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SD7080 (9.2%) (sd7080-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: SD7080 (9.2%) (sd7080-il)
Reynolds number: 200,000
Max Cl/Cd: 66.08 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sd7080-il-200000-n5.txt
Download as CSV file: xf-sd7080-il-200000-n5.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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3454   0.08180   0.07841  -0.0320   1.0000   0.0216
  -8.750  -0.4416   0.07883   0.07530  -0.0360   1.0000   0.0187
  -8.500  -0.4471   0.07506   0.07158  -0.0372   1.0000   0.0184
  -8.250  -0.4578   0.07120   0.06780  -0.0384   1.0000   0.0182
  -8.000  -0.4712   0.06708   0.06375  -0.0404   1.0000   0.0180
  -7.750  -0.4829   0.06194   0.05861  -0.0431   1.0000   0.0177
  -7.500  -0.4938   0.05700   0.05361  -0.0440   1.0000   0.0175
  -7.250  -0.5034   0.05172   0.04819  -0.0443   1.0000   0.0173
  -7.000  -0.4980   0.04494   0.04109  -0.0475   0.9972   0.0169
  -6.750  -0.4782   0.03738   0.03296  -0.0522   0.9917   0.0167
  -6.500  -0.4546   0.03191   0.02687  -0.0550   0.9868   0.0168
  -6.250  -0.4258   0.02795   0.02232  -0.0572   0.9834   0.0170
  -6.000  -0.3987   0.02556   0.01944  -0.0581   0.9788   0.0180
  -5.750  -0.3682   0.02355   0.01698  -0.0592   0.9749   0.0185
  -5.500  -0.3356   0.02163   0.01467  -0.0606   0.9720   0.0186
  -5.250  -0.3038   0.02006   0.01282  -0.0617   0.9687   0.0187
  -5.000  -0.2743   0.01881   0.01137  -0.0621   0.9639   0.0188
  -4.750  -0.2417   0.01742   0.00985  -0.0633   0.9605   0.0192
  -4.500  -0.2073   0.01622   0.00857  -0.0648   0.9578   0.0199
  -4.250  -0.1783   0.01542   0.00769  -0.0652   0.9524   0.0207
  -4.000  -0.1471   0.01475   0.00697  -0.0659   0.9473   0.0218
  -3.750  -0.1130   0.01417   0.00632  -0.0672   0.9435   0.0232
  -3.500  -0.0848   0.01377   0.00584  -0.0672   0.9366   0.0257
  -3.250  -0.0535   0.01321   0.00523  -0.0678   0.9310   0.0287
  -3.000  -0.0238   0.01280   0.00476  -0.0680   0.9245   0.0334
  -2.750   0.0052   0.01229   0.00434  -0.0681   0.9173   0.0544
  -2.500   0.0331   0.01175   0.00403  -0.0682   0.9097   0.1118
  -2.250   0.0608   0.01119   0.00378  -0.0683   0.9018   0.1956
  -2.000   0.0862   0.01057   0.00362  -0.0680   0.8923   0.3125
  -1.750   0.1119   0.00988   0.00349  -0.0676   0.8837   0.4663
  -1.500   0.1357   0.00939   0.00342  -0.0665   0.8728   0.5898
  -1.250   0.1596   0.00907   0.00336  -0.0652   0.8611   0.6766
  -1.000   0.1840   0.00884   0.00328  -0.0639   0.8488   0.7420
  -0.750   0.2081   0.00865   0.00320  -0.0624   0.8356   0.8007
  -0.500   0.2333   0.00850   0.00310  -0.0610   0.8212   0.8553
  -0.250   0.2637   0.00839   0.00297  -0.0608   0.8055   0.9061
   0.000   0.3024   0.00831   0.00281  -0.0626   0.7880   0.9510
   0.250   0.3447   0.00825   0.00263  -0.0653   0.7678   0.9875
   0.500   0.3760   0.00829   0.00251  -0.0659   0.7455   1.0000
   0.750   0.4007   0.00837   0.00245  -0.0651   0.7221   1.0000
   1.000   0.4254   0.00849   0.00240  -0.0643   0.6984   1.0000
   1.250   0.4502   0.00864   0.00239  -0.0635   0.6732   1.0000
   1.500   0.4751   0.00880   0.00241  -0.0628   0.6482   1.0000
   1.750   0.5000   0.00898   0.00245  -0.0621   0.6232   1.0000
   2.000   0.5249   0.00919   0.00251  -0.0614   0.5983   1.0000
   2.250   0.5499   0.00940   0.00259  -0.0608   0.5733   1.0000
   2.500   0.5749   0.00962   0.00269  -0.0602   0.5487   1.0000
   2.750   0.5998   0.00986   0.00281  -0.0596   0.5247   1.0000
   3.000   0.6248   0.01010   0.00295  -0.0590   0.5004   1.0000
   3.250   0.6497   0.01036   0.00310  -0.0584   0.4766   1.0000
   3.500   0.6745   0.01063   0.00329  -0.0579   0.4533   1.0000
   3.750   0.6994   0.01091   0.00348  -0.0573   0.4299   1.0000
   4.000   0.7242   0.01120   0.00368  -0.0568   0.4077   1.0000
   4.250   0.7489   0.01150   0.00390  -0.0562   0.3852   1.0000
   4.500   0.7736   0.01181   0.00417  -0.0557   0.3639   1.0000
   4.750   0.7982   0.01214   0.00443  -0.0552   0.3426   1.0000
   5.000   0.8227   0.01248   0.00471  -0.0547   0.3223   1.0000
   5.250   0.8471   0.01282   0.00501  -0.0541   0.3023   1.0000
   5.500   0.8712   0.01320   0.00533  -0.0536   0.2831   1.0000
   5.750   0.8955   0.01357   0.00570  -0.0530   0.2645   1.0000
   6.000   0.9195   0.01397   0.00607  -0.0525   0.2457   1.0000
   6.250   0.9431   0.01439   0.00646  -0.0519   0.2277   1.0000
   6.500   0.9665   0.01484   0.00687  -0.0513   0.2100   1.0000
   6.750   0.9898   0.01530   0.00734  -0.0506   0.1913   1.0000
   7.000   1.0125   0.01581   0.00781  -0.0500   0.1727   1.0000
   7.250   1.0349   0.01634   0.00832  -0.0493   0.1566   1.0000
   7.500   1.0574   0.01687   0.00885  -0.0485   0.1426   1.0000
   7.750   1.0795   0.01743   0.00941  -0.0478   0.1276   1.0000
   8.000   1.1008   0.01804   0.01003  -0.0470   0.1106   1.0000
   8.250   1.1215   0.01872   0.01067  -0.0461   0.0941   1.0000
   8.500   1.1412   0.01948   0.01137  -0.0452   0.0783   1.0000
   8.750   1.1606   0.02025   0.01210  -0.0442   0.0629   1.0000
   9.000   1.1793   0.02107   0.01290  -0.0431   0.0494   1.0000
   9.250   1.1974   0.02191   0.01376  -0.0419   0.0399   1.0000
   9.500   1.2139   0.02289   0.01477  -0.0405   0.0301   1.0000
   9.750   1.2288   0.02397   0.01589  -0.0389   0.0227   1.0000
  10.000   1.2411   0.02523   0.01719  -0.0370   0.0174   1.0000
  10.250   1.2538   0.02635   0.01843  -0.0351   0.0150   1.0000
  10.500   1.2615   0.02765   0.01978  -0.0327   0.0133   1.0000
  10.750   1.2703   0.02879   0.02108  -0.0304   0.0123   1.0000
  11.000   1.2774   0.03006   0.02250  -0.0281   0.0114   1.0000
  11.250   1.2830   0.03148   0.02404  -0.0259   0.0106   1.0000
  11.500   1.2862   0.03312   0.02582  -0.0237   0.0102   1.0000
  11.750   1.2873   0.03497   0.02784  -0.0217   0.0099   1.0000
  12.000   1.2842   0.03729   0.03030  -0.0197   0.0096   1.0000
  12.250   1.2829   0.03961   0.03277  -0.0183   0.0094   1.0000
  12.500   1.2811   0.04214   0.03549  -0.0173   0.0093   1.0000
  12.750   1.2779   0.04501   0.03852  -0.0167   0.0092   1.0000
  13.000   1.2738   0.04821   0.04189  -0.0166   0.0090   1.0000
  13.250   1.2686   0.05178   0.04564  -0.0170   0.0088   1.0000
  13.500   1.2627   0.05569   0.04972  -0.0178   0.0088   1.0000
  13.750   1.2556   0.05998   0.05419  -0.0190   0.0087   1.0000
  14.000   1.2480   0.06461   0.05898  -0.0207   0.0086   1.0000
  14.250   1.2396   0.06956   0.06410  -0.0227   0.0086   1.0000
  14.500   1.2295   0.07501   0.06973  -0.0251   0.0085   1.0000
  14.750   1.2192   0.08073   0.07562  -0.0278   0.0084   1.0000
  15.000   1.2084   0.08676   0.08182  -0.0308   0.0084   1.0000
  15.250   1.1969   0.09316   0.08838  -0.0341   0.0084   1.0000
  15.500   1.1851   0.09979   0.09518  -0.0377   0.0084   1.0000
  15.750   1.1722   0.10691   0.10245  -0.0416   0.0083   1.0000
  16.000   1.1596   0.11420   0.10990  -0.0456   0.0083   1.0000
  16.250   1.1469   0.12174   0.11760  -0.0499   0.0084   1.0000
  16.500   1.1336   0.12966   0.12567  -0.0545   0.0084   1.0000
  16.750   1.1194   0.13817   0.13431  -0.0595   0.0084   1.0000
  17.000   1.1049   0.14702   0.14331  -0.0648   0.0085   1.0000
  17.250   1.0896   0.15647   0.15290  -0.0705   0.0085   1.0000
  17.500   1.0719   0.16719   0.16374  -0.0769   0.0087   1.0000
  17.750   1.0472   0.18108   0.17775  -0.0849   0.0089   1.0000
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