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SD7080 (9.2%) (sd7080-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: SD7080 (9.2%) (sd7080-il)
Reynolds number: 1,000,000
Max Cl/Cd: 107.54 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sd7080-il-1000000.txt
Download as CSV file: xf-sd7080-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4359   0.08221   0.08061  -0.0319   1.0000   0.0128
  -8.750  -0.4386   0.07828   0.07670  -0.0336   1.0000   0.0131
  -8.500  -0.4438   0.07436   0.07281  -0.0352   1.0000   0.0134
  -8.250  -0.4587   0.07061   0.06912  -0.0356   1.0000   0.0137
  -8.000  -0.4776   0.06707   0.06563  -0.0366   0.9990   0.0136
  -7.750  -0.4587   0.05267   0.05107  -0.0573   0.9935   0.0142
  -7.500  -0.4403   0.04027   0.03818  -0.0674   0.9881   0.0151
  -7.250  -0.4178   0.03452   0.03198  -0.0725   0.9854   0.0152
  -7.000  -0.4075   0.02555   0.02242  -0.0762   0.9803   0.0162
  -6.750  -0.3811   0.02386   0.02061  -0.0771   0.9766   0.0166
  -6.500  -0.3540   0.02253   0.01915  -0.0780   0.9732   0.0173
  -6.250  -0.3381   0.01605   0.01179  -0.0761   0.9663   0.0134
  -6.000  -0.3145   0.01452   0.01002  -0.0753   0.9612   0.0134
  -5.750  -0.2901   0.01350   0.00884  -0.0746   0.9567   0.0136
  -5.500  -0.2665   0.01260   0.00782  -0.0737   0.9508   0.0137
  -5.250  -0.2424   0.01182   0.00693  -0.0728   0.9457   0.0139
  -5.000  -0.2177   0.01112   0.00615  -0.0721   0.9405   0.0140
  -4.750  -0.1929   0.01050   0.00546  -0.0713   0.9347   0.0142
  -4.500  -0.1676   0.01005   0.00494  -0.0706   0.9295   0.0146
  -4.250  -0.1417   0.00959   0.00442  -0.0701   0.9236   0.0149
  -4.000  -0.1159   0.00916   0.00393  -0.0695   0.9175   0.0151
  -3.750  -0.0902   0.00860   0.00329  -0.0690   0.9115   0.0156
  -3.500  -0.0640   0.00811   0.00272  -0.0685   0.9043   0.0166
  -3.250  -0.0373   0.00783   0.00239  -0.0681   0.8976   0.0175
  -3.000  -0.0101   0.00760   0.00212  -0.0678   0.8894   0.0185
  -2.750   0.0171   0.00741   0.00189  -0.0675   0.8814   0.0197
  -2.500   0.0444   0.00722   0.00165  -0.0672   0.8722   0.0227
  -2.250   0.0712   0.00680   0.00143  -0.0669   0.8620   0.0728
  -2.000   0.0978   0.00645   0.00128  -0.0667   0.8511   0.1407
  -1.750   0.1245   0.00614   0.00116  -0.0665   0.8386   0.2107
  -1.500   0.1513   0.00586   0.00107  -0.0663   0.8244   0.2847
  -1.250   0.1779   0.00559   0.00099  -0.0661   0.8081   0.3684
  -1.000   0.2038   0.00524   0.00095  -0.0659   0.7894   0.4866
  -0.750   0.2298   0.00503   0.00092  -0.0655   0.7690   0.5807
  -0.500   0.2556   0.00484   0.00092  -0.0650   0.7465   0.6709
  -0.250   0.2811   0.00475   0.00094  -0.0643   0.7233   0.7419
   0.000   0.3067   0.00472   0.00097  -0.0637   0.6993   0.7923
   0.250   0.3321   0.00473   0.00099  -0.0630   0.6758   0.8332
   0.750   0.3802   0.00477   0.00107  -0.0608   0.6288   0.9172
   1.000   0.4064   0.00484   0.00110  -0.0602   0.6052   0.9570
   1.250   0.4436   0.00496   0.00111  -0.0622   0.5791   0.9846
   1.500   0.4809   0.00510   0.00114  -0.0643   0.5524   1.0000
   1.750   0.5065   0.00526   0.00119  -0.0638   0.5291   1.0000
   2.000   0.5323   0.00544   0.00125  -0.0634   0.5051   1.0000
   2.250   0.5586   0.00560   0.00131  -0.0631   0.4822   1.0000
   2.500   0.5848   0.00578   0.00140  -0.0628   0.4591   1.0000
   2.750   0.6111   0.00596   0.00148  -0.0625   0.4363   1.0000
   3.000   0.6375   0.00615   0.00157  -0.0622   0.4147   1.0000
   3.250   0.6639   0.00635   0.00167  -0.0620   0.3925   1.0000
   3.500   0.6903   0.00655   0.00179  -0.0617   0.3717   1.0000
   3.750   0.7168   0.00675   0.00191  -0.0615   0.3509   1.0000
   4.250   0.7694   0.00719   0.00218  -0.0610   0.3111   1.0000
   4.500   0.7958   0.00740   0.00234  -0.0607   0.2937   1.0000
   4.750   0.8219   0.00765   0.00251  -0.0605   0.2741   1.0000
   5.000   0.8480   0.00789   0.00268  -0.0602   0.2570   1.0000
   5.250   0.8740   0.00814   0.00287  -0.0599   0.2372   1.0000
   5.500   0.8994   0.00846   0.00308  -0.0596   0.2149   1.0000
   5.750   0.9252   0.00873   0.00329  -0.0593   0.1983   1.0000
   6.000   0.9506   0.00904   0.00352  -0.0590   0.1795   1.0000
   6.250   0.9755   0.00940   0.00379  -0.0586   0.1592   1.0000
   6.500   1.0007   0.00972   0.00405  -0.0582   0.1426   1.0000
   6.750   1.0255   0.01009   0.00433  -0.0578   0.1247   1.0000
   7.000   1.0501   0.01047   0.00464  -0.0573   0.1092   1.0000
   7.250   1.0745   0.01086   0.00496  -0.0569   0.0952   1.0000
   7.500   1.0984   0.01129   0.00532  -0.0564   0.0796   1.0000
   7.750   1.1222   0.01174   0.00570  -0.0558   0.0653   1.0000
   8.000   1.1456   0.01221   0.00610  -0.0552   0.0525   1.0000
   8.250   1.1685   0.01272   0.00656  -0.0546   0.0406   1.0000
   8.500   1.1902   0.01335   0.00709  -0.0538   0.0281   1.0000
   8.750   1.2092   0.01427   0.00788  -0.0526   0.0120   1.0000
   9.000   1.2310   0.01487   0.00849  -0.0517   0.0095   1.0000
   9.250   1.2520   0.01552   0.00920  -0.0507   0.0081   1.0000
   9.500   1.2737   0.01607   0.00983  -0.0498   0.0076   1.0000
   9.750   1.2945   0.01668   0.01050  -0.0488   0.0071   1.0000
  10.000   1.3146   0.01733   0.01122  -0.0478   0.0067   1.0000
  10.250   1.3332   0.01808   0.01202  -0.0465   0.0063   1.0000
  10.500   1.3448   0.01943   0.01352  -0.0442   0.0058   1.0000
  10.750   1.3623   0.02012   0.01429  -0.0429   0.0057   1.0000
  11.000   1.3779   0.02092   0.01517  -0.0412   0.0056   1.0000
  11.250   1.3911   0.02180   0.01615  -0.0392   0.0055   1.0000
  11.500   1.4004   0.02268   0.01712  -0.0366   0.0054   1.0000
  11.750   1.4080   0.02362   0.01815  -0.0338   0.0053   1.0000
  12.000   1.4126   0.02479   0.01942  -0.0309   0.0052   1.0000
  12.250   1.4187   0.02591   0.02064  -0.0284   0.0051   1.0000
  12.500   1.4213   0.02733   0.02217  -0.0258   0.0050   1.0000
  12.750   1.4246   0.02879   0.02373  -0.0235   0.0049   1.0000
  13.000   1.4249   0.03057   0.02562  -0.0213   0.0049   1.0000
  13.250   1.4264   0.03238   0.02754  -0.0196   0.0048   1.0000
  13.500   1.4250   0.03457   0.02985  -0.0180   0.0048   1.0000
  13.750   1.4232   0.03699   0.03238  -0.0169   0.0047   1.0000
  14.000   1.4216   0.03957   0.03509  -0.0163   0.0046   1.0000
  14.250   1.4122   0.04326   0.03893  -0.0160   0.0047   1.0000
  14.500   1.4102   0.04636   0.04213  -0.0163   0.0046   1.0000
  14.750   1.4026   0.05043   0.04633  -0.0172   0.0046   1.0000
  15.000   1.3958   0.05465   0.05067  -0.0185   0.0045   1.0000
  15.250   1.3876   0.05935   0.05550  -0.0203   0.0045   1.0000
  15.500   1.3757   0.06488   0.06116  -0.0226   0.0045   1.0000
  15.750   1.3640   0.07063   0.06705  -0.0253   0.0044   1.0000
  16.000   1.3505   0.07694   0.07350  -0.0284   0.0044   1.0000
  16.250   1.3349   0.08382   0.08053  -0.0319   0.0045   1.0000
  16.500   1.3235   0.09027   0.08707  -0.0354   0.0044   1.0000
  16.750   1.3080   0.09761   0.09456  -0.0392   0.0044   1.0000
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