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S7075 (9%) (s7075-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: S7075 (9%) (s7075-il)
Reynolds number: 50,000
Max Cl/Cd: 40.16 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s7075-il-50000-n5.txt
Download as CSV file: xf-s7075-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S7075 (9%)                                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3869   0.11462   0.10740  -0.0324   1.0000   0.1130
  -9.250  -0.4001   0.11318   0.10609  -0.0347   1.0000   0.1143
  -9.000  -0.4090   0.11098   0.10401  -0.0359   1.0000   0.1147
  -8.750  -0.4072   0.10735   0.10048  -0.0355   1.0000   0.1150
  -8.500  -0.3854   0.10238   0.09544  -0.0332   1.0000   0.1118
  -8.250  -0.3981   0.09463   0.08772  -0.0375   1.0000   0.0579
  -8.000  -0.3984   0.09176   0.08492  -0.0363   1.0000   0.0562
  -7.750  -0.4052   0.08900   0.08226  -0.0354   1.0000   0.0546
  -7.500  -0.4147   0.08630   0.07968  -0.0346   1.0000   0.0533
  -7.250  -0.4232   0.08277   0.07624  -0.0355   1.0000   0.0518
  -6.750  -0.4417   0.07151   0.06491  -0.0437   1.0000   0.0467
  -6.500  -0.4401   0.06812   0.06150  -0.0435   1.0000   0.0462
  -6.250  -0.4375   0.06439   0.05772  -0.0439   1.0000   0.0458
  -6.000  -0.4327   0.06042   0.05363  -0.0447   1.0000   0.0453
  -5.750  -0.4249   0.05630   0.04933  -0.0458   1.0000   0.0448
  -5.500  -0.4139   0.05204   0.04480  -0.0470   1.0000   0.0444
  -5.250  -0.3992   0.04790   0.04030  -0.0483   1.0000   0.0442
  -5.000  -0.3811   0.04395   0.03587  -0.0495   1.0000   0.0449
  -4.750  -0.3600   0.04040   0.03170  -0.0504   1.0000   0.0460
  -4.500  -0.3372   0.03728   0.02799  -0.0509   1.0000   0.0474
  -4.250  -0.3154   0.03480   0.02523  -0.0510   1.0000   0.0486
  -4.000  -0.2918   0.03261   0.02269  -0.0509   1.0000   0.0498
  -3.750  -0.2676   0.03075   0.02050  -0.0507   1.0000   0.0512
  -3.500  -0.2429   0.02912   0.01854  -0.0502   1.0000   0.0534
  -3.250  -0.2185   0.02780   0.01685  -0.0496   1.0000   0.0576
  -3.000  -0.1953   0.02665   0.01562  -0.0490   1.0000   0.0634
  -2.750  -0.1720   0.02568   0.01445  -0.0481   1.0000   0.0703
  -2.500  -0.1491   0.02483   0.01355  -0.0475   1.0000   0.0822
  -2.250  -0.1226   0.02401   0.01270  -0.0475   0.9990   0.1037
  -2.000  -0.0849   0.02296   0.01188  -0.0500   0.9940   0.1629
  -1.750  -0.0493   0.02161   0.01152  -0.0525   0.9887   0.3501
  -1.500  -0.0246   0.02052   0.01181  -0.0511   0.9832   0.6526
  -1.250   0.0081   0.01990   0.01153  -0.0506   0.9736   1.0000
  -1.000   0.0462   0.02023   0.01139  -0.0531   0.9655   1.0000
  -0.750   0.0859   0.02061   0.01137  -0.0559   0.9576   1.0000
  -0.500   0.1209   0.02090   0.01134  -0.0577   0.9479   1.0000
  -0.250   0.1591   0.02124   0.01141  -0.0601   0.9392   1.0000
   0.000   0.1959   0.02153   0.01148  -0.0622   0.9297   1.0000
   0.250   0.2293   0.02180   0.01156  -0.0636   0.9190   1.0000
   0.500   0.2657   0.02206   0.01167  -0.0655   0.9091   1.0000
   0.750   0.3039   0.02229   0.01177  -0.0676   0.8994   1.0000
   1.000   0.3356   0.02249   0.01188  -0.0685   0.8873   1.0000
   1.250   0.3684   0.02267   0.01199  -0.0695   0.8752   1.0000
   1.500   0.4021   0.02281   0.01208  -0.0706   0.8632   1.0000
   1.750   0.4372   0.02289   0.01214  -0.0718   0.8514   1.0000
   2.000   0.4758   0.02289   0.01212  -0.0734   0.8406   1.0000
   2.250   0.5080   0.02290   0.01216  -0.0739   0.8271   1.0000
   2.500   0.5395   0.02288   0.01217  -0.0742   0.8130   1.0000
   2.750   0.5712   0.02281   0.01214  -0.0744   0.7985   1.0000
   3.000   0.6031   0.02269   0.01208  -0.0745   0.7836   1.0000
   3.250   0.6304   0.02267   0.01214  -0.0739   0.7658   1.0000
   3.500   0.6605   0.02255   0.01209  -0.0736   0.7483   1.0000
   3.750   0.6925   0.02235   0.01197  -0.0735   0.7305   1.0000
   4.000   0.7263   0.02209   0.01182  -0.0735   0.7122   1.0000
   4.250   0.7544   0.02204   0.01184  -0.0728   0.6891   1.0000
   4.500   0.7860   0.02190   0.01175  -0.0724   0.6659   1.0000
   4.750   0.8161   0.02185   0.01173  -0.0718   0.6398   1.0000
   5.000   0.8437   0.02194   0.01188  -0.0710   0.6109   1.0000
   5.250   0.8699   0.02214   0.01206  -0.0699   0.5799   1.0000
   5.500   0.8937   0.02246   0.01237  -0.0687   0.5466   1.0000
   5.750   0.9166   0.02285   0.01276  -0.0672   0.5118   1.0000
   6.000   0.9378   0.02335   0.01319  -0.0657   0.4760   1.0000
   6.250   0.9574   0.02394   0.01373  -0.0640   0.4390   1.0000
   6.500   0.9757   0.02464   0.01433  -0.0623   0.4016   1.0000
   6.750   0.9926   0.02543   0.01502  -0.0604   0.3637   1.0000
   7.000   1.0082   0.02632   0.01586  -0.0585   0.3255   1.0000
   7.250   1.0227   0.02734   0.01673  -0.0566   0.2889   1.0000
   7.500   1.0369   0.02845   0.01776  -0.0548   0.2534   1.0000
   7.750   1.0502   0.02970   0.01889  -0.0530   0.2213   1.0000
   8.000   1.0631   0.03105   0.02014  -0.0512   0.1925   1.0000
   8.250   1.0765   0.03250   0.02156  -0.0495   0.1678   1.0000
   8.500   1.0886   0.03404   0.02298  -0.0478   0.1480   1.0000
   8.750   1.1028   0.03561   0.02459  -0.0463   0.1313   1.0000
   9.000   1.1162   0.03722   0.02623  -0.0447   0.1182   1.0000
   9.250   1.1287   0.03886   0.02785  -0.0431   0.1076   1.0000
   9.500   1.1471   0.04065   0.02990  -0.0420   0.0988   1.0000
   9.750   1.1653   0.04256   0.03185  -0.0411   0.0926   1.0000
  10.000   1.1813   0.04450   0.03405  -0.0399   0.0860   1.0000
  10.250   1.1963   0.04642   0.03593  -0.0389   0.0810   1.0000
  10.500   1.2115   0.04885   0.03881  -0.0377   0.0768   1.0000
  10.750   1.2259   0.05140   0.04165  -0.0365   0.0738   1.0000
  11.000   1.2381   0.05394   0.04440  -0.0354   0.0714   1.0000
  11.250   1.2529   0.05664   0.04716  -0.0347   0.0689   1.0000
  11.500   1.2475   0.05980   0.05081  -0.0322   0.0674   1.0000
  11.750   1.2391   0.06319   0.05461  -0.0301   0.0658   1.0000
  12.000   1.2283   0.06685   0.05862  -0.0284   0.0646   1.0000
  12.250   1.2149   0.07089   0.06297  -0.0273   0.0636   1.0000
  12.500   1.1983   0.07547   0.06783  -0.0270   0.0629   1.0000
  12.750   1.1773   0.08088   0.07351  -0.0277   0.0626   1.0000
  13.000   1.1504   0.08761   0.08049  -0.0300   0.0627   1.0000
  13.250   1.1159   0.09646   0.08958  -0.0346   0.0635   1.0000
  13.500   1.0751   0.10823   0.10146  -0.0420   0.0649   1.0000
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