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SA7026 (sa7026-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: SA7026 (sa7026-il)
Reynolds number: 200,000
Max Cl/Cd: 82.78 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sa7026-il-200000-n5.txt
Download as CSV file: xf-sa7026-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SA7026                                          
  
 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  -0.3380   0.10264   0.09925  -0.0408   1.0000   0.0225
  -9.000  -0.3336   0.10072   0.09735  -0.0378   1.0000   0.0238
  -8.750  -0.3395   0.09877   0.09546  -0.0363   0.9999   0.0240
  -8.500  -0.3255   0.09516   0.09185  -0.0394   0.9963   0.0251
  -8.250  -0.3132   0.09124   0.08793  -0.0432   0.9916   0.0259
  -8.000  -0.3003   0.08733   0.08403  -0.0475   0.9868   0.0266
  -7.750  -0.2857   0.08303   0.07973  -0.0527   0.9829   0.0272
  -7.500  -0.2742   0.07908   0.07580  -0.0573   0.9760   0.0279
  -7.250  -0.2576   0.07432   0.07104  -0.0643   0.9708   0.0286
  -7.000  -0.2419   0.06951   0.06621  -0.0713   0.9631   0.0290
  -6.750  -0.2203   0.06387   0.06054  -0.0802   0.9578   0.0289
  -6.500  -0.2019   0.05498   0.05151  -0.0908   0.9483   0.0201
  -6.250  -0.1809   0.04905   0.04542  -0.0974   0.9433   0.0182
  -5.750  -0.1423   0.03471   0.03023  -0.1054   0.9293   0.0139
  -5.500  -0.1261   0.03115   0.02631  -0.1057   0.9217   0.0136
  -5.250  -0.1031   0.02755   0.02225  -0.1065   0.9172   0.0133
  -5.000  -0.0813   0.02471   0.01895  -0.1063   0.9116   0.0132
  -4.750  -0.0574   0.02237   0.01615  -0.1060   0.9064   0.0132
  -4.500  -0.0305   0.02038   0.01371  -0.1060   0.9028   0.0133
  -4.250  -0.0061   0.01891   0.01192  -0.1053   0.8972   0.0135
  -4.000   0.0202   0.01784   0.01058  -0.1048   0.8923   0.0142
  -3.750   0.0473   0.01650   0.00907  -0.1048   0.8886   0.0157
  -3.500   0.0717   0.01568   0.00816  -0.1041   0.8823   0.0165
  -3.250   0.0982   0.01485   0.00721  -0.1037   0.8773   0.0167
  -3.000   0.1251   0.01417   0.00641  -0.1033   0.8728   0.0170
  -2.750   0.1505   0.01366   0.00580  -0.1028   0.8665   0.0176
  -2.500   0.1783   0.01320   0.00521  -0.1026   0.8620   0.0184
  -2.250   0.2046   0.01286   0.00477  -0.1022   0.8559   0.0196
  -2.000   0.2319   0.01255   0.00435  -0.1018   0.8503   0.0224
  -1.750   0.2589   0.01203   0.00397  -0.1016   0.8451   0.0672
  -1.500   0.2836   0.01130   0.00382  -0.1014   0.8380   0.2221
  -1.250   0.3089   0.01059   0.00371  -0.1012   0.8325   0.4053
  -1.000   0.3279   0.00978   0.00379  -0.0993   0.8245   0.6537
  -0.750   0.3502   0.00932   0.00368  -0.0974   0.8188   0.7953
  -0.500   0.3990   0.00899   0.00349  -0.1013   0.8123   0.9877
  -0.250   0.4282   0.00897   0.00332  -0.1014   0.8061   1.0000
   0.000   0.4539   0.00902   0.00327  -0.1010   0.7972   1.0000
   0.250   0.4807   0.00904   0.00317  -0.1007   0.7895   1.0000
   0.500   0.5073   0.00906   0.00310  -0.1003   0.7803   1.0000
   0.750   0.5335   0.00910   0.00305  -0.0999   0.7701   1.0000
   1.000   0.5601   0.00913   0.00301  -0.0995   0.7602   1.0000
   1.250   0.5870   0.00917   0.00296  -0.0992   0.7504   1.0000
   1.500   0.6134   0.00923   0.00296  -0.0988   0.7394   1.0000
   1.750   0.6397   0.00930   0.00297  -0.0984   0.7280   1.0000
   2.000   0.6661   0.00938   0.00301  -0.0980   0.7160   1.0000
   2.250   0.6923   0.00947   0.00305  -0.0976   0.7028   1.0000
   2.500   0.7183   0.00956   0.00309  -0.0972   0.6881   1.0000
   2.750   0.7442   0.00968   0.00314  -0.0967   0.6721   1.0000
   3.000   0.7699   0.00981   0.00324  -0.0962   0.6553   1.0000
   3.250   0.7953   0.00996   0.00334  -0.0956   0.6376   1.0000
   3.500   0.8205   0.01014   0.00346  -0.0951   0.6192   1.0000
   3.750   0.8454   0.01034   0.00360  -0.0945   0.6002   1.0000
   4.000   0.8700   0.01055   0.00377  -0.0938   0.5793   1.0000
   4.250   0.8940   0.01080   0.00399  -0.0931   0.5571   1.0000
   4.500   0.9174   0.01109   0.00420  -0.0922   0.5322   1.0000
   4.750   0.9403   0.01141   0.00445  -0.0913   0.5063   1.0000
   5.000   0.9629   0.01176   0.00473  -0.0904   0.4805   1.0000
   5.250   0.9852   0.01212   0.00503  -0.0895   0.4556   1.0000
   5.500   1.0071   0.01252   0.00541  -0.0884   0.4306   1.0000
   5.750   1.0284   0.01295   0.00578  -0.0874   0.4045   1.0000
   6.000   1.0489   0.01342   0.00618  -0.0862   0.3749   1.0000
   6.250   1.0674   0.01401   0.00663  -0.0847   0.3377   1.0000
   6.500   1.0835   0.01476   0.00715  -0.0829   0.2899   1.0000
   6.750   1.0987   0.01559   0.00776  -0.0811   0.2410   1.0000
   7.000   1.1142   0.01644   0.00839  -0.0794   0.1964   1.0000
   7.250   1.1294   0.01733   0.00907  -0.0776   0.1542   1.0000
   7.500   1.1443   0.01825   0.00981  -0.0759   0.1182   1.0000
   7.750   1.1567   0.01936   0.01067  -0.0738   0.0778   1.0000
   8.000   1.1668   0.02060   0.01167  -0.0715   0.0419   1.0000
   8.250   1.1757   0.02182   0.01276  -0.0687   0.0193   1.0000
   8.500   1.1869   0.02286   0.01383  -0.0663   0.0129   1.0000
   8.750   1.1977   0.02395   0.01498  -0.0639   0.0104   1.0000
   9.000   1.2106   0.02486   0.01607  -0.0619   0.0089   1.0000
   9.250   1.2219   0.02590   0.01724  -0.0598   0.0080   1.0000
   9.500   1.2322   0.02704   0.01852  -0.0577   0.0076   1.0000
   9.750   1.2401   0.02838   0.02000  -0.0554   0.0072   1.0000
  10.000   1.2462   0.02989   0.02166  -0.0531   0.0069   1.0000
  10.250   1.2489   0.03170   0.02362  -0.0506   0.0066   1.0000
  10.500   1.2539   0.03337   0.02544  -0.0485   0.0066   1.0000
  10.750   1.2579   0.03520   0.02743  -0.0465   0.0065   1.0000
  11.000   1.2614   0.03717   0.02955  -0.0446   0.0063   1.0000
  11.250   1.2639   0.03934   0.03188  -0.0428   0.0062   1.0000
  11.500   1.2668   0.04157   0.03427  -0.0412   0.0062   1.0000
  11.750   1.2691   0.04397   0.03688  -0.0398   0.0061   1.0000
  12.000   1.2713   0.04649   0.03956  -0.0385   0.0060   1.0000
  12.250   1.2730   0.04918   0.04244  -0.0373   0.0060   1.0000
  12.500   1.2741   0.05201   0.04545  -0.0364   0.0060   1.0000
  12.750   1.2739   0.05510   0.04874  -0.0356   0.0059   1.0000
  13.000   1.2722   0.05845   0.05231  -0.0351   0.0059   1.0000
  13.250   1.2688   0.06212   0.05620  -0.0348   0.0059   1.0000
  13.500   1.2635   0.06612   0.06042  -0.0349   0.0059   1.0000
  13.750   1.2561   0.07055   0.06508  -0.0354   0.0059   1.0000
  14.000   1.2474   0.07533   0.07010  -0.0363   0.0059   1.0000
  14.250   1.2367   0.08068   0.07567  -0.0379   0.0059   1.0000
  14.500   1.2251   0.08640   0.08162  -0.0400   0.0059   1.0000
  14.750   1.2124   0.09264   0.08807  -0.0427   0.0059   1.0000
  15.000   1.1983   0.09949   0.09514  -0.0461   0.0059   1.0000
  15.250   1.1842   0.10668   0.10253  -0.0499   0.0060   1.0000
  15.500   1.1691   0.11456   0.11060  -0.0545   0.0060   1.0000
  15.750   1.1544   0.12273   0.11895  -0.0594   0.0060   1.0000
  16.000   1.1385   0.13171   0.12810  -0.0650   0.0061   1.0000
  16.250   1.1235   0.14091   0.13744  -0.0708   0.0061   1.0000
  16.500   1.1080   0.15086   0.14753  -0.0771   0.0062   1.0000
  16.750   1.0919   0.16167   0.15845  -0.0838   0.0062   1.0000
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