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SA7035 (sa7035-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: SA7035 (sa7035-il)
Reynolds number: 200,000
Max Cl/Cd: 71.3 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sa7035-il-200000.txt
Download as CSV file: xf-sa7035-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SA7035                                          
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3953   0.08649   0.08310  -0.0306   1.0000   0.0420
  -8.000  -0.3981   0.08293   0.07960  -0.0326   1.0000   0.0433
  -7.000  -0.4400   0.06803   0.06472  -0.0440   1.0000   0.0460
  -6.750  -0.4456   0.06526   0.06183  -0.0433   1.0000   0.0461
  -6.500  -0.4558   0.05909   0.05565  -0.0427   1.0000   0.0470
  -6.250  -0.4520   0.05637   0.05305  -0.0405   1.0000   0.0480
  -6.000  -0.4481   0.05426   0.05097  -0.0386   1.0000   0.0493
  -5.750  -0.4435   0.05178   0.04844  -0.0375   1.0000   0.0511
  -5.500  -0.4369   0.04877   0.04531  -0.0371   1.0000   0.0536
  -5.250  -0.4189   0.04319   0.03907  -0.0406   0.9981   0.0603
  -5.000  -0.3867   0.03974   0.03567  -0.0437   0.9943   0.0635
  -4.750  -0.3517   0.03580   0.03118  -0.0476   0.9887   0.0744
  -4.500  -0.3101   0.02623   0.02018  -0.0483   0.9856   0.0357
  -4.250  -0.2724   0.02313   0.01673  -0.0502   0.9823   0.0321
  -4.000  -0.2376   0.02031   0.01343  -0.0512   0.9772   0.0300
  -3.750  -0.1987   0.01832   0.01113  -0.0529   0.9733   0.0294
  -3.500  -0.1574   0.01684   0.00949  -0.0552   0.9702   0.0304
  -3.250  -0.1242   0.01577   0.00833  -0.0561   0.9629   0.0330
  -3.000  -0.0835   0.01465   0.00720  -0.0586   0.9586   0.0407
  -2.750  -0.0485   0.01301   0.00601  -0.0602   0.9524   0.1355
  -2.500  -0.0130   0.01171   0.00575  -0.0625   0.9465   0.3838
  -2.250   0.0253   0.01080   0.00570  -0.0646   0.9429   0.6113
  -2.000   0.0521   0.01042   0.00561  -0.0637   0.9336   0.7161
  -1.750   0.0867   0.01007   0.00547  -0.0640   0.9290   0.8081
  -1.500   0.1133   0.00988   0.00538  -0.0625   0.9194   0.8860
  -1.250   0.1657   0.00969   0.00512  -0.0664   0.9162   0.9518
  -1.000   0.2255   0.00948   0.00477  -0.0724   0.9118   0.9856
  -0.750   0.2733   0.00925   0.00440  -0.0764   0.9035   1.0000
  -0.500   0.2958   0.00912   0.00416  -0.0751   0.8901   1.0000
  -0.250   0.3183   0.00902   0.00396  -0.0738   0.8765   1.0000
   0.000   0.3410   0.00894   0.00377  -0.0724   0.8626   1.0000
   0.250   0.3642   0.00887   0.00361  -0.0711   0.8481   1.0000
   0.500   0.3878   0.00882   0.00346  -0.0699   0.8332   1.0000
   0.750   0.4120   0.00879   0.00333  -0.0687   0.8176   1.0000
   1.000   0.4365   0.00879   0.00322  -0.0677   0.8011   1.0000
   1.250   0.4610   0.00882   0.00317  -0.0667   0.7825   1.0000
   1.500   0.4860   0.00887   0.00312  -0.0658   0.7641   1.0000
   1.750   0.5114   0.00894   0.00308  -0.0650   0.7459   1.0000
   2.000   0.5365   0.00904   0.00310  -0.0643   0.7255   1.0000
   2.250   0.5619   0.00917   0.00314  -0.0635   0.7053   1.0000
   2.500   0.5871   0.00931   0.00319  -0.0628   0.6842   1.0000
   2.750   0.6124   0.00948   0.00325  -0.0621   0.6625   1.0000
   3.000   0.6375   0.00966   0.00335  -0.0614   0.6399   1.0000
   3.250   0.6627   0.00987   0.00347  -0.0607   0.6180   1.0000
   3.500   0.6878   0.01007   0.00361  -0.0601   0.5948   1.0000
   3.750   0.7128   0.01031   0.00377  -0.0595   0.5724   1.0000
   4.000   0.7377   0.01056   0.00394  -0.0588   0.5493   1.0000
   4.250   0.7625   0.01082   0.00416  -0.0582   0.5256   1.0000
   4.500   0.7870   0.01111   0.00437  -0.0576   0.5021   1.0000
   4.750   0.8113   0.01141   0.00461  -0.0569   0.4779   1.0000
   5.000   0.8356   0.01172   0.00487  -0.0563   0.4533   1.0000
   5.250   0.8597   0.01206   0.00518  -0.0556   0.4293   1.0000
   5.500   0.8835   0.01244   0.00548  -0.0549   0.4057   1.0000
   5.750   0.9072   0.01281   0.00583  -0.0542   0.3810   1.0000
   6.000   0.9307   0.01321   0.00620  -0.0535   0.3567   1.0000
   6.250   0.9536   0.01365   0.00660  -0.0528   0.3315   1.0000
   6.500   0.9761   0.01412   0.00701  -0.0520   0.3060   1.0000
   6.750   0.9984   0.01462   0.00746  -0.0512   0.2806   1.0000
   7.000   1.0205   0.01512   0.00795  -0.0504   0.2554   1.0000
   7.250   1.0422   0.01569   0.00848  -0.0496   0.2311   1.0000
   7.500   1.0632   0.01632   0.00908  -0.0486   0.2079   1.0000
   7.750   1.0838   0.01697   0.00970  -0.0477   0.1838   1.0000
   8.000   1.1040   0.01767   0.01038  -0.0467   0.1598   1.0000
   8.250   1.1229   0.01849   0.01115  -0.0456   0.1359   1.0000
   8.500   1.1403   0.01943   0.01200  -0.0443   0.1121   1.0000
   8.750   1.1563   0.02052   0.01299  -0.0429   0.0903   1.0000
   9.000   1.1716   0.02165   0.01411  -0.0413   0.0731   1.0000
   9.250   1.1851   0.02291   0.01541  -0.0394   0.0598   1.0000
   9.500   1.1963   0.02435   0.01687  -0.0373   0.0496   1.0000
   9.750   1.2030   0.02612   0.01860  -0.0348   0.0417   1.0000
  10.000   1.2141   0.02734   0.02000  -0.0325   0.0362   1.0000
  10.250   1.2147   0.02968   0.02232  -0.0294   0.0319   1.0000
  10.500   1.2254   0.03090   0.02374  -0.0273   0.0290   1.0000
  10.750   1.2327   0.03243   0.02538  -0.0252   0.0262   1.0000
  11.000   1.2373   0.03462   0.02762  -0.0231   0.0242   1.0000
  11.250   1.2434   0.03794   0.03113  -0.0212   0.0226   1.0000
  11.500   1.2481   0.03953   0.03295  -0.0193   0.0211   1.0000
  11.750   1.2519   0.04160   0.03524  -0.0176   0.0197   1.0000
  12.000   1.2534   0.04376   0.03756  -0.0162   0.0185   1.0000
  12.250   1.2535   0.04643   0.04040  -0.0150   0.0178   1.0000
  12.500   1.2520   0.04943   0.04356  -0.0140   0.0172   1.0000
  12.750   1.2474   0.05313   0.04745  -0.0133   0.0168   1.0000
  13.000   1.2386   0.05747   0.05203  -0.0129   0.0165   1.0000
  13.250   1.2271   0.06209   0.05690  -0.0132   0.0163   1.0000
  13.500   1.2130   0.06718   0.06224  -0.0142   0.0163   1.0000
  13.750   1.1953   0.07302   0.06833  -0.0161   0.0162   1.0000
  14.000   1.1809   0.07856   0.07408  -0.0184   0.0162   1.0000
  14.250   1.1656   0.08458   0.08032  -0.0215   0.0163   1.0000
  14.500   1.1499   0.09107   0.08700  -0.0253   0.0164   1.0000
  14.750   1.1330   0.09827   0.09440  -0.0297   0.0164   1.0000
  15.000   1.1150   0.10632   0.10265  -0.0351   0.0166   1.0000
  15.250   1.0885   0.11736   0.11396  -0.0429   0.0172   1.0000
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