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USNPS4 (smoothed) (usnps4-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: USNPS4 (smoothed) (usnps4-il)
Reynolds number: 50,000
Max Cl/Cd: 37.09 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usnps4-il-50000-n5.txt
Download as CSV file: xf-usnps4-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -6.500  -0.3840   0.10289   0.09703  -0.0189   1.0000   0.1024
  -6.250  -0.3879   0.10034   0.09454  -0.0191   1.0000   0.1049
  -6.000  -0.3927   0.09787   0.09210  -0.0219   1.0000   0.1088
  -5.750  -0.3838   0.09420   0.08835  -0.0303   0.9972   0.1113
  -5.500  -0.3674   0.08967   0.08389  -0.0285   0.9936   0.1138
  -5.250  -0.3452   0.08576   0.07995  -0.0314   0.9878   0.1186
  -5.000  -0.3172   0.08114   0.07517  -0.0403   0.9800   0.1289
  -4.500  -0.2703   0.07384   0.06777  -0.0460   0.9672   0.1504
  -4.250  -0.2062   0.06514   0.05809  -0.0601   0.9606   0.0795
  -4.000  -0.1692   0.05966   0.05210  -0.0647   0.9541   0.0670
  -3.750  -0.1375   0.05612   0.04842  -0.0676   0.9486   0.0651
  -3.500  -0.1034   0.05285   0.04473  -0.0707   0.9411   0.0655
  -3.250  -0.0636   0.04972   0.04107  -0.0743   0.9355   0.0660
  -3.000  -0.0308   0.04700   0.03801  -0.0763   0.9277   0.0656
  -2.750   0.0107   0.04431   0.03484  -0.0795   0.9225   0.0654
  -2.500   0.0444   0.04231   0.03232  -0.0809   0.9136   0.0671
  -2.250   0.0814   0.04041   0.03030  -0.0835   0.9071   0.0703
  -2.000   0.1162   0.03880   0.02834  -0.0848   0.8983   0.0719
  -1.750   0.1523   0.03735   0.02654  -0.0862   0.8900   0.0743
  -1.500   0.1916   0.03613   0.02487  -0.0878   0.8820   0.0793
  -1.250   0.2233   0.03493   0.02350  -0.0883   0.8718   0.0824
  -1.000   0.2647   0.03374   0.02218  -0.0904   0.8653   0.0896
  -0.750   0.2946   0.03304   0.02122  -0.0901   0.8535   0.0956
  -0.500   0.3269   0.03219   0.02035  -0.0906   0.8428   0.1047
  -0.250   0.3685   0.03111   0.01918  -0.0925   0.8355   0.1171
   0.000   0.3984   0.03046   0.01848  -0.0926   0.8229   0.1337
   0.250   0.4307   0.02969   0.01778  -0.0932   0.8111   0.1625
   0.500   0.4666   0.02641   0.01688  -0.0934   0.8042   1.0000
   0.750   0.4973   0.02625   0.01629  -0.0932   0.7908   1.0000
   1.000   0.5278   0.02609   0.01583  -0.0931   0.7770   1.0000
   1.250   0.5591   0.02590   0.01539  -0.0932   0.7632   1.0000
   1.500   0.5914   0.02568   0.01496  -0.0934   0.7491   1.0000
   1.750   0.6243   0.02546   0.01455  -0.0938   0.7346   1.0000
   2.000   0.6575   0.02525   0.01416  -0.0942   0.7193   1.0000
   2.250   0.6908   0.02507   0.01381  -0.0946   0.7031   1.0000
   2.500   0.7240   0.02493   0.01351  -0.0951   0.6860   1.0000
   2.750   0.7568   0.02482   0.01324  -0.0955   0.6681   1.0000
   3.000   0.7897   0.02475   0.01300  -0.0959   0.6498   1.0000
   3.250   0.8186   0.02484   0.01295  -0.0957   0.6300   1.0000
   3.500   0.8457   0.02503   0.01300  -0.0953   0.6098   1.0000
   3.750   0.8735   0.02523   0.01305  -0.0950   0.5900   1.0000
   4.000   0.9014   0.02548   0.01314  -0.0948   0.5709   1.0000
   4.250   0.9267   0.02583   0.01335  -0.0942   0.5519   1.0000
   4.500   0.9504   0.02625   0.01367  -0.0934   0.5332   1.0000
   4.750   0.9740   0.02671   0.01404  -0.0926   0.5153   1.0000
   5.000   0.9974   0.02720   0.01442  -0.0919   0.4984   1.0000
   5.250   1.0207   0.02772   0.01486  -0.0911   0.4825   1.0000
   5.500   1.0435   0.02827   0.01533  -0.0903   0.4672   1.0000
   5.750   1.0664   0.02885   0.01587  -0.0896   0.4528   1.0000
   6.000   1.0897   0.02944   0.01639  -0.0889   0.4395   1.0000
   6.250   1.1137   0.03003   0.01690  -0.0884   0.4268   1.0000
   6.500   1.1341   0.03073   0.01762  -0.0874   0.4141   1.0000
   6.750   1.1550   0.03145   0.01839  -0.0864   0.4024   1.0000
   7.000   1.1775   0.03215   0.01907  -0.0858   0.3918   1.0000
   7.250   1.1997   0.03286   0.01976  -0.0851   0.3815   1.0000
   7.500   1.2184   0.03370   0.02071  -0.0839   0.3713   1.0000
   7.750   1.2417   0.03444   0.02142  -0.0834   0.3626   1.0000
   8.000   1.2594   0.03533   0.02243  -0.0821   0.3534   1.0000
   8.250   1.2803   0.03618   0.02332  -0.0813   0.3453   1.0000
   8.500   1.2985   0.03711   0.02437  -0.0801   0.3372   1.0000
   8.750   1.3186   0.03804   0.02536  -0.0793   0.3300   1.0000
   9.000   1.3343   0.03908   0.02654  -0.0778   0.3226   1.0000
   9.250   1.3563   0.03998   0.02748  -0.0772   0.3162   1.0000
   9.500   1.3661   0.04124   0.02897  -0.0749   0.3094   1.0000
   9.750   1.3882   0.04216   0.02993  -0.0745   0.3037   1.0000
  10.000   1.3974   0.04353   0.03151  -0.0722   0.2980   1.0000
  10.250   1.4079   0.04484   0.03299  -0.0701   0.2922   1.0000
  10.500   1.4337   0.04568   0.03386  -0.0702   0.2872   1.0000
  10.750   1.4303   0.04761   0.03611  -0.0665   0.2822   1.0000
  11.000   1.4369   0.04925   0.03796  -0.0642   0.2774   1.0000
  11.250   1.4576   0.05031   0.03909  -0.0636   0.2731   1.0000
  11.500   1.4563   0.05239   0.04143  -0.0606   0.2689   1.0000
  11.750   1.4465   0.05494   0.04427  -0.0570   0.2646   1.0000
  12.000   1.4520   0.05676   0.04626  -0.0551   0.2605   1.0000
  12.250   1.4801   0.05747   0.04702  -0.0553   0.2568   1.0000
  12.500   1.4459   0.06184   0.05175  -0.0504   0.2536   1.0000
  12.750   1.4077   0.06721   0.05742  -0.0467   0.2503   1.0000
  13.000   1.3770   0.07266   0.06309  -0.0447   0.2469   1.0000
  13.250   1.3869   0.07449   0.06504  -0.0439   0.2436   1.0000
  13.500   1.1365   0.11537   0.10593  -0.0557   0.2307   1.0000
  13.750   1.1544   0.11571   0.10642  -0.0547   0.2283   1.0000
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