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S7075 (9%) (s7075-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: S7075 (9%) (s7075-il)
Reynolds number: 100,000
Max Cl/Cd: 57.66 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s7075-il-100000-n5.txt
Download as CSV file: xf-s7075-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3880   0.09199   0.08702  -0.0366   1.0000   0.0340
  -8.250  -0.3924   0.08919   0.08430  -0.0359   1.0000   0.0327
  -8.000  -0.4015   0.08638   0.08157  -0.0350   1.0000   0.0314
  -7.500  -0.4472   0.07720   0.07259  -0.0377   1.0000   0.0271
  -7.250  -0.4530   0.07411   0.06954  -0.0375   1.0000   0.0268
  -7.000  -0.4574   0.07065   0.06610  -0.0380   1.0000   0.0265
  -6.750  -0.4600   0.06674   0.06217  -0.0390   1.0000   0.0262
  -6.500  -0.4601   0.06235   0.05772  -0.0405   1.0000   0.0259
  -6.250  -0.4538   0.05681   0.05202  -0.0436   0.9991   0.0258
  -6.000  -0.4285   0.04905   0.04380  -0.0510   0.9944   0.0263
  -5.750  -0.4028   0.04305   0.03724  -0.0558   0.9898   0.0267
  -5.500  -0.3746   0.03823   0.03187  -0.0593   0.9859   0.0267
  -5.250  -0.3440   0.03427   0.02734  -0.0621   0.9828   0.0266
  -5.000  -0.3156   0.03106   0.02359  -0.0635   0.9787   0.0266
  -4.750  -0.2844   0.02843   0.02039  -0.0650   0.9752   0.0268
  -4.500  -0.2507   0.02631   0.01776  -0.0665   0.9722   0.0273
  -4.250  -0.2185   0.02433   0.01554  -0.0678   0.9693   0.0280
  -4.000  -0.1899   0.02300   0.01408  -0.0683   0.9646   0.0294
  -3.750  -0.1573   0.02208   0.01300  -0.0695   0.9606   0.0322
  -3.500  -0.1221   0.02116   0.01188  -0.0709   0.9574   0.0357
  -3.250  -0.0928   0.02011   0.01080  -0.0714   0.9526   0.0385
  -3.000  -0.0615   0.01935   0.00998  -0.0722   0.9476   0.0437
  -2.750  -0.0262   0.01863   0.00920  -0.0737   0.9438   0.0569
  -2.500   0.0045   0.01787   0.00865  -0.0746   0.9386   0.0936
  -2.250   0.0348   0.01706   0.00830  -0.0755   0.9330   0.1888
  -2.000   0.0698   0.01631   0.00808  -0.0773   0.9291   0.3341
  -1.750   0.0961   0.01566   0.00803  -0.0771   0.9225   0.4968
  -1.500   0.1226   0.01509   0.00809  -0.0761   0.9168   0.6753
  -1.250   0.1503   0.01483   0.00808  -0.0748   0.9120   0.8164
  -1.000   0.1763   0.01465   0.00790  -0.0735   0.9039   0.8961
  -0.750   0.2327   0.01442   0.00755  -0.0790   0.9009   1.0000
  -0.500   0.2629   0.01441   0.00739  -0.0795   0.8928   1.0000
  -0.250   0.2979   0.01435   0.00718  -0.0807   0.8862   1.0000
   0.000   0.3266   0.01434   0.00705  -0.0808   0.8770   1.0000
   0.250   0.3624   0.01423   0.00683  -0.0821   0.8705   1.0000
   0.500   0.3892   0.01422   0.00674  -0.0818   0.8597   1.0000
   0.750   0.4193   0.01415   0.00660  -0.0820   0.8500   1.0000
   1.000   0.4526   0.01401   0.00641  -0.0826   0.8414   1.0000
   1.250   0.4798   0.01396   0.00632  -0.0822   0.8289   1.0000
   1.500   0.5077   0.01390   0.00622  -0.0819   0.8162   1.0000
   1.750   0.5361   0.01383   0.00613  -0.0816   0.8027   1.0000
   2.000   0.5647   0.01376   0.00604  -0.0814   0.7881   1.0000
   2.250   0.5939   0.01368   0.00594  -0.0812   0.7724   1.0000
   2.500   0.6242   0.01359   0.00582  -0.0812   0.7556   1.0000
   2.750   0.6526   0.01356   0.00579  -0.0809   0.7356   1.0000
   3.000   0.6826   0.01352   0.00570  -0.0808   0.7144   1.0000
   3.250   0.7113   0.01355   0.00568  -0.0805   0.6905   1.0000
   3.500   0.7396   0.01364   0.00572  -0.0802   0.6649   1.0000
   3.750   0.7669   0.01380   0.00579  -0.0797   0.6375   1.0000
   4.000   0.7929   0.01402   0.00592  -0.0790   0.6085   1.0000
   4.250   0.8180   0.01430   0.00611  -0.0782   0.5778   1.0000
   4.500   0.8421   0.01463   0.00636  -0.0773   0.5456   1.0000
   4.750   0.8655   0.01501   0.00663  -0.0763   0.5124   1.0000
   5.000   0.8883   0.01543   0.00693  -0.0753   0.4790   1.0000
   5.250   0.9104   0.01589   0.00729  -0.0742   0.4442   1.0000
   5.500   0.9316   0.01640   0.00771  -0.0730   0.4085   1.0000
   5.750   0.9524   0.01696   0.00814  -0.0717   0.3720   1.0000
   6.000   0.9724   0.01759   0.00862  -0.0705   0.3351   1.0000
   6.250   0.9922   0.01824   0.00915  -0.0692   0.2989   1.0000
   6.500   1.0114   0.01896   0.00974  -0.0679   0.2637   1.0000
   6.750   1.0302   0.01973   0.01040  -0.0667   0.2297   1.0000
   7.000   1.0488   0.02054   0.01110  -0.0654   0.1972   1.0000
   7.250   1.0667   0.02142   0.01185  -0.0641   0.1668   1.0000
   7.500   1.0844   0.02235   0.01268  -0.0628   0.1404   1.0000
   7.750   1.1012   0.02334   0.01360  -0.0613   0.1192   1.0000
   8.000   1.1181   0.02434   0.01459  -0.0599   0.1028   1.0000
   8.250   1.1338   0.02541   0.01565  -0.0583   0.0904   1.0000
   8.500   1.1482   0.02656   0.01677  -0.0566   0.0806   1.0000
   8.750   1.1635   0.02762   0.01792  -0.0549   0.0723   1.0000
   9.000   1.1763   0.02886   0.01923  -0.0530   0.0669   1.0000
   9.250   1.1894   0.03003   0.02053  -0.0510   0.0626   1.0000
   9.500   1.2008   0.03131   0.02187  -0.0490   0.0592   1.0000
   9.750   1.2112   0.03281   0.02339  -0.0469   0.0565   1.0000
  10.000   1.2251   0.03413   0.02491  -0.0452   0.0534   1.0000
  10.250   1.2376   0.03549   0.02641  -0.0436   0.0506   1.0000
  10.500   1.2489   0.03695   0.02796  -0.0419   0.0484   1.0000
  10.750   1.2604   0.03868   0.02979  -0.0403   0.0468   1.0000
  11.000   1.2744   0.04070   0.03192  -0.0391   0.0454   1.0000
  11.250   1.2874   0.04261   0.03411  -0.0377   0.0443   1.0000
  11.500   1.2981   0.04470   0.03648  -0.0362   0.0430   1.0000
  11.750   1.3055   0.04684   0.03888  -0.0345   0.0416   1.0000
  12.000   1.3101   0.04903   0.04130  -0.0328   0.0403   1.0000
  12.250   1.3127   0.05124   0.04372  -0.0312   0.0391   1.0000
  12.500   1.3144   0.05363   0.04629  -0.0297   0.0381   1.0000
  12.750   1.3149   0.05635   0.04919  -0.0284   0.0374   1.0000
  13.000   1.3137   0.05937   0.05240  -0.0274   0.0368   1.0000
  13.250   1.3103   0.06287   0.05613  -0.0265   0.0362   1.0000
  13.500   1.3018   0.06705   0.06051  -0.0260   0.0358   1.0000
  13.750   1.2870   0.07150   0.06527  -0.0260   0.0356   1.0000
  14.000   1.2695   0.07656   0.07064  -0.0268   0.0355   1.0000
  14.250   1.2499   0.08232   0.07667  -0.0286   0.0353   1.0000
  14.500   1.2280   0.08891   0.08352  -0.0315   0.0353   1.0000
  14.750   1.2044   0.09639   0.09124  -0.0355   0.0353   1.0000
  15.000   1.1790   0.10499   0.10001  -0.0407   0.0355   1.0000
  15.250   1.1515   0.11492   0.11012  -0.0472   0.0356   1.0000
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