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PW98-mod (pw98mod-pw) Xfoil prediction polar at RE=5,000,000 Ncrit=9


Details Polar file
Airfoil: PW98-mod (pw98mod-pw)
Reynolds number: 5,000,000
Max Cl/Cd: 106.82 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-pw98mod-pw-5000000.txt
Download as CSV file: xf-pw98mod-pw-5000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: PW98-mod                                        
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     5.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.8121   0.02376   0.02189  -0.0102   1.0000   0.0006
  -8.250  -0.7979   0.01925   0.01695  -0.0095   0.9965   0.0006
  -8.000  -0.7808   0.01644   0.01377  -0.0082   0.9614   0.0006
  -7.750  -0.7622   0.01438   0.01137  -0.0067   0.9372   0.0006
  -7.500  -0.7403   0.01269   0.00938  -0.0057   0.9156   0.0006
  -7.250  -0.7166   0.01132   0.00773  -0.0050   0.8949   0.0006
  -7.000  -0.6931   0.00966   0.00570  -0.0041   0.8737   0.0007
  -6.750  -0.6677   0.00865   0.00435  -0.0035   0.8519   0.0009
  -6.500  -0.6404   0.00826   0.00378  -0.0033   0.8309   0.0010
  -6.250  -0.6126   0.00802   0.00341  -0.0031   0.8092   0.0012
  -6.000  -0.5846   0.00785   0.00313  -0.0030   0.7874   0.0013
  -3.500  -0.2968   0.01025   0.00564  -0.0048   0.5992   0.0023
  -3.250  -0.2690   0.00970   0.00501  -0.0046   0.5845   0.0012
  -3.000  -0.2410   0.00929   0.00454  -0.0045   0.5701   0.0011
  -2.750  -0.2130   0.00888   0.00408  -0.0044   0.5556   0.0010
  -2.500  -0.1851   0.00845   0.00358  -0.0043   0.5417   0.0010
  -2.250  -0.1572   0.00801   0.00308  -0.0041   0.5277   0.0009
  -2.000  -0.1293   0.00759   0.00260  -0.0039   0.5139   0.0009
  -1.750  -0.1014   0.00716   0.00210  -0.0037   0.5001   0.0009
  -1.500  -0.0733   0.00684   0.00169  -0.0036   0.4853   0.0010
  -1.250  -0.0443   0.00730   0.00205  -0.0041   0.4692   0.0019
  -1.000  -0.0164   0.00612   0.00064  -0.0031   0.4562   0.0055
  -0.750   0.0122   0.00610   0.00061  -0.0032   0.4425   0.0065
  -0.500   0.0408   0.00609   0.00057  -0.0033   0.4287   0.0072
  -0.250   0.0694   0.00608   0.00053  -0.0034   0.4147   0.0083
   0.000   0.0980   0.00608   0.00051  -0.0035   0.4010   0.0086
   0.250   0.1267   0.00610   0.00051  -0.0035   0.3867   0.0122
   0.500   0.1553   0.00612   0.00051  -0.0036   0.3731   0.0157
   0.750   0.1839   0.00613   0.00051  -0.0037   0.3588   0.0201
   1.000   0.2120   0.00595   0.00050  -0.0038   0.3459   0.1040
   1.250   0.2395   0.00556   0.00050  -0.0040   0.3319   0.2794
   1.500   0.2648   0.00465   0.00051  -0.0040   0.3191   0.6447
   1.750   0.2903   0.00418   0.00055  -0.0036   0.3061   0.8369
   2.000   0.3176   0.00413   0.00059  -0.0034   0.2946   0.8856
   2.250   0.3445   0.00412   0.00064  -0.0031   0.2818   0.9208
   2.500   0.3713   0.00416   0.00069  -0.0027   0.2700   0.9445
   2.750   0.3967   0.00445   0.00082  -0.0023   0.2140   0.9685
   3.000   0.4247   0.00491   0.00100  -0.0025   0.1431   0.9839
   3.250   0.4540   0.00589   0.00146  -0.0033   0.0101   0.9931
   3.500   0.4892   0.00607   0.00159  -0.0050   0.0021   0.9965
   3.750   0.5230   0.00618   0.00168  -0.0063   0.0008   0.9986
   4.000   0.5555   0.00631   0.00179  -0.0074   0.0007   0.9997
   4.250   0.5838   0.00644   0.00191  -0.0075   0.0008   1.0000
   4.500   0.6103   0.00657   0.00201  -0.0072   0.0008   1.0000
   4.750   0.6369   0.00669   0.00210  -0.0070   0.0009   1.0000
   5.000   0.6637   0.00682   0.00220  -0.0068   0.0011   1.0000
   5.250   0.6910   0.00684   0.00221  -0.0067   0.0086   1.0000
   5.500   0.7189   0.00673   0.00218  -0.0066   0.0258   1.0000
   5.750   0.7454   0.00718   0.00252  -0.0065   0.0049   1.0000
   6.000   0.7729   0.00734   0.00265  -0.0064   0.0023   1.0000
   6.500   0.8272   0.00787   0.00324  -0.0063   0.0012   1.0000
   6.750   0.8545   0.00811   0.00350  -0.0063   0.0009   1.0000
   7.000   0.8815   0.00844   0.00388  -0.0062   0.0007   1.0000
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