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SA7025 (sa7025-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: SA7025 (sa7025-il)
Reynolds number: 500,000
Max Cl/Cd: 111.6 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sa7025-il-500000.txt
Download as CSV file: xf-sa7025-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3482   0.09124   0.08910  -0.0324   1.0000   0.0138
  -8.000  -0.3586   0.08974   0.08766  -0.0298   1.0000   0.0138
  -7.750  -0.3717   0.08844   0.08641  -0.0268   1.0000   0.0138
  -7.500  -0.3578   0.08417   0.08214  -0.0322   0.9970   0.0139
  -7.250  -0.3380   0.07906   0.07703  -0.0399   0.9926   0.0140
  -7.000  -0.3140   0.07331   0.07128  -0.0489   0.9880   0.0140
  -6.750  -0.2961   0.06432   0.06228  -0.0607   0.9844   0.0148
  -6.500  -0.2738   0.06124   0.05917  -0.0651   0.9814   0.0157
  -6.250  -0.2472   0.05632   0.05420  -0.0727   0.9766   0.0165
  -6.000  -0.2131   0.05041   0.04818  -0.0822   0.9736   0.0177
  -5.750  -0.1645   0.04360   0.04110  -0.0925   0.9716   0.0212
  -5.500  -0.1342   0.03893   0.03610  -0.0972   0.9670   0.0214
  -5.250  -0.1175   0.03173   0.02868  -0.1015   0.9611   0.0236
  -5.000  -0.0884   0.02976   0.02659  -0.1036   0.9582   0.0256
  -4.750  -0.0636   0.02718   0.02375  -0.1042   0.9525   0.0283
  -4.500  -0.0325   0.02732   0.02353  -0.1036   0.9475   0.0316
  -4.250  -0.0119   0.02139   0.01716  -0.1049   0.9431   0.0342
  -4.000   0.0103   0.01999   0.01568  -0.1042   0.9363   0.0361
  -3.750   0.0363   0.01854   0.01400  -0.1038   0.9316   0.0391
  -3.500   0.0648   0.01357   0.00819  -0.1016   0.9265   0.0182
  -3.250   0.0902   0.01196   0.00634  -0.1005   0.9205   0.0170
  -3.000   0.1166   0.01102   0.00527  -0.0998   0.9159   0.0173
  -2.750   0.1420   0.01036   0.00453  -0.0990   0.9090   0.0180
  -2.500   0.1684   0.00985   0.00394  -0.0984   0.9034   0.0191
  -2.250   0.1947   0.00948   0.00352  -0.0979   0.8969   0.0206
  -2.000   0.2215   0.00904   0.00299  -0.0974   0.8904   0.0210
  -1.750   0.2484   0.00869   0.00252  -0.0969   0.8835   0.0224
  -1.500   0.2753   0.00824   0.00215  -0.0964   0.8761   0.0596
  -1.250   0.3011   0.00751   0.00199  -0.0963   0.8678   0.2399
  -1.000   0.3272   0.00702   0.00190  -0.0960   0.8601   0.3869
  -0.750   0.3518   0.00640   0.00189  -0.0955   0.8502   0.5860
  -0.500   0.3829   0.00537   0.00185  -0.0954   0.8420   1.0000
  -0.250   0.4095   0.00538   0.00174  -0.0950   0.8321   1.0000
   0.000   0.4361   0.00540   0.00166  -0.0946   0.8204   1.0000
   0.250   0.4629   0.00543   0.00160  -0.0942   0.8078   1.0000
   0.500   0.4896   0.00546   0.00154  -0.0938   0.7939   1.0000
   0.750   0.5162   0.00552   0.00150  -0.0934   0.7787   1.0000
   1.000   0.5428   0.00559   0.00147  -0.0930   0.7619   1.0000
   1.250   0.5694   0.00567   0.00147  -0.0926   0.7439   1.0000
   1.500   0.5958   0.00578   0.00147  -0.0922   0.7252   1.0000
   1.750   0.6221   0.00591   0.00150  -0.0918   0.7058   1.0000
   2.000   0.6484   0.00606   0.00154  -0.0914   0.6850   1.0000
   2.250   0.6744   0.00622   0.00161  -0.0910   0.6640   1.0000
   2.500   0.7004   0.00640   0.00169  -0.0905   0.6417   1.0000
   2.750   0.7263   0.00658   0.00178  -0.0901   0.6193   1.0000
   3.000   0.7520   0.00679   0.00188  -0.0897   0.5969   1.0000
   3.250   0.7779   0.00699   0.00202  -0.0893   0.5742   1.0000
   3.500   0.8035   0.00720   0.00216  -0.0889   0.5516   1.0000
   3.750   0.8288   0.00745   0.00231  -0.0884   0.5268   1.0000
   4.000   0.8540   0.00771   0.00247  -0.0880   0.5009   1.0000
   4.250   0.8793   0.00796   0.00265  -0.0875   0.4761   1.0000
   4.500   0.9044   0.00824   0.00287  -0.0871   0.4515   1.0000
   4.750   0.9294   0.00853   0.00308  -0.0866   0.4271   1.0000
   5.000   0.9541   0.00884   0.00331  -0.0861   0.4021   1.0000
   5.250   0.9787   0.00917   0.00356  -0.0856   0.3756   1.0000
   5.500   1.0024   0.00958   0.00386  -0.0850   0.3415   1.0000
   5.750   1.0248   0.01012   0.00419  -0.0843   0.2959   1.0000
   6.000   1.0471   0.01068   0.00454  -0.0835   0.2536   1.0000
   6.250   1.0693   0.01126   0.00493  -0.0828   0.2132   1.0000
   6.500   1.0919   0.01180   0.00534  -0.0821   0.1827   1.0000
   6.750   1.1141   0.01238   0.00581  -0.0813   0.1502   1.0000
   7.000   1.1340   0.01320   0.00637  -0.0803   0.1065   1.0000
   7.250   1.1516   0.01428   0.00712  -0.0790   0.0569   1.0000
   7.500   1.1668   0.01562   0.00815  -0.0772   0.0154   1.0000
   7.750   1.1861   0.01651   0.00908  -0.0758   0.0094   1.0000
   8.000   1.2067   0.01722   0.00990  -0.0746   0.0084   1.0000
   8.250   1.2263   0.01800   0.01082  -0.0733   0.0078   1.0000
   8.500   1.2445   0.01888   0.01181  -0.0719   0.0072   1.0000
   8.750   1.2609   0.01987   0.01291  -0.0702   0.0069   1.0000
   9.000   1.2755   0.02095   0.01411  -0.0682   0.0067   1.0000
   9.250   1.2881   0.02214   0.01543  -0.0660   0.0067   1.0000
   9.500   1.2977   0.02344   0.01686  -0.0633   0.0066   1.0000
   9.750   1.3048   0.02477   0.01832  -0.0602   0.0066   1.0000
  10.000   1.3106   0.02628   0.01996  -0.0572   0.0066   1.0000
  10.250   1.3165   0.02793   0.02177  -0.0543   0.0067   1.0000
  10.500   1.3218   0.02991   0.02393  -0.0515   0.0068   1.0000
  10.750   1.3279   0.03214   0.02635  -0.0490   0.0069   1.0000
  11.000   1.3331   0.03481   0.02929  -0.0465   0.0071   1.0000
  11.250   1.3374   0.03728   0.03197  -0.0443   0.0072   1.0000
  11.500   1.3408   0.03924   0.03407  -0.0423   0.0070   1.0000
  11.750   1.3394   0.04243   0.03753  -0.0400   0.0071   1.0000
  12.000   1.3392   0.04464   0.03988  -0.0384   0.0068   1.0000
  12.250   1.3346   0.04778   0.04323  -0.0368   0.0068   1.0000
  12.500   1.3219   0.05228   0.04805  -0.0352   0.0070   1.0000
  12.750   1.3023   0.05785   0.05395  -0.0344   0.0074   1.0000
  13.000   1.2860   0.06297   0.05932  -0.0346   0.0075   1.0000
  13.250   1.2685   0.06858   0.06516  -0.0358   0.0076   1.0000
  13.500   1.2485   0.07502   0.07181  -0.0380   0.0078   1.0000
  13.750   1.2298   0.08175   0.07873  -0.0410   0.0079   1.0000
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