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SA7025 (sa7025-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: SA7025 (sa7025-il)
Reynolds number: 100,000
Max Cl/Cd: 60.42 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sa7025-il-100000-n5.txt
Download as CSV file: xf-sa7025-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3576   0.09321   0.08863  -0.0329   1.0000   0.0515
  -7.500  -0.3729   0.09205   0.08759  -0.0318   1.0000   0.0521
  -7.250  -0.3848   0.09025   0.08589  -0.0325   1.0000   0.0524
  -7.000  -0.3909   0.08782   0.08352  -0.0344   1.0000   0.0527
  -6.750  -0.3935   0.08481   0.08054  -0.0366   1.0000   0.0528
  -6.500  -0.3931   0.08145   0.07716  -0.0390   1.0000   0.0530
  -6.250  -0.3932   0.07733   0.07312  -0.0380   1.0000   0.0534
  -6.000  -0.3814   0.07311   0.06893  -0.0378   0.9972   0.0543
  -5.500  -0.3318   0.06205   0.05767  -0.0471   0.9873   0.0358
  -5.250  -0.2896   0.05219   0.04740  -0.0592   0.9820   0.0269
  -5.000  -0.2632   0.04730   0.04229  -0.0636   0.9760   0.0258
  -4.750  -0.2298   0.04195   0.03659  -0.0689   0.9715   0.0246
  -4.500  -0.1972   0.03715   0.03135  -0.0729   0.9667   0.0237
  -4.250  -0.1645   0.03286   0.02646  -0.0757   0.9615   0.0229
  -4.000  -0.1281   0.02917   0.02213  -0.0784   0.9578   0.0224
  -3.750  -0.0946   0.02642   0.01881  -0.0800   0.9534   0.0222
  -3.500  -0.0624   0.02444   0.01637  -0.0810   0.9480   0.0233
  -3.250  -0.0260   0.02295   0.01448  -0.0826   0.9442   0.0257
  -3.000   0.0066   0.02167   0.01287  -0.0833   0.9390   0.0273
  -2.750   0.0392   0.02042   0.01142  -0.0840   0.9335   0.0278
  -2.500   0.0759   0.01908   0.00993  -0.0857   0.9299   0.0291
  -2.250   0.1050   0.01825   0.00900  -0.0859   0.9228   0.0313
  -2.000   0.1403   0.01759   0.00820  -0.0872   0.9177   0.0350
  -1.750   0.1720   0.01696   0.00750  -0.0877   0.9112   0.0461
  -1.500   0.2033   0.01583   0.00708  -0.0888   0.9049   0.2104
  -1.250   0.2300   0.01435   0.00709  -0.0888   0.8993   0.6003
  -1.000   0.2685   0.01344   0.00681  -0.0895   0.8933   1.0000
  -0.750   0.3036   0.01338   0.00647  -0.0906   0.8871   1.0000
  -0.500   0.3315   0.01338   0.00625  -0.0904   0.8772   1.0000
  -0.250   0.3603   0.01336   0.00606  -0.0904   0.8678   1.0000
   0.000   0.3935   0.01328   0.00581  -0.0911   0.8606   1.0000
   0.250   0.4202   0.01328   0.00569  -0.0906   0.8493   1.0000
   0.500   0.4478   0.01326   0.00556  -0.0903   0.8382   1.0000
   0.750   0.4761   0.01323   0.00543  -0.0901   0.8270   1.0000
   1.000   0.5046   0.01319   0.00530  -0.0898   0.8153   1.0000
   1.250   0.5328   0.01316   0.00519  -0.0896   0.8029   1.0000
   1.500   0.5605   0.01314   0.00512  -0.0892   0.7894   1.0000
   1.750   0.5880   0.01313   0.00506  -0.0888   0.7749   1.0000
   2.000   0.6154   0.01314   0.00502  -0.0883   0.7595   1.0000
   2.250   0.6431   0.01315   0.00499  -0.0879   0.7432   1.0000
   2.500   0.6709   0.01317   0.00498  -0.0875   0.7261   1.0000
   2.750   0.6979   0.01323   0.00500  -0.0870   0.7073   1.0000
   3.000   0.7247   0.01332   0.00504  -0.0865   0.6873   1.0000
   3.250   0.7513   0.01345   0.00511  -0.0859   0.6670   1.0000
   3.500   0.7773   0.01362   0.00528  -0.0853   0.6454   1.0000
   3.750   0.8029   0.01382   0.00544  -0.0846   0.6232   1.0000
   4.000   0.8283   0.01405   0.00562  -0.0839   0.6006   1.0000
   4.250   0.8530   0.01432   0.00585  -0.0831   0.5763   1.0000
   4.500   0.8774   0.01462   0.00612  -0.0823   0.5518   1.0000
   4.750   0.9014   0.01495   0.00647  -0.0815   0.5269   1.0000
   5.000   0.9251   0.01531   0.00680  -0.0806   0.5018   1.0000
   5.250   0.9483   0.01570   0.00716  -0.0797   0.4761   1.0000
   5.500   0.9711   0.01613   0.00757  -0.0787   0.4495   1.0000
   5.750   0.9933   0.01658   0.00801  -0.0777   0.4222   1.0000
   6.000   1.0152   0.01708   0.00849  -0.0767   0.3948   1.0000
   6.250   1.0366   0.01761   0.00908  -0.0756   0.3677   1.0000
   6.500   1.0576   0.01817   0.00966  -0.0745   0.3402   1.0000
   6.750   1.0779   0.01879   0.01027  -0.0733   0.3123   1.0000
   7.000   1.0974   0.01947   0.01094  -0.0720   0.2829   1.0000
   7.250   1.1163   0.02020   0.01167  -0.0707   0.2511   1.0000
   7.500   1.1329   0.02109   0.01244  -0.0692   0.2126   1.0000
   7.750   1.1472   0.02223   0.01336  -0.0676   0.1633   1.0000
   8.000   1.1598   0.02362   0.01440  -0.0659   0.1100   1.0000
   8.250   1.1720   0.02513   0.01562  -0.0641   0.0658   1.0000
   8.500   1.1820   0.02688   0.01715  -0.0620   0.0349   1.0000
   8.750   1.1914   0.02864   0.01894  -0.0595   0.0232   1.0000
   9.000   1.1998   0.03038   0.02080  -0.0570   0.0190   1.0000
   9.250   1.2047   0.03216   0.02276  -0.0541   0.0171   1.0000
   9.500   1.2098   0.03381   0.02465  -0.0512   0.0160   1.0000
   9.750   1.2136   0.03561   0.02667  -0.0485   0.0152   1.0000
  10.000   1.2169   0.03751   0.02877  -0.0460   0.0146   1.0000
  10.250   1.2200   0.03955   0.03100  -0.0436   0.0139   1.0000
  10.500   1.2230   0.04169   0.03332  -0.0416   0.0133   1.0000
  10.750   1.2254   0.04388   0.03573  -0.0399   0.0123   1.0000
  11.000   1.2256   0.04642   0.03843  -0.0383   0.0117   1.0000
  11.250   1.2224   0.04959   0.04177  -0.0368   0.0110   1.0000
  11.500   1.2219   0.05269   0.04506  -0.0356   0.0107   1.0000
  11.750   1.2223   0.05566   0.04830  -0.0348   0.0104   1.0000
  12.000   1.2204   0.05908   0.05198  -0.0341   0.0101   1.0000
  12.250   1.2164   0.06286   0.05602  -0.0339   0.0101   1.0000
  12.500   1.2099   0.06706   0.06049  -0.0341   0.0100   1.0000
  12.750   1.2014   0.07170   0.06538  -0.0349   0.0100   1.0000
  13.000   1.1909   0.07682   0.07075  -0.0363   0.0099   1.0000
  13.250   1.1788   0.08241   0.07659  -0.0384   0.0099   1.0000
  13.500   1.1651   0.08862   0.08304  -0.0412   0.0100   1.0000
  13.750   1.1502   0.09543   0.09006  -0.0448   0.0100   1.0000
  14.000   1.1353   0.10272   0.09755  -0.0489   0.0101   1.0000
  14.250   1.1194   0.11074   0.10575  -0.0538   0.0101   1.0000
  14.500   1.1032   0.11939   0.11457  -0.0592   0.0102   1.0000
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