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USNPS4 (smoothed) (usnps4-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: USNPS4 (smoothed) (usnps4-il)
Reynolds number: 200,000
Max Cl/Cd: 67.23 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usnps4-il-200000-n5.txt
Download as CSV file: xf-usnps4-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USNPS4 (smoothed)                               
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.2176   0.08890   0.08546  -0.0598   0.9682   0.0281
  -7.250  -0.2051   0.08473   0.08128  -0.0652   0.9638   0.0295
  -7.000  -0.1958   0.07957   0.07611  -0.0727   0.9546   0.0306
  -6.750  -0.1720   0.07316   0.06961  -0.0831   0.9506   0.0309
  -6.500  -0.1614   0.06876   0.06514  -0.0861   0.9420   0.0310
  -6.000  -0.1305   0.05461   0.05067  -0.0942   0.9307   0.0214
  -5.500  -0.0778   0.04800   0.04384  -0.1003   0.9241   0.0224
  -5.250  -0.0598   0.04553   0.04125  -0.1005   0.9164   0.0235
  -5.000  -0.0303   0.04093   0.03635  -0.1035   0.9123   0.0241
  -4.750   0.0029   0.03603   0.03107  -0.1064   0.9099   0.0240
  -4.500   0.0238   0.03232   0.02700  -0.1060   0.9018   0.0241
  -4.250   0.0559   0.02747   0.02152  -0.1073   0.8982   0.0252
  -4.000   0.0906   0.02448   0.01803  -0.1089   0.8957   0.0266
  -3.750   0.1145   0.02311   0.01647  -0.1082   0.8875   0.0271
  -3.500   0.1480   0.02137   0.01442  -0.1093   0.8831   0.0280
  -3.250   0.1864   0.01962   0.01232  -0.1112   0.8801   0.0292
  -3.000   0.2111   0.01854   0.01089  -0.1102   0.8703   0.0312
  -2.750   0.2500   0.01759   0.00990  -0.1125   0.8658   0.0327
  -2.500   0.2782   0.01688   0.00909  -0.1124   0.8558   0.0340
  -2.250   0.3208   0.01592   0.00798  -0.1152   0.8503   0.0361
  -2.000   0.3516   0.01531   0.00732  -0.1157   0.8392   0.0386
  -1.750   0.3870   0.01481   0.00680  -0.1172   0.8286   0.0417
  -1.500   0.4245   0.01423   0.00611  -0.1191   0.8172   0.0449
  -1.250   0.4604   0.01376   0.00564  -0.1207   0.8034   0.0495
  -1.000   0.4943   0.01344   0.00522  -0.1218   0.7873   0.0548
  -0.750   0.5262   0.01314   0.00488  -0.1227   0.7693   0.0617
  -0.500   0.5571   0.01293   0.00457  -0.1232   0.7495   0.0696
  -0.250   0.5870   0.01282   0.00434  -0.1235   0.7287   0.0806
   0.000   0.6147   0.01272   0.00417  -0.1234   0.7067   0.0977
   0.250   0.6411   0.01252   0.00407  -0.1232   0.6838   0.1651
   0.500   0.6691   0.01071   0.00426  -0.1229   0.6614   1.0000
   0.750   0.6928   0.01091   0.00422  -0.1219   0.6378   1.0000
   1.000   0.7160   0.01114   0.00422  -0.1208   0.6143   1.0000
   1.250   0.7387   0.01137   0.00425  -0.1197   0.5912   1.0000
   1.500   0.7610   0.01163   0.00431  -0.1185   0.5687   1.0000
   1.750   0.7833   0.01189   0.00439  -0.1174   0.5465   1.0000
   2.000   0.8053   0.01217   0.00449  -0.1162   0.5253   1.0000
   2.250   0.8272   0.01246   0.00461  -0.1150   0.5052   1.0000
   2.500   0.8493   0.01274   0.00475  -0.1139   0.4858   1.0000
   2.750   0.8713   0.01304   0.00490  -0.1127   0.4675   1.0000
   3.000   0.8931   0.01334   0.00507  -0.1116   0.4499   1.0000
   3.250   0.9150   0.01364   0.00526  -0.1105   0.4336   1.0000
   3.500   0.9369   0.01395   0.00546  -0.1094   0.4185   1.0000
   3.750   0.9587   0.01426   0.00567  -0.1083   0.4039   1.0000
   4.000   0.9802   0.01458   0.00590  -0.1072   0.3903   1.0000
   4.250   1.0016   0.01491   0.00614  -0.1061   0.3778   1.0000
   4.500   1.0231   0.01524   0.00640  -0.1049   0.3658   1.0000
   4.750   1.0447   0.01556   0.00666  -0.1039   0.3544   1.0000
   5.000   1.0657   0.01589   0.00694  -0.1027   0.3437   1.0000
   5.250   1.0856   0.01625   0.00723  -0.1013   0.3337   1.0000
   5.500   1.1065   0.01657   0.00754  -0.1001   0.3245   1.0000
   5.750   1.1260   0.01694   0.00787  -0.0987   0.3160   1.0000
   6.000   1.1464   0.01729   0.00820  -0.0975   0.3071   1.0000
   6.250   1.1661   0.01769   0.00858  -0.0961   0.2991   1.0000
   6.500   1.1861   0.01807   0.00895  -0.0949   0.2912   1.0000
   6.750   1.2057   0.01848   0.00934  -0.0936   0.2846   1.0000
   7.000   1.2259   0.01887   0.00975  -0.0924   0.2777   1.0000
   7.250   1.2442   0.01935   0.01020  -0.0909   0.2715   1.0000
   7.500   1.2646   0.01974   0.01064  -0.0898   0.2648   1.0000
   7.750   1.2828   0.02022   0.01111  -0.0884   0.2587   1.0000
   8.000   1.3020   0.02068   0.01160  -0.0871   0.2532   1.0000
   8.250   1.3211   0.02114   0.01211  -0.0859   0.2477   1.0000
   8.500   1.3384   0.02169   0.01266  -0.0844   0.2430   1.0000
   8.750   1.3572   0.02218   0.01321  -0.0831   0.2382   1.0000
   9.000   1.3754   0.02270   0.01379  -0.0818   0.2331   1.0000
   9.250   1.3917   0.02330   0.01441  -0.0802   0.2285   1.0000
   9.500   1.4092   0.02387   0.01504  -0.0789   0.2242   1.0000
   9.750   1.4269   0.02444   0.01569  -0.0776   0.2199   1.0000
  10.000   1.4431   0.02508   0.01639  -0.0761   0.2160   1.0000
  10.250   1.4579   0.02581   0.01713  -0.0745   0.2127   1.0000
  10.500   1.4751   0.02643   0.01787  -0.0732   0.2091   1.0000
  10.750   1.4912   0.02710   0.01864  -0.0718   0.2052   1.0000
  11.000   1.5057   0.02785   0.01946  -0.0702   0.2015   1.0000
  11.250   1.5188   0.02871   0.02034  -0.0686   0.1984   1.0000
  11.500   1.5343   0.02946   0.02122  -0.0672   0.1954   1.0000
  11.750   1.5493   0.03025   0.02214  -0.0659   0.1923   1.0000
  12.000   1.5630   0.03111   0.02312  -0.0644   0.1893   1.0000
  12.250   1.5752   0.03206   0.02414  -0.0628   0.1864   1.0000
  12.500   1.5860   0.03310   0.02523  -0.0611   0.1829   1.0000
  12.750   1.5972   0.03408   0.02639  -0.0596   0.1779   1.0000
  13.000   1.6050   0.03528   0.02766  -0.0578   0.1727   1.0000
  13.250   1.6126   0.03655   0.02903  -0.0561   0.1676   1.0000
  13.500   1.6211   0.03781   0.03044  -0.0546   0.1620   1.0000
  13.750   1.6256   0.03940   0.03207  -0.0530   0.1573   1.0000
  14.000   1.6337   0.04081   0.03365  -0.0517   0.1520   1.0000
  14.250   1.6385   0.04253   0.03547  -0.0503   0.1464   1.0000
  14.500   1.6421   0.04442   0.03747  -0.0491   0.1409   1.0000
  14.750   1.6460   0.04639   0.03956  -0.0480   0.1344   1.0000
  15.000   1.6471   0.04870   0.04197  -0.0469   0.1282   1.0000
  15.250   1.6480   0.05114   0.04452  -0.0461   0.1210   1.0000
  15.500   1.6474   0.05384   0.04733  -0.0454   0.1141   1.0000
  15.750   1.6424   0.05714   0.05070  -0.0448   0.1063   1.0000
  16.000   1.6368   0.06064   0.05429  -0.0445   0.0966   1.0000
  16.250   1.6260   0.06493   0.05864  -0.0445   0.0859   1.0000
  16.500   1.6100   0.07009   0.06384  -0.0448   0.0746   1.0000
  16.750   1.5895   0.07604   0.06983  -0.0456   0.0642   1.0000
  17.000   1.5672   0.08251   0.07637  -0.0469   0.0559   1.0000
  17.250   1.5441   0.08935   0.08329  -0.0485   0.0494   1.0000
  17.500   1.5209   0.09641   0.09047  -0.0506   0.0450   1.0000
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