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PT40 (pt40-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: PT40 (pt40-il)
Reynolds number: 200,000
Max Cl/Cd: 57.47 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-pt40-il-200000-n5.txt
Download as CSV file: xf-pt40-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: PT40                                            
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3460   0.10684   0.10251  -0.0265   1.0000   0.0554
  -9.000  -0.3490   0.10305   0.09874  -0.0288   1.0000   0.0567
  -8.750  -0.3556   0.09886   0.09457  -0.0315   1.0000   0.0570
  -8.250  -0.3542   0.09140   0.08716  -0.0322   1.0000   0.0517
  -8.000  -0.3508   0.08897   0.08478  -0.0317   1.0000   0.0510
  -7.750  -0.3544   0.08597   0.08183  -0.0317   1.0000   0.0504
  -7.500  -0.3639   0.08287   0.07879  -0.0315   1.0000   0.0498
  -7.250  -0.3824   0.08001   0.07602  -0.0302   1.0000   0.0494
  -7.000  -0.3964   0.07578   0.07183  -0.0322   0.9983   0.0490
  -6.750  -0.3763   0.06951   0.06550  -0.0419   0.9913   0.0494
  -6.500  -0.3553   0.06279   0.05866  -0.0514   0.9835   0.0500
  -6.250  -0.3363   0.05563   0.05131  -0.0595   0.9741   0.0501
  -6.000  -0.3159   0.04875   0.04415  -0.0660   0.9654   0.0503
  -5.750  -0.2940   0.04117   0.03609  -0.0716   0.9578   0.0512
  -5.500  -0.2785   0.03330   0.02743  -0.0744   0.9471   0.0524
  -5.250  -0.2464   0.03184   0.02589  -0.0761   0.9423   0.0527
  -5.000  -0.2210   0.03026   0.02418  -0.0764   0.9322   0.0532
  -4.750  -0.1894   0.02837   0.02209  -0.0780   0.9264   0.0538
  -4.500  -0.1632   0.02674   0.02025  -0.0782   0.9159   0.0547
  -4.250  -0.1325   0.02445   0.01756  -0.0792   0.9090   0.0561
  -4.000  -0.1058   0.02224   0.01486  -0.0792   0.8984   0.0570
  -3.750  -0.0742   0.02119   0.01369  -0.0800   0.8905   0.0576
  -3.500  -0.0454   0.02049   0.01295  -0.0800   0.8797   0.0581
  -3.250  -0.0147   0.01980   0.01217  -0.0804   0.8703   0.0588
  -3.000   0.0140   0.01916   0.01144  -0.0803   0.8591   0.0598
  -2.750   0.0431   0.01843   0.01055  -0.0803   0.8488   0.0611
  -2.500   0.0717   0.01766   0.00954  -0.0800   0.8376   0.0623
  -2.250   0.0998   0.01706   0.00885  -0.0797   0.8266   0.0630
  -2.000   0.1280   0.01662   0.00839  -0.0795   0.8157   0.0638
  -1.750   0.1556   0.01623   0.00797  -0.0791   0.8044   0.0646
  -1.500   0.1837   0.01587   0.00755  -0.0788   0.7936   0.0659
  -1.250   0.2110   0.01553   0.00715  -0.0783   0.7817   0.0674
  -1.000   0.2384   0.01519   0.00668  -0.0776   0.7671   0.0688
  -0.750   0.2649   0.01487   0.00635  -0.0769   0.7485   0.0698
  -0.500   0.2910   0.01463   0.00605  -0.0761   0.7270   0.0709
  -0.250   0.3172   0.01440   0.00576  -0.0753   0.7066   0.0723
   0.000   0.3437   0.01422   0.00550  -0.0746   0.6884   0.0741
   0.250   0.3703   0.01402   0.00528  -0.0739   0.6720   0.0759
   0.500   0.3967   0.01384   0.00513  -0.0733   0.6556   0.0776
   0.750   0.4231   0.01370   0.00497  -0.0727   0.6383   0.0794
   1.000   0.4495   0.01359   0.00482  -0.0720   0.6203   0.0814
   1.250   0.4756   0.01350   0.00470  -0.0713   0.6010   0.0838
   1.500   0.5016   0.01344   0.00462  -0.0706   0.5805   0.0866
   1.750   0.5275   0.01343   0.00455  -0.0698   0.5587   0.0896
   2.000   0.5531   0.01343   0.00450  -0.0691   0.5356   0.0925
   2.250   0.5785   0.01349   0.00449  -0.0683   0.5110   0.0969
   2.500   0.6035   0.01358   0.00449  -0.0674   0.4843   0.1022
   2.750   0.6283   0.01370   0.00453  -0.0666   0.4536   0.1091
   3.000   0.6525   0.01386   0.00459  -0.0657   0.4196   0.1208
   3.250   0.6754   0.01383   0.00473  -0.0647   0.3806   0.2179
   3.750   0.7259   0.01288   0.00526  -0.0633   0.3049   1.0000
   4.000   0.7487   0.01331   0.00550  -0.0622   0.2805   1.0000
   4.250   0.7719   0.01372   0.00575  -0.0612   0.2617   1.0000
   4.500   0.7954   0.01411   0.00601  -0.0602   0.2461   1.0000
   4.750   0.8189   0.01450   0.00629  -0.0592   0.2322   1.0000
   5.000   0.8422   0.01491   0.00658  -0.0583   0.2194   1.0000
   5.250   0.8656   0.01531   0.00687  -0.0573   0.2071   1.0000
   5.500   0.8896   0.01566   0.00716  -0.0565   0.1965   1.0000
   5.750   0.9129   0.01606   0.00748  -0.0556   0.1873   1.0000
   6.000   0.9367   0.01641   0.00778  -0.0547   0.1781   1.0000
   6.250   0.9601   0.01679   0.00811  -0.0538   0.1697   1.0000
   6.500   0.9833   0.01718   0.00844  -0.0529   0.1615   1.0000
   6.750   1.0069   0.01754   0.00878  -0.0520   0.1547   1.0000
   7.000   1.0296   0.01795   0.00915  -0.0510   0.1478   1.0000
   7.250   1.0528   0.01832   0.00952  -0.0501   0.1407   1.0000
   7.500   1.0750   0.01876   0.00990  -0.0491   0.1334   1.0000
   7.750   1.0974   0.01916   0.01031  -0.0481   0.1254   1.0000
   8.000   1.1194   0.01960   0.01073  -0.0471   0.1172   1.0000
   8.250   1.1406   0.02009   0.01118  -0.0459   0.1078   1.0000
   8.500   1.1609   0.02063   0.01168  -0.0447   0.0969   1.0000
   8.750   1.1799   0.02126   0.01223  -0.0433   0.0851   1.0000
   9.000   1.1978   0.02197   0.01286  -0.0418   0.0743   1.0000
   9.250   1.2145   0.02273   0.01356  -0.0402   0.0668   1.0000
   9.500   1.2299   0.02349   0.01430  -0.0383   0.0619   1.0000
   9.750   1.2439   0.02429   0.01508  -0.0363   0.0587   1.0000
  10.000   1.2580   0.02508   0.01590  -0.0343   0.0562   1.0000
  10.250   1.2706   0.02599   0.01682  -0.0322   0.0544   1.0000
  10.500   1.2835   0.02687   0.01775  -0.0303   0.0529   1.0000
  10.750   1.2957   0.02781   0.01874  -0.0284   0.0515   1.0000
  11.000   1.3066   0.02886   0.01984  -0.0265   0.0504   1.0000
  11.250   1.3159   0.03005   0.02106  -0.0246   0.0495   1.0000
  11.500   1.3247   0.03131   0.02236  -0.0228   0.0486   1.0000
  11.750   1.3343   0.03256   0.02370  -0.0212   0.0477   1.0000
  12.000   1.3428   0.03394   0.02515  -0.0196   0.0469   1.0000
  12.250   1.3503   0.03544   0.02672  -0.0182   0.0462   1.0000
  12.500   1.3568   0.03709   0.02844  -0.0170   0.0455   1.0000
  12.750   1.3620   0.03892   0.03031  -0.0158   0.0449   1.0000
  13.000   1.3657   0.04094   0.03238  -0.0148   0.0444   1.0000
  13.250   1.3700   0.04299   0.03450  -0.0139   0.0440   1.0000
  13.500   1.3748   0.04506   0.03667  -0.0132   0.0436   1.0000
  13.750   1.3788   0.04726   0.03898  -0.0126   0.0431   1.0000
  14.000   1.3820   0.04961   0.04142  -0.0121   0.0427   1.0000
  14.250   1.3845   0.05208   0.04398  -0.0118   0.0424   1.0000
  14.500   1.3862   0.05468   0.04667  -0.0116   0.0420   1.0000
  14.750   1.3875   0.05740   0.04947  -0.0115   0.0417   1.0000
  15.000   1.3881   0.06024   0.05241  -0.0116   0.0414   1.0000
  15.250   1.3883   0.06318   0.05543  -0.0117   0.0411   1.0000
  15.500   1.3884   0.06621   0.05853  -0.0120   0.0408   1.0000
  15.750   1.3884   0.06930   0.06169  -0.0124   0.0405   1.0000
  16.000   1.3884   0.07242   0.06487  -0.0128   0.0403   1.0000
  16.250   1.3888   0.07549   0.06799  -0.0132   0.0400   1.0000
  16.500   1.3900   0.07847   0.07099  -0.0136   0.0398   1.0000
  16.750   1.3868   0.08234   0.07502  -0.0147   0.0395   1.0000
  17.000   1.3825   0.08645   0.07928  -0.0161   0.0393   1.0000
  17.250   1.3775   0.09074   0.08372  -0.0176   0.0390   1.0000
  17.500   1.3717   0.09524   0.08837  -0.0194   0.0388   1.0000
  17.750   1.3653   0.09995   0.09322  -0.0213   0.0385   1.0000
  18.000   1.3581   0.10487   0.09830  -0.0235   0.0383   1.0000
  18.250   1.3501   0.11001   0.10358  -0.0260   0.0381   1.0000
  18.500   1.3415   0.11538   0.10910  -0.0287   0.0379   1.0000
  18.750   1.3319   0.12105   0.11492  -0.0317   0.0377   1.0000
  19.000   1.3209   0.12715   0.12117  -0.0351   0.0375   1.0000
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