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USA 25 AIRFOIL (usa25-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: USA 25 AIRFOIL (usa25-il)
Reynolds number: 500,000
Max Cl/Cd: 101.97 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-usa25-il-500000.txt
Download as CSV file: xf-usa25-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA 25 AIRFOIL                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3463   0.11780   0.11553  -0.0237   1.0000   0.0216
 -10.000  -0.3502   0.11517   0.11293  -0.0246   1.0000   0.0217
  -9.750  -0.3529   0.11241   0.11020  -0.0250   1.0000   0.0217
  -9.500  -0.3552   0.10968   0.10749  -0.0252   1.0000   0.0218
  -9.250  -0.3572   0.10548   0.10332  -0.0244   1.0000   0.0220
  -9.000  -0.3520   0.10289   0.10074  -0.0227   1.0000   0.0223
  -8.750  -0.3496   0.10077   0.09863  -0.0215   1.0000   0.0226
  -8.500  -0.3503   0.09869   0.09658  -0.0204   1.0000   0.0228
  -8.250  -0.3486   0.09646   0.09437  -0.0202   0.9997   0.0232
  -8.000  -0.3321   0.09283   0.09074  -0.0245   0.9974   0.0240
  -7.750  -0.3154   0.08886   0.08677  -0.0299   0.9946   0.0252
  -7.500  -0.3044   0.08446   0.08237  -0.0376   0.9887   0.0268
  -7.250  -0.2737   0.07790   0.07574  -0.0519   0.9838   0.0274
  -7.000  -0.2640   0.07151   0.06932  -0.0565   0.9778   0.0278
  -6.750  -0.2416   0.06838   0.06617  -0.0590   0.9745   0.0284
  -6.500  -0.2130   0.06528   0.06304  -0.0630   0.9720   0.0291
  -6.250  -0.1890   0.06206   0.05978  -0.0667   0.9669   0.0302
  -6.000  -0.1637   0.05828   0.05594  -0.0711   0.9613   0.0320
  -5.750  -0.1289   0.05023   0.04766  -0.0810   0.9576   0.0352
  -5.500  -0.1112   0.04829   0.04569  -0.0810   0.9513   0.0359
  -5.250  -0.0853   0.04617   0.04353  -0.0827   0.9468   0.0368
  -5.000  -0.0532   0.04354   0.04082  -0.0859   0.9437   0.0387
  -4.750  -0.0299   0.03748   0.03446  -0.0882   0.9341   0.0439
  -4.500   0.0001   0.03618   0.03314  -0.0900   0.9289   0.0451
  -4.250   0.0217   0.03499   0.03192  -0.0896   0.9172   0.0467
  -3.500   0.0881   0.01588   0.01104  -0.0890   0.8774   0.0407
  -3.250   0.1218   0.01335   0.00792  -0.0901   0.8562   0.0391
  -3.000   0.1543   0.01219   0.00637  -0.0907   0.8265   0.0386
  -2.750   0.1811   0.01158   0.00546  -0.0902   0.7902   0.0386
  -2.500   0.2029   0.01126   0.00483  -0.0885   0.7387   0.0387
  -2.250   0.2169   0.01131   0.00439  -0.0852   0.6448   0.0388
  -2.000   0.2317   0.01142   0.00407  -0.0823   0.5666   0.0390
  -1.750   0.2522   0.01136   0.00377  -0.0807   0.5282   0.0393
  -1.500   0.2747   0.01125   0.00350  -0.0795   0.5076   0.0399
  -1.250   0.2983   0.01112   0.00327  -0.0784   0.4946   0.0408
  -1.000   0.3220   0.01100   0.00306  -0.0775   0.4853   0.0413
  -0.750   0.3462   0.01090   0.00288  -0.0765   0.4775   0.0419
  -0.500   0.3704   0.01083   0.00274  -0.0757   0.4712   0.0427
  -0.250   0.3952   0.01075   0.00262  -0.0749   0.4654   0.0441
   0.000   0.4195   0.01072   0.00255  -0.0740   0.4604   0.0474
   0.250   0.4439   0.01068   0.00254  -0.0732   0.4562   0.0557
   0.500   0.4689   0.01062   0.00256  -0.0725   0.4523   0.0819
   0.750   0.4941   0.01064   0.00260  -0.0719   0.4484   0.0970
   1.000   0.5192   0.01072   0.00268  -0.0713   0.4447   0.1125
   1.250   0.5447   0.01081   0.00276  -0.0708   0.4409   0.1221
   1.500   0.5704   0.01084   0.00282  -0.0703   0.4372   0.1325
   1.750   0.5958   0.01088   0.00289  -0.0698   0.4333   0.1443
   2.000   0.6210   0.01096   0.00297  -0.0692   0.4295   0.1570
   2.250   0.6464   0.01106   0.00307  -0.0687   0.4254   0.1701
   2.500   0.6717   0.01107   0.00314  -0.0682   0.4220   0.1852
   2.750   0.6970   0.01111   0.00324  -0.0676   0.4189   0.2038
   3.000   0.7221   0.01116   0.00333  -0.0671   0.4153   0.2255
   3.250   0.7472   0.01126   0.00346  -0.0666   0.4117   0.2496
   3.500   0.7717   0.01123   0.00357  -0.0659   0.4086   0.2912
   3.750   0.8133   0.00999   0.00390  -0.0690   0.4040   0.9660
   4.000   0.8781   0.01027   0.00415  -0.0772   0.3991   0.9878
   4.250   0.9433   0.01058   0.00440  -0.0856   0.3944   0.9985
   4.500   0.9751   0.01066   0.00451  -0.0866   0.3911   1.0000
   4.750   0.9952   0.01072   0.00459  -0.0850   0.3870   1.0000
   5.000   1.0144   0.01082   0.00466  -0.0832   0.3811   1.0000
   5.250   1.0334   0.01083   0.00471  -0.0814   0.3744   1.0000
   5.500   1.0523   0.01088   0.00475  -0.0795   0.3676   1.0000
   5.750   1.0718   0.01095   0.00485  -0.0778   0.3613   1.0000
   6.000   1.0912   0.01099   0.00491  -0.0761   0.3532   1.0000
   6.250   1.1108   0.01107   0.00500  -0.0744   0.3445   1.0000
   6.500   1.1298   0.01116   0.00507  -0.0726   0.3335   1.0000
   6.750   1.1492   0.01127   0.00516  -0.0710   0.3179   1.0000
   7.000   1.1665   0.01149   0.00529  -0.0689   0.2897   1.0000
   7.250   1.1804   0.01199   0.00556  -0.0664   0.2493   1.0000
   7.500   1.1912   0.01279   0.00607  -0.0634   0.2021   1.0000
   7.750   1.2034   0.01354   0.00660  -0.0607   0.1685   1.0000
   8.000   1.2169   0.01418   0.00709  -0.0582   0.1422   1.0000
   8.250   1.2170   0.01559   0.00802  -0.0536   0.0722   1.0000
   8.500   1.2205   0.01656   0.00882  -0.0493   0.0410   1.0000
   8.750   1.2265   0.01740   0.00955  -0.0454   0.0211   1.0000
   9.000   1.2388   0.01795   0.01015  -0.0427   0.0191   1.0000
   9.250   1.2504   0.01856   0.01083  -0.0400   0.0179   1.0000
   9.500   1.2615   0.01921   0.01156  -0.0372   0.0170   1.0000
   9.750   1.2711   0.01996   0.01242  -0.0343   0.0162   1.0000
  10.000   1.2812   0.02070   0.01325  -0.0316   0.0157   1.0000
  10.250   1.2899   0.02153   0.01417  -0.0289   0.0152   1.0000
  10.500   1.2970   0.02247   0.01520  -0.0260   0.0147   1.0000
  10.750   1.3024   0.02355   0.01636  -0.0231   0.0142   1.0000
  11.000   1.3067   0.02472   0.01762  -0.0202   0.0140   1.0000
  11.250   1.3077   0.02617   0.01916  -0.0173   0.0136   1.0000
  11.500   1.3078   0.02777   0.02087  -0.0146   0.0133   1.0000
  11.750   1.3056   0.02968   0.02287  -0.0120   0.0132   1.0000
  12.000   1.3042   0.03168   0.02497  -0.0100   0.0131   1.0000
  12.250   1.2964   0.03443   0.02781  -0.0080   0.0128   1.0000
  12.500   1.2889   0.03741   0.03090  -0.0066   0.0126   1.0000
  12.750   1.2818   0.04060   0.03419  -0.0057   0.0125   1.0000
  13.000   1.2782   0.04362   0.03730  -0.0052   0.0125   1.0000
  13.250   1.2681   0.04736   0.04112  -0.0046   0.0123   1.0000
  13.500   1.2634   0.05049   0.04430  -0.0039   0.0122   1.0000
  13.750   1.2681   0.05310   0.04705  -0.0045   0.0120   1.0000
  14.000   1.2689   0.05591   0.04994  -0.0044   0.0119   1.0000
  14.250   1.2700   0.05865   0.05276  -0.0043   0.0118   1.0000
  14.500   1.2711   0.06145   0.05565  -0.0043   0.0117   1.0000
  14.750   1.2726   0.06423   0.05852  -0.0044   0.0115   1.0000
  15.000   1.2736   0.06715   0.06153  -0.0046   0.0113   1.0000
  15.250   1.2749   0.07000   0.06447  -0.0048   0.0111   1.0000
  15.500   1.2767   0.07269   0.06723  -0.0046   0.0110   1.0000
  15.750   1.2783   0.07547   0.07011  -0.0047   0.0109   1.0000
  16.000   1.2797   0.07832   0.07305  -0.0048   0.0108   1.0000
  16.250   1.2821   0.08094   0.07577  -0.0043   0.0109   1.0000
  16.500   1.2821   0.08416   0.07910  -0.0049   0.0109   1.0000
  16.750   1.2817   0.08738   0.08244  -0.0051   0.0109   1.0000
  17.000   1.2791   0.09111   0.08630  -0.0061   0.0107   1.0000
  17.250   1.2763   0.09488   0.09021  -0.0068   0.0108   1.0000
  17.500   1.2719   0.09903   0.09450  -0.0080   0.0108   1.0000
  17.750   1.2660   0.10343   0.09905  -0.0092   0.0110   1.0000
  18.000   1.2582   0.10831   0.10408  -0.0110   0.0111   1.0000
  18.250   1.2520   0.11286   0.10878  -0.0122   0.0115   1.0000
  18.500   1.2423   0.11826   0.11432  -0.0145   0.0116   1.0000
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