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SD5060 (9.5%) (sd5060-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: SD5060 (9.5%) (sd5060-il)
Reynolds number: 100,000
Max Cl/Cd: 51.52 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sd5060-il-100000.txt
Download as CSV file: xf-sd5060-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD5060 (9.5%)                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4519   0.09682   0.09201  -0.0130   1.0000   0.1255
  -8.500  -0.4482   0.09354   0.08876  -0.0143   1.0000   0.1299
  -8.250  -0.4880   0.09107   0.08651  -0.0242   1.0000   0.1346
  -8.000  -0.4619   0.08602   0.08144  -0.0204   1.0000   0.1368
  -7.750  -0.4485   0.08274   0.07816  -0.0194   1.0000   0.1397
  -7.500  -0.4485   0.07948   0.07496  -0.0207   1.0000   0.1434
  -7.250  -0.5125   0.05375   0.04859  -0.0501   1.0000   0.0802
  -7.000  -0.4948   0.05060   0.04563  -0.0486   1.0000   0.0763
  -6.750  -0.5031   0.04058   0.03450  -0.0511   1.0000   0.0662
  -6.500  -0.4934   0.03662   0.03025  -0.0501   1.0000   0.0653
  -6.250  -0.4823   0.03318   0.02640  -0.0489   1.0000   0.0648
  -6.000  -0.4689   0.03056   0.02323  -0.0473   1.0000   0.0660
  -5.750  -0.4543   0.02792   0.02020  -0.0459   1.0000   0.0678
  -5.500  -0.4375   0.02587   0.01797  -0.0446   1.0000   0.0698
  -5.250  -0.4189   0.02418   0.01606  -0.0433   1.0000   0.0720
  -5.000  -0.3993   0.02268   0.01434  -0.0419   1.0000   0.0752
  -4.750  -0.3788   0.02137   0.01274  -0.0407   1.0000   0.0804
  -4.500  -0.3592   0.02031   0.01176  -0.0396   1.0000   0.0888
  -4.250  -0.3383   0.01915   0.01060  -0.0386   1.0000   0.1002
  -4.000  -0.3172   0.01810   0.00966  -0.0376   1.0000   0.1278
  -3.750  -0.2964   0.01751   0.00920  -0.0369   1.0000   0.1734
  -3.500  -0.2761   0.01726   0.00903  -0.0362   1.0000   0.2121
  -3.250  -0.2564   0.01719   0.00901  -0.0355   1.0000   0.2500
  -3.000  -0.2359   0.01696   0.00880  -0.0348   1.0000   0.2817
  -2.750  -0.1990   0.01667   0.00869  -0.0372   0.9942   0.3206
  -2.500  -0.1574   0.01640   0.00857  -0.0403   0.9858   0.3685
  -2.250  -0.1173   0.01611   0.00851  -0.0430   0.9772   0.4247
  -2.000  -0.0744   0.01577   0.00853  -0.0461   0.9696   0.5029
  -1.750  -0.0402   0.01537   0.00858  -0.0472   0.9597   0.6021
  -1.500  -0.0081   0.01499   0.00872  -0.0471   0.9506   0.7386
  -1.250   0.0592   0.01452   0.00861  -0.0530   0.9464   0.9937
  -1.000   0.1072   0.01467   0.00847  -0.0575   0.9373   1.0000
  -0.750   0.1585   0.01473   0.00833  -0.0622   0.9289   1.0000
  -0.500   0.1978   0.01484   0.00827  -0.0645   0.9175   1.0000
  -0.250   0.2376   0.01491   0.00823  -0.0668   0.9067   1.0000
   0.000   0.2800   0.01490   0.00812  -0.0691   0.8970   1.0000
   0.250   0.3128   0.01495   0.00808  -0.0697   0.8845   1.0000
   0.500   0.3419   0.01502   0.00807  -0.0695   0.8710   1.0000
   0.750   0.3697   0.01507   0.00807  -0.0689   0.8573   1.0000
   1.000   0.3964   0.01510   0.00805  -0.0679   0.8433   1.0000
   1.250   0.4222   0.01512   0.00801  -0.0668   0.8290   1.0000
   1.500   0.4473   0.01511   0.00795  -0.0654   0.8144   1.0000
   1.750   0.4720   0.01509   0.00789  -0.0639   0.7994   1.0000
   2.000   0.4967   0.01505   0.00781  -0.0624   0.7840   1.0000
   2.250   0.5213   0.01500   0.00773  -0.0608   0.7683   1.0000
   2.500   0.5460   0.01494   0.00763  -0.0593   0.7522   1.0000
   2.750   0.5710   0.01487   0.00753  -0.0577   0.7356   1.0000
   3.000   0.5954   0.01486   0.00749  -0.0563   0.7167   1.0000
   3.250   0.6201   0.01484   0.00745  -0.0549   0.6966   1.0000
   3.500   0.6453   0.01478   0.00734  -0.0535   0.6769   1.0000
   3.750   0.6699   0.01480   0.00735  -0.0522   0.6534   1.0000
   4.000   0.6950   0.01480   0.00728  -0.0509   0.6300   1.0000
   4.250   0.7196   0.01486   0.00729  -0.0496   0.6032   1.0000
   4.500   0.7440   0.01497   0.00735  -0.0483   0.5734   1.0000
   4.750   0.7680   0.01515   0.00746  -0.0471   0.5400   1.0000
   5.000   0.7916   0.01542   0.00761  -0.0459   0.5027   1.0000
   5.250   0.8145   0.01581   0.00785  -0.0447   0.4624   1.0000
   5.500   0.8369   0.01634   0.00820  -0.0435   0.4207   1.0000
   5.750   0.8588   0.01702   0.00863  -0.0423   0.3812   1.0000
   6.000   0.8809   0.01779   0.00923  -0.0413   0.3440   1.0000
   6.250   0.9030   0.01863   0.00989  -0.0404   0.3129   1.0000
   6.500   0.9254   0.01953   0.01068  -0.0396   0.2866   1.0000
   6.750   0.9482   0.02049   0.01145  -0.0389   0.2650   1.0000
   7.000   0.9711   0.02142   0.01238  -0.0381   0.2449   1.0000
   7.250   0.9941   0.02239   0.01333  -0.0374   0.2278   1.0000
   7.500   1.0170   0.02339   0.01433  -0.0368   0.2122   1.0000
   7.750   1.0399   0.02444   0.01540  -0.0361   0.1981   1.0000
   8.000   1.0624   0.02553   0.01653  -0.0354   0.1848   1.0000
   8.250   1.0846   0.02669   0.01773  -0.0347   0.1723   1.0000
   8.500   1.1066   0.02791   0.01900  -0.0340   0.1604   1.0000
   8.750   1.1287   0.02920   0.02024  -0.0334   0.1490   1.0000
   9.000   1.1488   0.03035   0.02153  -0.0324   0.1379   1.0000
   9.250   1.1675   0.03178   0.02320  -0.0313   0.1272   1.0000
   9.500   1.1865   0.03343   0.02497  -0.0304   0.1175   1.0000
   9.750   1.2062   0.03502   0.02652  -0.0297   0.1081   1.0000
  10.000   1.2204   0.03649   0.02834  -0.0281   0.0994   1.0000
  10.250   1.2348   0.03851   0.03055  -0.0268   0.0914   1.0000
  10.500   1.2524   0.04009   0.03202  -0.0260   0.0835   1.0000
  10.750   1.2576   0.04228   0.03474  -0.0237   0.0771   1.0000
  11.000   1.2723   0.04422   0.03653  -0.0229   0.0703   1.0000
  11.250   1.2702   0.04667   0.03956  -0.0202   0.0658   1.0000
  11.500   1.2801   0.04805   0.04088  -0.0189   0.0605   1.0000
  11.750   1.2753   0.05146   0.04461  -0.0167   0.0576   1.0000
  12.000   1.2607   0.05458   0.04813  -0.0137   0.0560   1.0000
  12.250   1.2449   0.05812   0.05200  -0.0117   0.0548   1.0000
  12.500   1.2277   0.06202   0.05617  -0.0106   0.0538   1.0000
  12.750   1.2073   0.06666   0.06108  -0.0107   0.0534   1.0000
  13.000   1.1801   0.07260   0.06730  -0.0123   0.0538   1.0000
  13.250   1.1484   0.07996   0.07493  -0.0157   0.0550   1.0000
  13.500   1.1161   0.08842   0.08359  -0.0206   0.0561   1.0000
  13.750   1.0855   0.09786   0.09317  -0.0265   0.0575   1.0000
  14.000   1.0580   0.10790   0.10328  -0.0327   0.0586   1.0000
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