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PT40 (pt40-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: PT40 (pt40-il)
Reynolds number: 200,000
Max Cl/Cd: 64.3 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-pt40-il-200000.txt
Download as CSV file: xf-pt40-il-200000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3274   0.10088   0.09670  -0.0275   1.0000   0.0724
  -8.250  -0.3320   0.09784   0.09370  -0.0294   1.0000   0.0744
  -8.000  -0.3677   0.09357   0.08952  -0.0346   1.0000   0.0755
  -7.750  -0.3505   0.09118   0.08716  -0.0320   1.0000   0.0759
  -7.500  -0.3422   0.08902   0.08504  -0.0302   1.0000   0.0764
  -7.250  -0.3408   0.08696   0.08304  -0.0287   1.0000   0.0771
  -7.000  -0.3466   0.08505   0.08120  -0.0270   1.0000   0.0777
  -6.750  -0.3613   0.08345   0.07969  -0.0243   1.0000   0.0783
  -6.500  -0.3772   0.08166   0.07799  -0.0223   1.0000   0.0790
  -6.250  -0.4232   0.07352   0.06959  -0.0366   0.9971   0.0828
  -6.000  -0.3960   0.07071   0.06689  -0.0367   0.9944   0.0832
  -5.750  -0.3689   0.06820   0.06444  -0.0378   0.9908   0.0839
  -5.500  -0.3400   0.06547   0.06171  -0.0406   0.9860   0.0851
  -5.250  -0.3068   0.05749   0.05327  -0.0544   0.9769   0.0916
  -5.000  -0.2763   0.05497   0.05084  -0.0562   0.9729   0.0924
  -4.750  -0.2442   0.05249   0.04837  -0.0590   0.9686   0.0940
  -4.500  -0.2108   0.04740   0.04276  -0.0661   0.9600   0.1011
  -4.250  -0.1756   0.04484   0.04031  -0.0689   0.9573   0.1023
  -4.000  -0.1479   0.04293   0.03841  -0.0701   0.9489   0.1046
  -3.750  -0.1093   0.03951   0.03463  -0.0748   0.9445   0.1126
  -3.500  -0.0723   0.03747   0.03264  -0.0776   0.9410   0.1153
  -3.250  -0.0415   0.03524   0.03005  -0.0795   0.9321   0.1244
  -3.000  -0.0051   0.03317   0.02806  -0.0818   0.9283   0.1273
  -2.750   0.0249   0.03166   0.02625  -0.0828   0.9193   0.1382
  -2.500   0.0580   0.02983   0.02452  -0.0842   0.9132   0.1420
  -2.250   0.0888   0.02843   0.02297  -0.0852   0.9053   0.1550
  -2.000   0.1189   0.02734   0.02189  -0.0855   0.8963   0.1628
  -1.750   0.1605   0.02210   0.01511  -0.0851   0.8891   0.0997
  -1.500   0.1889   0.02077   0.01368  -0.0848   0.8784   0.0991
  -1.250   0.2188   0.01960   0.01238  -0.0846   0.8681   0.0985
  -1.000   0.2484   0.01854   0.01117  -0.0840   0.8551   0.0979
  -0.750   0.2752   0.01772   0.01020  -0.0829   0.8383   0.0979
  -0.500   0.3022   0.01710   0.00943  -0.0818   0.8210   0.0989
  -0.250   0.3298   0.01675   0.00890  -0.0808   0.8052   0.1003
   0.000   0.3577   0.01588   0.00800  -0.0802   0.7920   0.1017
   0.250   0.3837   0.01540   0.00754  -0.0793   0.7767   0.1031
   0.500   0.4106   0.01502   0.00716  -0.0785   0.7623   0.1050
   0.750   0.4379   0.01473   0.00681  -0.0778   0.7482   0.1079
   1.000   0.4646   0.01452   0.00655  -0.0769   0.7327   0.1104
   1.250   0.4903   0.01405   0.00615  -0.0760   0.7168   0.1130
   1.500   0.5166   0.01378   0.00592  -0.0752   0.7010   0.1164
   1.750   0.5430   0.01362   0.00573  -0.0743   0.6847   0.1211
   2.000   0.5688   0.01335   0.00548  -0.0734   0.6673   0.1261
   2.250   0.5945   0.01320   0.00534  -0.0725   0.6483   0.1323
   2.500   0.6201   0.01305   0.00520  -0.0716   0.6280   0.1419
   2.750   0.6456   0.01293   0.00508  -0.0707   0.6063   0.1603
   3.000   0.6799   0.01085   0.00517  -0.0713   0.5802   1.0000
   3.250   0.7036   0.01106   0.00515  -0.0699   0.5519   1.0000
   3.500   0.7265   0.01131   0.00519  -0.0685   0.5193   1.0000
   3.750   0.7485   0.01164   0.00529  -0.0669   0.4797   1.0000
   4.000   0.7688   0.01209   0.00544  -0.0652   0.4293   1.0000
   4.250   0.7878   0.01268   0.00568  -0.0633   0.3728   1.0000
   4.500   0.8070   0.01335   0.00600  -0.0616   0.3297   1.0000
   4.750   0.8279   0.01397   0.00637  -0.0602   0.3004   1.0000
   5.000   0.8494   0.01455   0.00676  -0.0589   0.2794   1.0000
   5.250   0.8719   0.01507   0.00713  -0.0578   0.2626   1.0000
   5.500   0.8949   0.01555   0.00752  -0.0568   0.2488   1.0000
   5.750   0.9173   0.01609   0.00792  -0.0557   0.2372   1.0000
   6.000   0.9407   0.01651   0.00828  -0.0548   0.2262   1.0000
   6.250   0.9639   0.01696   0.00868  -0.0539   0.2164   1.0000
   6.500   0.9867   0.01743   0.00907  -0.0529   0.2078   1.0000
   6.750   1.0100   0.01786   0.00949  -0.0519   0.2000   1.0000
   7.000   1.0327   0.01830   0.00989  -0.0510   0.1923   1.0000
   7.250   1.0555   0.01874   0.01032  -0.0500   0.1847   1.0000
   7.500   1.0777   0.01915   0.01070  -0.0489   0.1769   1.0000
   7.750   1.0998   0.01958   0.01115  -0.0479   0.1690   1.0000
   8.000   1.1207   0.02003   0.01155  -0.0467   0.1608   1.0000
   8.250   1.1424   0.02038   0.01196  -0.0456   0.1511   1.0000
   8.500   1.1626   0.02081   0.01239  -0.0443   0.1396   1.0000
   8.750   1.1811   0.02134   0.01286  -0.0428   0.1250   1.0000
   9.000   1.1978   0.02205   0.01349  -0.0411   0.1083   1.0000
   9.250   1.2124   0.02292   0.01424  -0.0391   0.0961   1.0000
   9.500   1.2253   0.02380   0.01508  -0.0368   0.0885   1.0000
   9.750   1.2374   0.02475   0.01599  -0.0345   0.0835   1.0000
  10.000   1.2496   0.02571   0.01691  -0.0323   0.0799   1.0000
  10.250   1.2615   0.02675   0.01796  -0.0301   0.0770   1.0000
  10.500   1.2741   0.02775   0.01899  -0.0281   0.0745   1.0000
  10.750   1.2851   0.02889   0.02008  -0.0261   0.0726   1.0000
  11.000   1.2971   0.03006   0.02128  -0.0243   0.0708   1.0000
  11.250   1.3097   0.03118   0.02245  -0.0226   0.0690   1.0000
  11.500   1.3218   0.03235   0.02364  -0.0210   0.0675   1.0000
  11.750   1.3337   0.03362   0.02486  -0.0194   0.0663   1.0000
  12.000   1.3471   0.03497   0.02620  -0.0180   0.0652   1.0000
  12.250   1.3595   0.03627   0.02761  -0.0165   0.0643   1.0000
  12.500   1.3720   0.03762   0.02904  -0.0152   0.0633   1.0000
  12.750   1.3845   0.03899   0.03048  -0.0139   0.0624   1.0000
  13.000   1.3975   0.04038   0.03190  -0.0127   0.0616   1.0000
  13.250   1.4113   0.04177   0.03330  -0.0115   0.0609   1.0000
  13.500   1.4280   0.04314   0.03464  -0.0106   0.0602   1.0000
  13.750   1.4463   0.04470   0.03618  -0.0098   0.0595   1.0000
  14.000   1.4510   0.04659   0.03827  -0.0083   0.0591   1.0000
  14.250   1.4549   0.04863   0.04049  -0.0070   0.0585   1.0000
  14.500   1.4583   0.05079   0.04283  -0.0059   0.0580   1.0000
  14.750   1.4609   0.05308   0.04528  -0.0048   0.0575   1.0000
  15.000   1.4627   0.05550   0.04786  -0.0040   0.0571   1.0000
  15.250   1.4635   0.05809   0.05060  -0.0032   0.0567   1.0000
  15.500   1.4629   0.06088   0.05354  -0.0027   0.0564   1.0000
  15.750   1.4605   0.06389   0.05672  -0.0023   0.0562   1.0000
  16.000   1.4555   0.06724   0.06024  -0.0022   0.0559   1.0000
  16.250   1.4476   0.07099   0.06417  -0.0024   0.0558   1.0000
  16.500   1.4362   0.07524   0.06862  -0.0030   0.0556   1.0000
  16.750   1.4201   0.08024   0.07384  -0.0042   0.0556   1.0000
  17.000   1.3951   0.08667   0.08054  -0.0067   0.0556   1.0000
  17.250   1.3451   0.09753   0.09184  -0.0126   0.0560   1.0000
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