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USNPS4 (smoothed) (usnps4-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: USNPS4 (smoothed) (usnps4-il)
Reynolds number: 100,000
Max Cl/Cd: 55.54 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-usnps4-il-100000.txt
Download as CSV file: xf-usnps4-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3575   0.11538   0.11095  -0.0237   1.0000   0.0656
  -7.750  -0.3774   0.11462   0.11029  -0.0221   1.0000   0.0659
  -7.500  -0.3958   0.11350   0.10926  -0.0221   1.0000   0.0662
  -7.250  -0.4075   0.11169   0.10749  -0.0248   1.0000   0.0664
  -7.000  -0.4144   0.10943   0.10522  -0.0281   1.0000   0.0666
  -6.750  -0.4114   0.10397   0.09988  -0.0229   1.0000   0.0675
  -6.500  -0.4078   0.10066   0.09663  -0.0181   1.0000   0.0686
  -6.250  -0.4079   0.09800   0.09400  -0.0162   1.0000   0.0699
  -6.000  -0.4087   0.09539   0.09142  -0.0156   1.0000   0.0712
  -5.750  -0.4086   0.09266   0.08873  -0.0159   1.0000   0.0729
  -5.500  -0.4064   0.08976   0.08584  -0.0172   1.0000   0.0750
  -5.250  -0.3980   0.08665   0.08266  -0.0219   1.0000   0.0783
  -5.000  -0.3710   0.08173   0.07746  -0.0327   0.9976   0.0810
  -4.750  -0.3499   0.07731   0.07318  -0.0325   0.9922   0.0836
  -4.500  -0.2881   0.07420   0.06942  -0.0479   0.9822   0.0954
  -4.250  -0.2705   0.06825   0.06375  -0.0479   0.9771   0.0979
  -4.000  -0.2400   0.06491   0.06038  -0.0510   0.9694   0.1038
  -3.750  -0.1928   0.06045   0.05563  -0.0592   0.9631   0.1143
  -3.500  -0.1534   0.05748   0.05229  -0.0646   0.9536   0.1283
  -3.250  -0.1225   0.05429   0.04916  -0.0669   0.9465   0.1376
  -3.000  -0.0813   0.05120   0.04582  -0.0720   0.9392   0.1623
  -2.750  -0.0496   0.04861   0.04321  -0.0742   0.9307   0.1831
  -2.500  -0.0076   0.04611   0.04056  -0.0786   0.9246   0.2278
  -1.750   0.1490   0.03787   0.03012  -0.0894   0.9017   0.1263
  -1.500   0.2006   0.03433   0.02619  -0.0929   0.8970   0.1037
  -1.250   0.2399   0.03273   0.02425  -0.0943   0.8878   0.1026
  -1.000   0.2894   0.03093   0.02211  -0.0973   0.8820   0.1021
  -0.750   0.3258   0.02977   0.02078  -0.0983   0.8717   0.1057
  -0.500   0.3759   0.02813   0.01900  -0.1014   0.8666   0.1129
  -0.250   0.4098   0.02708   0.01800  -0.1020   0.8554   0.1240
   0.000   0.4596   0.02540   0.01641  -0.1051   0.8511   0.1421
   0.250   0.4925   0.02433   0.01546  -0.1053   0.8395   0.1686
   0.500   0.5406   0.02094   0.01413  -0.1072   0.8364   1.0000
   0.750   0.5757   0.02042   0.01332  -0.1076   0.8243   1.0000
   1.000   0.6185   0.01970   0.01239  -0.1096   0.8142   1.0000
   1.250   0.6702   0.01876   0.01126  -0.1132   0.8059   1.0000
   1.750   0.7500   0.01765   0.00985  -0.1163   0.7761   1.0000
   2.000   0.7916   0.01717   0.00921  -0.1182   0.7589   1.0000
   2.250   0.8227   0.01702   0.00893  -0.1183   0.7367   1.0000
   2.500   0.8577   0.01687   0.00860  -0.1191   0.7143   1.0000
   2.750   0.8875   0.01691   0.00847  -0.1191   0.6899   1.0000
   3.000   0.9179   0.01701   0.00836  -0.1191   0.6654   1.0000
   3.250   0.9426   0.01727   0.00845  -0.1182   0.6398   1.0000
   3.500   0.9698   0.01755   0.00851  -0.1178   0.6159   1.0000
   3.750   0.9924   0.01793   0.00874  -0.1166   0.5912   1.0000
   4.000   1.0180   0.01833   0.00890  -0.1160   0.5694   1.0000
   4.250   1.0394   0.01878   0.00926  -0.1147   0.5470   1.0000
   4.500   1.0625   0.01925   0.00957  -0.1137   0.5266   1.0000
   4.750   1.0861   0.01976   0.00991  -0.1129   0.5080   1.0000
   5.000   1.1099   0.02030   0.01028  -0.1122   0.4906   1.0000
   5.250   1.1326   0.02085   0.01074  -0.1113   0.4740   1.0000
   5.500   1.1559   0.02142   0.01120  -0.1105   0.4585   1.0000
   5.750   1.1783   0.02200   0.01170  -0.1096   0.4438   1.0000
   6.000   1.2001   0.02259   0.01228  -0.1086   0.4299   1.0000
   6.250   1.2222   0.02321   0.01288  -0.1077   0.4170   1.0000
   6.500   1.2452   0.02387   0.01350  -0.1070   0.4053   1.0000
   6.750   1.2707   0.02454   0.01405  -0.1068   0.3945   1.0000
   7.000   1.2914   0.02518   0.01475  -0.1057   0.3835   1.0000
   7.250   1.3133   0.02591   0.01551  -0.1048   0.3736   1.0000
   7.500   1.3406   0.02664   0.01612  -0.1051   0.3648   1.0000
   7.750   1.3584   0.02739   0.01705  -0.1035   0.3556   1.0000
   8.000   1.3853   0.02818   0.01773  -0.1037   0.3476   1.0000
   8.250   1.4024   0.02894   0.01868  -0.1020   0.3392   1.0000
   8.500   1.4304   0.02980   0.01944  -0.1024   0.3322   1.0000
   8.750   1.4460   0.03069   0.02058  -0.1005   0.3250   1.0000
   9.000   1.4742   0.03153   0.02134  -0.1010   0.3187   1.0000
   9.250   1.4888   0.03254   0.02259  -0.0990   0.3121   1.0000
   9.500   1.5101   0.03339   0.02353  -0.0982   0.3058   1.0000
   9.750   1.5346   0.03447   0.02464  -0.0982   0.3004   1.0000
  10.000   1.5470   0.03561   0.02606  -0.0959   0.2950   1.0000
  10.250   1.5695   0.03660   0.02711  -0.0954   0.2899   1.0000
  10.500   1.5916   0.03783   0.02844  -0.0950   0.2851   1.0000
  10.750   1.5992   0.03912   0.03004  -0.0920   0.2801   1.0000
  11.000   1.6183   0.04020   0.03124  -0.0910   0.2755   1.0000
  11.250   1.6485   0.04151   0.03253  -0.0921   0.2714   1.0000
  11.500   1.6451   0.04325   0.03471  -0.0875   0.2678   1.0000
  11.750   1.6517   0.04479   0.03651  -0.0847   0.2637   1.0000
  12.000   1.6712   0.04592   0.03774  -0.0839   0.2595   1.0000
  12.250   1.6936   0.04746   0.03936  -0.0838   0.2558   1.0000
  12.500   1.6777   0.04973   0.04205  -0.0778   0.2531   1.0000
  12.750   1.6655   0.05192   0.04453  -0.0726   0.2502   1.0000
  13.000   1.6669   0.05365   0.04647  -0.0694   0.2469   1.0000
  13.250   1.7146   0.05397   0.04670  -0.0728   0.2411   1.0000
  13.500   1.6778   0.05688   0.04998  -0.0645   0.2395   1.0000
  13.750   1.6375   0.06065   0.05408  -0.0573   0.2380   1.0000
  14.000   1.5850   0.06604   0.05977  -0.0506   0.2371   1.0000
  14.250   1.6090   0.06566   0.05944  -0.0500   0.2307   1.0000
  14.500   1.5617   0.07176   0.06579  -0.0457   0.2300   1.0000
  14.750   1.5208   0.07818   0.07240  -0.0432   0.2286   1.0000
  15.000   1.4775   0.08600   0.08036  -0.0423   0.2272   1.0000
  15.250   1.6946   0.06083   0.05441  -0.0459   0.1972   1.0000
  15.500   1.6560   0.06561   0.05956  -0.0418   0.1957   1.0000
  15.750   1.6115   0.07182   0.06609  -0.0389   0.1947   1.0000
  16.000   1.5474   0.08161   0.07619  -0.0378   0.1956   1.0000
  16.250   1.6278   0.07274   0.06712  -0.0369   0.1822   1.0000
  16.500   1.5777   0.08089   0.07558  -0.0362   0.1818   1.0000
  16.750   1.5080   0.09333   0.08827  -0.0381   0.1831   1.0000
  17.000   1.5823   0.08353   0.07837  -0.0354   0.1689   1.0000
  17.250   1.5275   0.09416   0.08926  -0.0376   0.1691   1.0000
  17.500   1.0348   0.21297   0.20727  -0.1058   0.2212   1.0000
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