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SD5060 (9.5%) (sd5060-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: SD5060 (9.5%) (sd5060-il)
Reynolds number: 500,000
Max Cl/Cd: 88.78 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sd5060-il-500000.txt
Download as CSV file: xf-sd5060-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.5892   0.05951   0.05738  -0.0349   1.0000   0.0194
  -9.000  -0.6891   0.03357   0.03007  -0.0544   1.0000   0.0157
  -8.750  -0.6786   0.03001   0.02613  -0.0545   1.0000   0.0157
  -8.500  -0.6650   0.02686   0.02268  -0.0544   1.0000   0.0160
  -8.250  -0.6477   0.02461   0.02019  -0.0539   1.0000   0.0163
  -8.000  -0.6295   0.02300   0.01841  -0.0532   1.0000   0.0168
  -7.750  -0.6143   0.02155   0.01681  -0.0516   1.0000   0.0171
  -7.500  -0.5937   0.02032   0.01542  -0.0510   0.9984   0.0177
  -7.250  -0.5583   0.01907   0.01399  -0.0531   0.9941   0.0188
  -7.000  -0.5237   0.01790   0.01261  -0.0549   0.9893   0.0196
  -6.750  -0.4878   0.01693   0.01144  -0.0567   0.9850   0.0201
  -6.500  -0.4562   0.01474   0.00907  -0.0581   0.9790   0.0209
  -6.250  -0.4236   0.01363   0.00789  -0.0594   0.9723   0.0220
  -6.000  -0.3930   0.01302   0.00724  -0.0601   0.9639   0.0234
  -5.750  -0.3640   0.01244   0.00657  -0.0602   0.9552   0.0246
  -5.500  -0.3389   0.01192   0.00596  -0.0595   0.9443   0.0255
  -5.250  -0.3141   0.01151   0.00546  -0.0587   0.9337   0.0263
  -5.000  -0.2902   0.01081   0.00468  -0.0577   0.9239   0.0283
  -4.750  -0.2652   0.01045   0.00425  -0.0569   0.9143   0.0312
  -4.500  -0.2393   0.01014   0.00388  -0.0563   0.9045   0.0345
  -4.250  -0.2140   0.00962   0.00340  -0.0556   0.8956   0.0498
  -4.000  -0.1884   0.00909   0.00307  -0.0552   0.8862   0.0982
  -3.750  -0.1619   0.00883   0.00288  -0.0548   0.8771   0.1266
  -3.500  -0.1354   0.00865   0.00271  -0.0543   0.8687   0.1510
  -3.250  -0.1081   0.00846   0.00258  -0.0541   0.8590   0.1747
  -3.000  -0.0811   0.00830   0.00244  -0.0538   0.8504   0.1969
  -2.750  -0.0539   0.00814   0.00231  -0.0535   0.8411   0.2213
  -2.500  -0.0264   0.00796   0.00219  -0.0533   0.8318   0.2481
  -2.250   0.0007   0.00780   0.00209  -0.0530   0.8231   0.2813
  -2.000   0.0282   0.00760   0.00199  -0.0529   0.8130   0.3183
  -1.750   0.0557   0.00743   0.00191  -0.0527   0.8035   0.3585
  -1.500   0.0828   0.00725   0.00183  -0.0524   0.7941   0.4081
  -1.250   0.1102   0.00704   0.00177  -0.0522   0.7833   0.4615
  -1.000   0.1374   0.00685   0.00173  -0.0520   0.7728   0.5197
  -0.750   0.1643   0.00667   0.00170  -0.0516   0.7623   0.5811
  -0.500   0.1909   0.00646   0.00167  -0.0511   0.7508   0.6493
  -0.250   0.2169   0.00627   0.00167  -0.0505   0.7386   0.7195
   0.000   0.2418   0.00607   0.00168  -0.0495   0.7262   0.7947
   0.250   0.2648   0.00589   0.00169  -0.0479   0.7137   0.8707
   0.500   0.2942   0.00579   0.00166  -0.0476   0.7007   0.9493
   0.750   0.3377   0.00578   0.00159  -0.0508   0.6863   1.0000
   1.000   0.3648   0.00586   0.00158  -0.0505   0.6722   1.0000
   1.250   0.3920   0.00594   0.00158  -0.0502   0.6571   1.0000
   1.500   0.4193   0.00603   0.00159  -0.0500   0.6411   1.0000
   1.750   0.4466   0.00613   0.00162  -0.0497   0.6242   1.0000
   2.000   0.4740   0.00624   0.00165  -0.0495   0.6063   1.0000
   2.250   0.5012   0.00637   0.00169  -0.0493   0.5877   1.0000
   2.500   0.5286   0.00650   0.00174  -0.0491   0.5677   1.0000
   2.750   0.5557   0.00666   0.00182  -0.0488   0.5456   1.0000
   3.000   0.5829   0.00683   0.00190  -0.0486   0.5232   1.0000
   3.250   0.6098   0.00703   0.00200  -0.0484   0.4984   1.0000
   3.500   0.6366   0.00725   0.00212  -0.0482   0.4703   1.0000
   3.750   0.6633   0.00750   0.00225  -0.0479   0.4418   1.0000
   4.000   0.6898   0.00777   0.00241  -0.0477   0.4116   1.0000
   4.250   0.7160   0.00809   0.00259  -0.0474   0.3774   1.0000
   4.500   0.7420   0.00844   0.00280  -0.0472   0.3433   1.0000
   4.750   0.7679   0.00880   0.00303  -0.0469   0.3116   1.0000
   5.000   0.7936   0.00920   0.00328  -0.0466   0.2802   1.0000
   5.250   0.8193   0.00959   0.00356  -0.0464   0.2517   1.0000
   5.500   0.8450   0.00997   0.00384  -0.0461   0.2276   1.0000
   5.750   0.8705   0.01038   0.00414  -0.0458   0.2058   1.0000
   6.000   0.8962   0.01074   0.00445  -0.0455   0.1878   1.0000
   6.250   0.9217   0.01112   0.00478  -0.0452   0.1716   1.0000
   6.500   0.9471   0.01151   0.00511  -0.0449   0.1576   1.0000
   6.750   0.9725   0.01189   0.00546  -0.0446   0.1454   1.0000
   7.000   0.9975   0.01230   0.00583  -0.0442   0.1346   1.0000
   7.250   1.0226   0.01269   0.00621  -0.0438   0.1247   1.0000
   7.500   1.0478   0.01305   0.00659  -0.0435   0.1164   1.0000
   7.750   1.0720   0.01351   0.00702  -0.0430   0.1078   1.0000
   8.000   1.0970   0.01387   0.00740  -0.0426   0.1002   1.0000
   8.250   1.1212   0.01431   0.00787  -0.0422   0.0926   1.0000
   8.500   1.1447   0.01481   0.00833  -0.0417   0.0837   1.0000
   8.750   1.1692   0.01517   0.00871  -0.0413   0.0754   1.0000
   9.000   1.1926   0.01565   0.00918  -0.0408   0.0669   1.0000
   9.250   1.2148   0.01625   0.00974  -0.0401   0.0586   1.0000
   9.500   1.2376   0.01674   0.01027  -0.0395   0.0520   1.0000
   9.750   1.2593   0.01736   0.01090  -0.0388   0.0456   1.0000
  10.000   1.2793   0.01811   0.01163  -0.0379   0.0390   1.0000
  10.250   1.3005   0.01868   0.01225  -0.0371   0.0342   1.0000
  10.500   1.3191   0.01951   0.01308  -0.0361   0.0290   1.0000
  10.750   1.3370   0.02036   0.01395  -0.0350   0.0243   1.0000
  11.000   1.3535   0.02128   0.01493  -0.0337   0.0201   1.0000
  11.250   1.3658   0.02251   0.01620  -0.0319   0.0166   1.0000
  11.500   1.3792   0.02352   0.01728  -0.0303   0.0145   1.0000
  11.750   1.3815   0.02503   0.01887  -0.0272   0.0129   1.0000
  12.000   1.3889   0.02611   0.02006  -0.0249   0.0121   1.0000
  12.250   1.3943   0.02738   0.02144  -0.0227   0.0115   1.0000
  12.500   1.3985   0.02884   0.02300  -0.0207   0.0109   1.0000
  12.750   1.3993   0.03066   0.02491  -0.0189   0.0103   1.0000
  13.000   1.3963   0.03294   0.02730  -0.0173   0.0100   1.0000
  13.250   1.3898   0.03576   0.03026  -0.0160   0.0096   1.0000
  13.500   1.3899   0.03816   0.03280  -0.0153   0.0094   1.0000
  13.750   1.3921   0.04049   0.03526  -0.0150   0.0090   1.0000
  14.000   1.3902   0.04342   0.03832  -0.0150   0.0088   1.0000
  14.250   1.3850   0.04692   0.04196  -0.0154   0.0086   1.0000
  14.500   1.3786   0.05078   0.04596  -0.0163   0.0085   1.0000
  14.750   1.3725   0.05485   0.05016  -0.0175   0.0083   1.0000
  15.000   1.3643   0.05943   0.05487  -0.0192   0.0082   1.0000
  15.250   1.3553   0.06436   0.05994  -0.0213   0.0081   1.0000
  15.500   1.3446   0.06982   0.06554  -0.0238   0.0080   1.0000
  15.750   1.3314   0.07595   0.07182  -0.0268   0.0080   1.0000
  16.000   1.3196   0.08217   0.07817  -0.0300   0.0080   1.0000
  16.250   1.3051   0.08904   0.08519  -0.0336   0.0079   1.0000
  16.500   1.2922   0.09590   0.09217  -0.0373   0.0078   1.0000
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