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SA7025 (sa7025-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: SA7025 (sa7025-il)
Reynolds number: 50,000
Max Cl/Cd: 41.88 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sa7025-il-50000-n5.txt
Download as CSV file: xf-sa7025-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SA7025                                          
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3595   0.10141   0.09485  -0.0315   1.0000   0.1054
  -7.750  -0.3789   0.10095   0.09459  -0.0321   1.0000   0.1067
  -7.500  -0.3900   0.09926   0.09307  -0.0337   1.0000   0.1071
  -7.250  -0.3792   0.09468   0.08850  -0.0304   1.0000   0.1084
  -7.000  -0.3776   0.09170   0.08558  -0.0291   1.0000   0.1094
  -6.750  -0.3792   0.08902   0.08298  -0.0286   1.0000   0.1101
  -6.500  -0.3814   0.08634   0.08038  -0.0286   1.0000   0.1105
  -6.250  -0.3782   0.07783   0.07173  -0.0408   1.0000   0.0532
  -6.000  -0.3752   0.07558   0.06954  -0.0354   1.0000   0.0504
  -5.750  -0.3718   0.07226   0.06623  -0.0358   1.0000   0.0484
  -5.500  -0.3660   0.06846   0.06242  -0.0374   1.0000   0.0465
  -5.250  -0.3568   0.06416   0.05804  -0.0400   1.0000   0.0447
  -5.000  -0.3438   0.05956   0.05330  -0.0430   1.0000   0.0435
  -4.750  -0.3273   0.05493   0.04845  -0.0459   1.0000   0.0428
  -4.500  -0.3098   0.05110   0.04440  -0.0479   1.0000   0.0432
  -4.250  -0.2901   0.04744   0.04048  -0.0497   1.0000   0.0439
  -4.000  -0.2668   0.04357   0.03620  -0.0517   1.0000   0.0438
  -3.750  -0.2405   0.03972   0.03175  -0.0536   1.0000   0.0428
  -3.500  -0.2129   0.03630   0.02771  -0.0549   1.0000   0.0421
  -3.250  -0.1863   0.03365   0.02451  -0.0555   1.0000   0.0418
  -3.000  -0.1581   0.03137   0.02177  -0.0561   0.9992   0.0422
  -2.750  -0.1199   0.02929   0.01920  -0.0584   0.9943   0.0432
  -2.500  -0.0832   0.02763   0.01716  -0.0601   0.9887   0.0447
  -2.250  -0.0455   0.02629   0.01547  -0.0618   0.9832   0.0473
  -2.000  -0.0104   0.02527   0.01406  -0.0630   0.9764   0.0509
  -1.750   0.0286   0.02447   0.01305  -0.0653   0.9704   0.0629
  -1.500   0.0650   0.02358   0.01212  -0.0671   0.9629   0.0875
  -1.250   0.1011   0.02116   0.01179  -0.0697   0.9584   0.4792
  -1.000   0.1314   0.01987   0.01139  -0.0688   0.9493   1.0000
  -0.750   0.1710   0.02017   0.01110  -0.0712   0.9409   1.0000
  -0.500   0.2069   0.02044   0.01095  -0.0730   0.9310   1.0000
  -0.250   0.2409   0.02068   0.01086  -0.0744   0.9205   1.0000
   0.000   0.2765   0.02092   0.01079  -0.0761   0.9103   1.0000
   0.250   0.3164   0.02113   0.01074  -0.0785   0.9015   1.0000
   0.500   0.3486   0.02132   0.01076  -0.0794   0.8897   1.0000
   0.750   0.3813   0.02150   0.01078  -0.0803   0.8780   1.0000
   1.000   0.4146   0.02165   0.01081  -0.0813   0.8664   1.0000
   1.250   0.4478   0.02177   0.01083  -0.0822   0.8547   1.0000
   1.500   0.4809   0.02185   0.01084  -0.0830   0.8430   1.0000
   1.750   0.5141   0.02188   0.01084  -0.0837   0.8311   1.0000
   2.000   0.5469   0.02188   0.01081  -0.0842   0.8189   1.0000
   2.250   0.5780   0.02188   0.01080  -0.0843   0.8057   1.0000
   2.500   0.6072   0.02190   0.01083  -0.0841   0.7912   1.0000
   2.750   0.6357   0.02192   0.01092  -0.0838   0.7761   1.0000
   3.000   0.6644   0.02192   0.01096  -0.0835   0.7606   1.0000
   3.250   0.6935   0.02190   0.01098  -0.0831   0.7447   1.0000
   3.500   0.7232   0.02184   0.01098  -0.0827   0.7284   1.0000
   3.750   0.7538   0.02175   0.01101  -0.0824   0.7118   1.0000
   4.000   0.7809   0.02179   0.01113  -0.0817   0.6925   1.0000
   4.250   0.8092   0.02181   0.01121  -0.0810   0.6728   1.0000
   4.500   0.8367   0.02188   0.01134  -0.0802   0.6521   1.0000
   4.750   0.8639   0.02200   0.01152  -0.0794   0.6303   1.0000
   5.000   0.8892   0.02221   0.01190  -0.0784   0.6068   1.0000
   5.250   0.9147   0.02245   0.01220  -0.0774   0.5826   1.0000
   5.500   0.9395   0.02275   0.01254  -0.0763   0.5576   1.0000
   5.750   0.9633   0.02311   0.01296  -0.0751   0.5315   1.0000
   6.000   0.9859   0.02355   0.01347  -0.0738   0.5046   1.0000
   6.250   1.0077   0.02406   0.01404  -0.0724   0.4770   1.0000
   6.500   1.0285   0.02464   0.01477  -0.0710   0.4487   1.0000
   6.750   1.0482   0.02528   0.01549  -0.0694   0.4195   1.0000
   7.000   1.0669   0.02599   0.01628  -0.0678   0.3898   1.0000
   7.250   1.0847   0.02677   0.01714  -0.0661   0.3600   1.0000
   7.500   1.1014   0.02764   0.01807  -0.0643   0.3302   1.0000
   7.750   1.1166   0.02860   0.01907  -0.0624   0.3001   1.0000
   8.000   1.1300   0.02967   0.02024  -0.0604   0.2694   1.0000
   8.250   1.1415   0.03086   0.02150  -0.0582   0.2373   1.0000
   8.500   1.1506   0.03220   0.02285  -0.0560   0.2060   1.0000
   8.750   1.1569   0.03376   0.02436  -0.0535   0.1742   1.0000
   9.000   1.1602   0.03555   0.02611  -0.0509   0.1414   1.0000
   9.250   1.1593   0.03773   0.02815  -0.0480   0.1117   1.0000
   9.500   1.1558   0.04027   0.03048  -0.0455   0.0845   1.0000
  10.000   1.1521   0.04575   0.03587  -0.0416   0.0501   1.0000
  10.250   1.1511   0.04872   0.03897  -0.0398   0.0431   1.0000
  10.500   1.1492   0.05173   0.04205  -0.0385   0.0384   1.0000
  10.750   1.1493   0.05484   0.04535  -0.0373   0.0350   1.0000
  11.000   1.1509   0.05793   0.04872  -0.0363   0.0315   1.0000
  11.250   1.1502   0.06124   0.05221  -0.0356   0.0293   1.0000
  11.500   1.1485   0.06475   0.05587  -0.0353   0.0278   1.0000
  11.750   1.1474   0.06857   0.05984  -0.0349   0.0268   1.0000
  12.000   1.1473   0.07260   0.06425  -0.0347   0.0261   1.0000
  12.250   1.1440   0.07707   0.06905  -0.0351   0.0257   1.0000
  12.500   1.1367   0.08212   0.07443  -0.0362   0.0254   1.0000
  12.750   1.1267   0.08772   0.08031  -0.0380   0.0252   1.0000
  13.000   1.1145   0.09391   0.08676  -0.0407   0.0252   1.0000
  13.250   1.1009   0.10062   0.09370  -0.0440   0.0253   1.0000
  13.500   1.0864   0.10797   0.10125  -0.0481   0.0254   1.0000
  13.750   1.0717   0.11587   0.10934  -0.0527   0.0255   1.0000
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