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SA7035 (sa7035-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: SA7035 (sa7035-il)
Reynolds number: 200,000
Max Cl/Cd: 68.02 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sa7035-il-200000-n5.txt
Download as CSV file: xf-sa7035-il-200000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3308   0.08347   0.08013  -0.0307   1.0000   0.0117
  -9.000  -0.4048   0.09285   0.08928  -0.0274   1.0000   0.0152
  -8.750  -0.4100   0.08625   0.08273  -0.0306   1.0000   0.0115
  -8.500  -0.4098   0.08282   0.07934  -0.0318   1.0000   0.0113
  -8.250  -0.4107   0.07938   0.07595  -0.0331   1.0000   0.0110
  -8.000  -0.4156   0.07550   0.07214  -0.0347   1.0000   0.0109
  -7.750  -0.4241   0.07216   0.06889  -0.0355   1.0000   0.0107
  -7.500  -0.4349   0.06816   0.06496  -0.0375   1.0000   0.0105
  -7.250  -0.4438   0.06369   0.06051  -0.0398   1.0000   0.0103
  -7.000  -0.4518   0.05947   0.05626  -0.0407   1.0000   0.0100
  -6.750  -0.4454   0.05218   0.04881  -0.0461   0.9962   0.0097
  -6.500  -0.4254   0.04228   0.03844  -0.0535   0.9885   0.0090
  -6.250  -0.4034   0.03253   0.02780  -0.0581   0.9820   0.0085
  -6.000  -0.3779   0.02836   0.02306  -0.0598   0.9760   0.0086
  -5.750  -0.3472   0.02509   0.01926  -0.0617   0.9722   0.0088
  -5.500  -0.3170   0.02315   0.01698  -0.0629   0.9678   0.0094
  -5.250  -0.2866   0.02139   0.01487  -0.0638   0.9628   0.0103
  -5.000  -0.2529   0.01991   0.01299  -0.0650   0.9589   0.0115
  -4.750  -0.2218   0.01841   0.01118  -0.0656   0.9540   0.0118
  -4.500  -0.1926   0.01692   0.00954  -0.0659   0.9479   0.0121
  -4.250  -0.1606   0.01561   0.00813  -0.0669   0.9436   0.0129
  -4.000  -0.1337   0.01480   0.00724  -0.0667   0.9360   0.0136
  -3.750  -0.1026   0.01406   0.00639  -0.0673   0.9303   0.0151
  -3.500  -0.0751   0.01349   0.00568  -0.0671   0.9224   0.0170
  -3.250  -0.0452   0.01284   0.00498  -0.0674   0.9157   0.0255
  -3.000  -0.0191   0.01211   0.00443  -0.0670   0.9064   0.0646
  -2.750   0.0080   0.01136   0.00408  -0.0671   0.8983   0.1575
  -2.500   0.0336   0.01066   0.00384  -0.0669   0.8886   0.2785
  -2.250   0.0594   0.01022   0.00362  -0.0666   0.8784   0.3642
  -2.000   0.0854   0.00979   0.00344  -0.0661   0.8686   0.4545
  -1.750   0.1109   0.00941   0.00332  -0.0654   0.8584   0.5477
  -1.500   0.1352   0.00910   0.00324  -0.0643   0.8465   0.6328
  -1.250   0.1593   0.00884   0.00315  -0.0630   0.8342   0.7063
  -1.000   0.1831   0.00865   0.00306  -0.0616   0.8212   0.7677
  -0.750   0.2070   0.00850   0.00298  -0.0601   0.8075   0.8242
  -0.500   0.2339   0.00839   0.00288  -0.0591   0.7931   0.8798
  -0.250   0.2682   0.00833   0.00276  -0.0599   0.7778   0.9306
   0.000   0.3075   0.00830   0.00260  -0.0620   0.7615   0.9697
   0.250   0.3481   0.00829   0.00245  -0.0646   0.7436   0.9987
   0.500   0.3734   0.00836   0.00239  -0.0640   0.7250   1.0000
   0.750   0.3981   0.00846   0.00234  -0.0633   0.7059   1.0000
   1.000   0.4230   0.00858   0.00232  -0.0626   0.6863   1.0000
   1.250   0.4482   0.00870   0.00233  -0.0620   0.6665   1.0000
   1.500   0.4734   0.00885   0.00235  -0.0613   0.6470   1.0000
   1.750   0.4989   0.00900   0.00239  -0.0608   0.6271   1.0000
   2.000   0.5243   0.00917   0.00245  -0.0603   0.6071   1.0000
   2.250   0.5497   0.00934   0.00253  -0.0598   0.5871   1.0000
   2.500   0.5751   0.00953   0.00262  -0.0593   0.5664   1.0000
   2.750   0.6005   0.00974   0.00273  -0.0588   0.5451   1.0000
   3.000   0.6257   0.00996   0.00285  -0.0583   0.5230   1.0000
   3.250   0.6510   0.01019   0.00301  -0.0578   0.5015   1.0000
   3.500   0.6763   0.01042   0.00317  -0.0573   0.4808   1.0000
   3.750   0.7015   0.01068   0.00335  -0.0568   0.4603   1.0000
   4.000   0.7267   0.01093   0.00355  -0.0564   0.4393   1.0000
   4.250   0.7516   0.01122   0.00379  -0.0559   0.4185   1.0000
   4.500   0.7765   0.01151   0.00403  -0.0554   0.3968   1.0000
   4.750   0.8011   0.01183   0.00429  -0.0549   0.3751   1.0000
   5.000   0.8257   0.01216   0.00457  -0.0545   0.3532   1.0000
   5.250   0.8502   0.01250   0.00489  -0.0540   0.3321   1.0000
   5.500   0.8745   0.01286   0.00522  -0.0535   0.3112   1.0000
   5.750   0.8986   0.01324   0.00557  -0.0529   0.2914   1.0000
   6.000   0.9226   0.01364   0.00594  -0.0524   0.2709   1.0000
   6.250   0.9460   0.01408   0.00637  -0.0518   0.2494   1.0000
   6.500   0.9691   0.01456   0.00680  -0.0512   0.2264   1.0000
   6.750   0.9920   0.01506   0.00726  -0.0506   0.2045   1.0000
   7.000   1.0144   0.01560   0.00776  -0.0499   0.1834   1.0000
   7.250   1.0369   0.01614   0.00828  -0.0493   0.1635   1.0000
   7.500   1.0588   0.01673   0.00888  -0.0485   0.1451   1.0000
   7.750   1.0802   0.01737   0.00950  -0.0477   0.1268   1.0000
   8.000   1.1013   0.01803   0.01015  -0.0469   0.1092   1.0000
   8.250   1.1213   0.01878   0.01087  -0.0460   0.0920   1.0000
   8.500   1.1406   0.01959   0.01165  -0.0450   0.0753   1.0000
   8.750   1.1593   0.02043   0.01249  -0.0439   0.0603   1.0000
   9.000   1.1771   0.02133   0.01342  -0.0428   0.0487   1.0000
   9.250   1.1939   0.02229   0.01441  -0.0415   0.0405   1.0000
   9.500   1.2094   0.02332   0.01549  -0.0400   0.0337   1.0000
   9.750   1.2247   0.02432   0.01660  -0.0385   0.0283   1.0000
  10.000   1.2359   0.02560   0.01792  -0.0366   0.0238   1.0000
  10.250   1.2470   0.02671   0.01920  -0.0345   0.0212   1.0000
  10.500   1.2555   0.02790   0.02051  -0.0322   0.0188   1.0000
  10.750   1.2594   0.02941   0.02210  -0.0296   0.0168   1.0000
  11.000   1.2638   0.03094   0.02378  -0.0272   0.0154   1.0000
  11.250   1.2696   0.03242   0.02542  -0.0253   0.0139   1.0000
  11.500   1.2736   0.03410   0.02727  -0.0234   0.0129   1.0000
  11.750   1.2754   0.03602   0.02929  -0.0219   0.0115   1.0000
  12.000   1.2718   0.03858   0.03197  -0.0203   0.0109   1.0000
  12.250   1.2742   0.04073   0.03432  -0.0193   0.0102   1.0000
  12.500   1.2735   0.04334   0.03712  -0.0186   0.0094   1.0000
  12.750   1.2710   0.04629   0.04023  -0.0183   0.0089   1.0000
  13.000   1.2672   0.04958   0.04368  -0.0184   0.0084   1.0000
  13.250   1.2626   0.05317   0.04743  -0.0189   0.0083   1.0000
  13.500   1.2562   0.05720   0.05162  -0.0199   0.0080   1.0000
  13.750   1.2480   0.06172   0.05630  -0.0213   0.0078   1.0000
  14.000   1.2366   0.06696   0.06168  -0.0233   0.0075   1.0000
  14.500   1.2140   0.07813   0.07317  -0.0281   0.0072   1.0000
  14.750   1.2040   0.08398   0.07923  -0.0309   0.0070   1.0000
  15.000   1.1923   0.09030   0.08572  -0.0340   0.0070   1.0000
  15.250   1.1803   0.09702   0.09263  -0.0376   0.0069   1.0000
  15.500   1.1677   0.10416   0.09996  -0.0416   0.0067   1.0000
  15.750   1.1546   0.11151   0.10746  -0.0456   0.0068   1.0000
  16.000   1.1412   0.11934   0.11546  -0.0502   0.0067   1.0000
  16.250   1.1271   0.12742   0.12367  -0.0547   0.0068   1.0000
  16.500   1.1131   0.13591   0.13231  -0.0597   0.0068   1.0000
  16.750   1.0988   0.14472   0.14126  -0.0649   0.0069   1.0000
  17.000   1.0847   0.15385   0.15051  -0.0703   0.0069   1.0000
  17.250   1.0691   0.16391   0.16067  -0.0762   0.0070   1.0000
  17.500   1.0553   0.17379   0.17062  -0.0819   0.0072   1.0000
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