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USNPS4 (smoothed) (usnps4-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: USNPS4 (smoothed) (usnps4-il)
Reynolds number: 50,000
Max Cl/Cd: 32.73 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-usnps4-il-50000.txt
Download as CSV file: xf-usnps4-il-50000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3456   0.11605   0.10984  -0.0216   1.0000   0.1554
  -7.500  -0.3686   0.11568   0.10961  -0.0198   1.0000   0.1576
  -7.250  -0.3938   0.11540   0.10949  -0.0197   1.0000   0.1587
  -7.000  -0.3766   0.11005   0.10416  -0.0160   1.0000   0.1639
  -6.750  -0.3807   0.10778   0.10197  -0.0144   1.0000   0.1695
  -6.500  -0.3986   0.10659   0.10089  -0.0157   1.0000   0.1741
  -6.250  -0.4050   0.10365   0.09804  -0.0159   1.0000   0.1773
  -6.000  -0.3979   0.10043   0.09486  -0.0120   1.0000   0.1849
  -5.250  -0.4086   0.09292   0.08749  -0.0164   1.0000   0.2095
  -5.000  -0.4030   0.08966   0.08432  -0.0111   1.0000   0.2184
  -4.750  -0.4013   0.08677   0.08147  -0.0114   1.0000   0.2304
  -4.500  -0.3980   0.08405   0.07878  -0.0112   1.0000   0.2464
  -4.250  -0.3941   0.08148   0.07625  -0.0098   1.0000   0.2650
  -4.000   0.0557   0.05964   0.05358  -0.0278   1.0000   1.0000
  -3.750  -0.3866   0.07657   0.07146  -0.0062   1.0000   0.3163
  -3.500  -0.3841   0.07430   0.06926  -0.0031   1.0000   0.3493
  -3.250  -0.3839   0.07225   0.06730   0.0006   1.0000   0.3940
  -3.000  -0.1744   0.06494   0.05988   0.0245   1.0000   0.8756
  -2.750  -0.2261   0.06510   0.06023   0.0336   1.0000   0.8433
  -2.500  -0.3985   0.06682   0.06226   0.0243   1.0000   0.5441
  -2.250  -0.4052   0.06503   0.06061   0.0342   1.0000   0.5964
  -2.000  -0.4104   0.06322   0.05891   0.0438   1.0000   0.6495
  -1.750  -0.4132   0.06131   0.05709   0.0524   1.0000   0.7017
  -1.500  -0.4135   0.05926   0.05511   0.0571   1.0000   0.7393
  -1.250  -0.1132   0.04987   0.04258  -0.0466   1.0000   0.2518
  -1.000  -0.0323   0.04787   0.03937  -0.0561   0.9892   0.1873
  -0.750   0.0404   0.04647   0.03717  -0.0640   0.9753   0.1685
  -0.500   0.0985   0.04546   0.03557  -0.0694   0.9599   0.1634
  -0.250   0.1500   0.04469   0.03446  -0.0737   0.9443   0.1666
   0.000   0.2003   0.04413   0.03354  -0.0775   0.9287   0.1727
   0.250   0.2493   0.04351   0.03273  -0.0808   0.9135   0.1841
   0.500   0.2974   0.04297   0.03209  -0.0840   0.8983   0.2056
   0.750   0.3458   0.04220   0.03147  -0.0874   0.8831   0.2450
   1.000   0.3819   0.03946   0.03090  -0.0876   0.8682   1.0000
   1.250   0.4283   0.03967   0.03028  -0.0899   0.8517   1.0000
   1.500   0.4740   0.03968   0.02989  -0.0925   0.8354   1.0000
   1.750   0.5027   0.03997   0.02996  -0.0927   0.8153   1.0000
   2.000   0.5402   0.03995   0.02974  -0.0940   0.7973   1.0000
   2.250   0.5798   0.03976   0.02937  -0.0954   0.7802   1.0000
   2.500   0.6208   0.03935   0.02882  -0.0967   0.7638   1.0000
   2.750   0.6621   0.03877   0.02812  -0.0978   0.7478   1.0000
   3.000   0.7043   0.03796   0.02721  -0.0988   0.7325   1.0000
   3.250   0.7489   0.03695   0.02611  -0.0999   0.7175   1.0000
   3.500   0.7972   0.03581   0.02490  -0.1017   0.7024   1.0000
   3.750   0.8481   0.03463   0.02364  -0.1039   0.6867   1.0000
   4.000   0.8961   0.03362   0.02255  -0.1057   0.6701   1.0000
   4.250   0.9434   0.03276   0.02162  -0.1075   0.6525   1.0000
   4.500   0.9897   0.03210   0.02084  -0.1094   0.6344   1.0000
   4.750   1.0260   0.03207   0.02072  -0.1100   0.6157   1.0000
   5.000   1.0486   0.03269   0.02131  -0.1088   0.5963   1.0000
   5.250   1.0758   0.03321   0.02176  -0.1083   0.5783   1.0000
   5.500   1.1029   0.03379   0.02231  -0.1078   0.5611   1.0000
   5.750   1.1286   0.03448   0.02295  -0.1072   0.5449   1.0000
   6.000   1.1525   0.03532   0.02377  -0.1064   0.5296   1.0000
   6.250   1.1755   0.03625   0.02469  -0.1056   0.5153   1.0000
   6.500   1.1996   0.03718   0.02562  -0.1049   0.5018   1.0000
   6.750   1.2288   0.03796   0.02635  -0.1050   0.4893   1.0000
   7.000   1.2435   0.03934   0.02782  -0.1031   0.4770   1.0000
   7.250   1.2524   0.04108   0.02970  -0.1006   0.4658   1.0000
   7.500   1.2747   0.04230   0.03096  -0.0998   0.4555   1.0000
   7.750   1.2922   0.04374   0.03248  -0.0985   0.4455   1.0000
   8.000   1.2914   0.04614   0.03509  -0.0949   0.4367   1.0000
   8.250   1.3325   0.04658   0.03546  -0.0967   0.4273   1.0000
   8.500   1.2998   0.05064   0.03987  -0.0894   0.4203   1.0000
   8.750   1.3415   0.05113   0.04036  -0.0912   0.4122   1.0000
   9.000   1.2912   0.05656   0.04612  -0.0828   0.4072   1.0000
   9.250   0.9682   0.09425   0.08388  -0.0740   0.4073   1.0000
   9.500   0.9302   0.10374   0.09336  -0.0758   0.4064   1.0000
   9.750   0.9103   0.11082   0.10049  -0.0772   0.4065   1.0000
  10.000   0.9020   0.11679   0.10651  -0.0785   0.4085   1.0000
  10.250   0.9160   0.12114   0.11097  -0.0796   0.4115   1.0000
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