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USNPS4 (smoothed) (usnps4-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: USNPS4 (smoothed) (usnps4-il)
Reynolds number: 200,000
Max Cl/Cd: 74.32 at α=2.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-usnps4-il-200000.txt
Download as CSV file: xf-usnps4-il-200000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.2506   0.10783   0.10487  -0.0312   0.9920   0.0370
  -8.250  -0.2541   0.10388   0.10094  -0.0366   0.9881   0.0373
  -8.000  -0.2550   0.09966   0.09672  -0.0418   0.9843   0.0375
  -7.750  -0.2314   0.09415   0.09122  -0.0400   0.9816   0.0382
  -7.500  -0.2144   0.09035   0.08741  -0.0410   0.9781   0.0395
  -7.250  -0.2029   0.08615   0.08321  -0.0442   0.9753   0.0409
  -7.000  -0.2014   0.08249   0.07957  -0.0460   0.9685   0.0420
  -6.750  -0.3231   0.09063   0.08756  -0.0423   0.9794   0.0382
  -6.500  -0.3029   0.08729   0.08422  -0.0434   0.9762   0.0393
  -6.250  -0.2838   0.08330   0.08021  -0.0478   0.9697   0.0409
  -6.000  -0.2555   0.07819   0.07503  -0.0560   0.9644   0.0430
  -5.750  -0.2121   0.07113   0.06748  -0.0731   0.9540   0.0454
  -5.500  -0.1947   0.06605   0.06255  -0.0738   0.9518   0.0462
  -5.250  -0.1765   0.06306   0.05957  -0.0745   0.9457   0.0473
  -5.000  -0.1483   0.05956   0.05600  -0.0778   0.9407   0.0493
  -4.750  -0.0881   0.05588   0.05149  -0.0881   0.9373   0.0550
  -4.500  -0.0786   0.05027   0.04612  -0.0880   0.9294   0.0564
  -4.250  -0.0475   0.04751   0.04338  -0.0906   0.9260   0.0591
  -4.000   0.0041   0.04425   0.03938  -0.0963   0.9236   0.0673
  -3.750   0.0216   0.04078   0.03604  -0.0962   0.9150   0.0690
  -3.500   0.0586   0.03813   0.03333  -0.0992   0.9119   0.0728
  -3.250   0.1043   0.03516   0.02985  -0.1031   0.9098   0.0826
  -3.000   0.1275   0.03328   0.02801  -0.1030   0.9011   0.0872
  -2.750   0.1687   0.03090   0.02535  -0.1060   0.8979   0.0997
  -2.500   0.2122   0.02876   0.02295  -0.1093   0.8959   0.1144
  -2.250   0.2529   0.02466   0.01794  -0.1083   0.8897   0.0640
  -2.000   0.2918   0.02264   0.01562  -0.1099   0.8852   0.0632
  -1.750   0.3358   0.02058   0.01329  -0.1122   0.8829   0.0618
  -1.500   0.3817   0.01908   0.01157  -0.1151   0.8810   0.0643
  -1.250   0.4110   0.01813   0.01049  -0.1147   0.8718   0.0676
  -1.000   0.4553   0.01672   0.00913  -0.1177   0.8681   0.0729
  -0.750   0.4916   0.01605   0.00840  -0.1189   0.8601   0.0803
  -0.500   0.5309   0.01490   0.00734  -0.1209   0.8527   0.0914
  -0.250   0.5641   0.01416   0.00665  -0.1217   0.8413   0.1047
   0.000   0.6013   0.01346   0.00598  -0.1233   0.8298   0.1309
   0.250   0.6421   0.01093   0.00568  -0.1254   0.8190   1.0000
   0.500   0.6736   0.01083   0.00536  -0.1258   0.8015   1.0000
   0.750   0.7043   0.01078   0.00512  -0.1261   0.7823   1.0000
   1.000   0.7350   0.01078   0.00492  -0.1264   0.7618   1.0000
   1.250   0.7634   0.01085   0.00480  -0.1262   0.7399   1.0000
   1.500   0.7895   0.01098   0.00474  -0.1256   0.7160   1.0000
   1.750   0.8149   0.01115   0.00472  -0.1249   0.6918   1.0000
   2.000   0.8389   0.01137   0.00474  -0.1240   0.6666   1.0000
   2.250   0.8618   0.01161   0.00480  -0.1228   0.6411   1.0000
   2.500   0.8844   0.01190   0.00489  -0.1216   0.6163   1.0000
   2.750   0.9059   0.01220   0.00502  -0.1203   0.5909   1.0000
   3.000   0.9273   0.01253   0.00517  -0.1189   0.5669   1.0000
   3.250   0.9483   0.01286   0.00535  -0.1175   0.5433   1.0000
   3.500   0.9692   0.01324   0.00555  -0.1161   0.5216   1.0000
   3.750   0.9900   0.01359   0.00577  -0.1147   0.5001   1.0000
   4.000   1.0108   0.01397   0.00601  -0.1134   0.4804   1.0000
   4.250   1.0317   0.01436   0.00628  -0.1121   0.4623   1.0000
   4.500   1.0525   0.01476   0.00656  -0.1108   0.4453   1.0000
   4.750   1.0734   0.01516   0.00685  -0.1096   0.4293   1.0000
   5.000   1.0943   0.01556   0.00716  -0.1083   0.4144   1.0000
   5.250   1.1154   0.01596   0.00751  -0.1072   0.4006   1.0000
   5.500   1.1365   0.01637   0.00785  -0.1060   0.3878   1.0000
   5.750   1.1574   0.01681   0.00821  -0.1049   0.3760   1.0000
   6.000   1.1783   0.01728   0.00857  -0.1037   0.3648   1.0000
   6.250   1.1988   0.01766   0.00898  -0.1025   0.3537   1.0000
   6.500   1.2200   0.01813   0.00939  -0.1015   0.3442   1.0000
   6.750   1.2408   0.01859   0.00980  -0.1004   0.3351   1.0000
   7.000   1.2611   0.01902   0.01027  -0.0991   0.3261   1.0000
   7.250   1.2822   0.01957   0.01070  -0.0982   0.3180   1.0000
   7.500   1.3006   0.01996   0.01118  -0.0966   0.3098   1.0000
   7.750   1.3226   0.02053   0.01166  -0.0958   0.3027   1.0000
   8.000   1.3413   0.02098   0.01221  -0.0943   0.2956   1.0000
   8.250   1.3619   0.02151   0.01271  -0.0933   0.2892   1.0000
   8.500   1.3822   0.02206   0.01330  -0.0923   0.2828   1.0000
   8.750   1.4008   0.02255   0.01385  -0.0908   0.2765   1.0000
   9.000   1.4238   0.02321   0.01445  -0.0904   0.2708   1.0000
   9.250   1.4408   0.02372   0.01509  -0.0887   0.2653   1.0000
   9.500   1.4605   0.02429   0.01569  -0.0876   0.2602   1.0000
   9.750   1.4846   0.02501   0.01639  -0.0875   0.2554   1.0000
  10.000   1.5005   0.02558   0.01712  -0.0857   0.2506   1.0000
  10.250   1.5187   0.02617   0.01776  -0.0844   0.2458   1.0000
  10.500   1.5445   0.02696   0.01849  -0.0846   0.2412   1.0000
  10.750   1.5577   0.02760   0.01933  -0.0824   0.2373   1.0000
  11.000   1.5750   0.02827   0.02012  -0.0810   0.2332   1.0000
  11.250   1.5958   0.02896   0.02083  -0.0803   0.2295   1.0000
  11.500   1.6199   0.02984   0.02176  -0.0803   0.2257   1.0000
  11.750   1.6302   0.03060   0.02273  -0.0778   0.2221   1.0000
  12.000   1.6428   0.03130   0.02354  -0.0758   0.2180   1.0000
  12.250   1.6606   0.03197   0.02417  -0.0747   0.2134   1.0000
  12.500   1.6650   0.03284   0.02523  -0.0715   0.2090   1.0000
  12.750   1.6683   0.03362   0.02617  -0.0683   0.2042   1.0000
  13.000   1.6783   0.03434   0.02686  -0.0662   0.1992   1.0000
  13.250   1.6817   0.03541   0.02811  -0.0634   0.1948   1.0000
  13.500   1.6841   0.03646   0.02934  -0.0605   0.1903   1.0000
  13.750   1.6902   0.03745   0.03036  -0.0584   0.1859   1.0000
  14.000   1.6940   0.03872   0.03177  -0.0561   0.1814   1.0000
  14.250   1.6932   0.04017   0.03341  -0.0535   0.1767   1.0000
  14.500   1.6955   0.04155   0.03486  -0.0515   0.1721   1.0000
  14.750   1.6975   0.04318   0.03662  -0.0496   0.1678   1.0000
  15.000   1.6963   0.04507   0.03873  -0.0477   0.1631   1.0000
  15.250   1.6960   0.04699   0.04072  -0.0462   0.1583   1.0000
  15.500   1.6946   0.04924   0.04316  -0.0449   0.1534   1.0000
  15.750   1.6917   0.05179   0.04590  -0.0439   0.1476   1.0000
  16.000   1.6872   0.05465   0.04886  -0.0431   0.1417   1.0000
  16.250   1.6817   0.05794   0.05236  -0.0427   0.1337   1.0000
  16.500   1.6736   0.06176   0.05633  -0.0427   0.1241   1.0000
  16.750   1.6602   0.06648   0.06116  -0.0431   0.1113   1.0000
  17.000   1.6392   0.07242   0.06713  -0.0439   0.0963   1.0000
  17.250   1.6134   0.07927   0.07399  -0.0452   0.0809   1.0000
  17.500   1.5852   0.08674   0.08149  -0.0469   0.0702   1.0000
  17.750   1.5568   0.09449   0.08930  -0.0491   0.0632   1.0000
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