0501   0.0494   1.0000
   9.000   1.2164   0.01651   0.00965  -0.0490   0.0335   1.0000
   9.250   1.2325   0.01766   0.01069  -0.0474   0.0183   1.0000
   9.500   1.2497   0.01865   0.01172  -0.0459   0.0143   1.0000
   9.750   1.2678   0.01947   0.01262  -0.0445   0.0127   1.0000
  10.000   1.2826   0.02055   0.01378  -0.0427   0.0116   1.0000
  10.250   1.2957   0.02167   0.01502  -0.0407   0.0111   1.0000
  10.500   1.3097   0.02262   0.01609  -0.0389   0.0105   1.0000
  10.750   1.3201   0.02364   0.01722  -0.0365   0.0102   1.0000
  11.000   1.3271   0.02474   0.01843  -0.0336   0.0100   1.0000
  11.250   1.3333   0.02593   0.01971  -0.0309   0.0096   1.0000
  11.500   1.3387   0.02719   0.02107  -0.0283   0.0094   1.0000
  11.750   1.3434   0.02855   0.02253  -0.0260   0.0090   1.0000
  12.000   1.3438   0.03031   0.02441  -0.0234   0.0088   1.0000
  12.250   1.3428   0.03231   0.02651  -0.0212   0.0085   1.0000
  12.500   1.3373   0.03489   0.02922  -0.0191   0.0084   1.0000
  12.750   1.3303   0.03785   0.03233  -0.0173   0.0082   1.0000
  13.000   1.3267   0.04070   0.03532  -0.0162   0.0082   1.0000
  13.250   1.3251   0.04349   0.03826  -0.0156   0.0081   1.0000
  13.500   1.3227   0.04652   0.04144  -0.0153   0.0081   1.0000
  13.750   1.3197   0.04981   0.04488  -0.0155   0.0080   1.0000
  14.000   1.3162   0.05332   0.04855  -0.0160   0.0080   1.0000
  14.250   1.3087   0.05759   0.05297  -0.0169   0.0080   1.0000
  14.500   1.3031   0.06178   0.05733  -0.0183   0.0079   1.0000
  14.750   1.2948   0.06658   0.06228  -0.0200   0.0079   1.0000
  15.000   1.2861   0.07168   0.06755  -0.0223   0.0079   1.0000
  15.250   1.2761   0.07721   0.07324  -0.0248   0.0079   1.0000
  15.500   1.2641   0.08335   0.07954  -0.0279   0.0079   1.0000
  15.750   1.2516   0.08982   0.08617  -0.0313   0.0079   1.0000
  16.000   1.2379   0.09677   0.09328  -0.0351   0.0079   1.0000
  16.250   1.2232   0.10418   0.10085  -0.0392   0.0079   1.0000
  16.500   1.2094   0.11178   0.10860  -0.0437   0.0079   1.0000
  16.750   1.1938   0.11989   0.11686  -0.0485   0.0079   1.0000
  17.000   1.1767   0.12863   0.12575  -0.0538   0.0080   1.0000
  17.250   1.1623   0.13724   0.13450  -0.0592   0.0080   1.0000
  17.500   1.1449   0.14669   0.14408  -0.0651   0.0081   1.0000
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