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Joukovsky f=0% t=9% (joukowsk0009-jf) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: Joukovsky f=0% t=9% (joukowsk0009-jf)
Reynolds number: 200,000
Max Cl/Cd: 44.08 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-joukowsk0009-jf-200000-n5.txt
Download as CSV file: xf-joukowsk0009-jf-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Joukovsky f=0% t=9%                             
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -13.250  -0.9372   0.09164   0.08782   0.0163   1.0000   0.0165
 -13.000  -0.9688   0.07987   0.07589   0.0080   1.0000   0.0163
 -12.750  -0.9932   0.07048   0.06633   0.0008   1.0000   0.0162
 -12.500  -1.0141   0.06256   0.05823  -0.0053   1.0000   0.0161
 -12.250  -1.0328   0.05588   0.05133  -0.0104   1.0000   0.0161
 -12.000  -1.0488   0.05052   0.04573  -0.0138   1.0000   0.0161
 -11.750  -1.0630   0.04628   0.04123  -0.0155   1.0000   0.0163
 -11.500  -1.0736   0.04303   0.03774  -0.0152   1.0000   0.0164
 -11.250  -1.0778   0.04022   0.03463  -0.0141   1.0000   0.0166
 -11.000  -1.0745   0.03761   0.03181  -0.0133   1.0000   0.0169
 -10.750  -1.0641   0.03582   0.02991  -0.0127   1.0000   0.0174
 -10.500  -1.0506   0.03428   0.02826  -0.0121   1.0000   0.0180
 -10.250  -1.0355   0.03274   0.02655  -0.0115   1.0000   0.0187
 -10.000  -1.0195   0.03108   0.02468  -0.0109   1.0000   0.0195
  -9.750  -1.0023   0.02932   0.02264  -0.0103   1.0000   0.0204
  -9.500  -0.9837   0.02767   0.02073  -0.0096   1.0000   0.0211
  -9.250  -0.9646   0.02604   0.01894  -0.0090   1.0000   0.0219
  -9.000  -0.9443   0.02474   0.01757  -0.0086   1.0000   0.0228
  -8.750  -0.9224   0.02373   0.01647  -0.0082   1.0000   0.0240
  -8.500  -0.8995   0.02279   0.01541  -0.0078   1.0000   0.0257
  -8.250  -0.8762   0.02183   0.01426  -0.0073   1.0000   0.0273
  -8.000  -0.8542   0.02064   0.01302  -0.0069   1.0000   0.0289
  -7.750  -0.8305   0.01978   0.01210  -0.0065   1.0000   0.0307
  -7.500  -0.8060   0.01903   0.01126  -0.0062   1.0000   0.0333
  -7.250  -0.7818   0.01819   0.01033  -0.0059   1.0000   0.0360
  -7.000  -0.7573   0.01741   0.00953  -0.0056   1.0000   0.0390
  -6.750  -0.7320   0.01678   0.00880  -0.0053   1.0000   0.0427
  -6.500  -0.7069   0.01606   0.00808  -0.0050   1.0000   0.0475
  -6.250  -0.6811   0.01550   0.00744  -0.0048   1.0000   0.0531
  -6.000  -0.6555   0.01487   0.00683  -0.0046   1.0000   0.0600
  -5.750  -0.6294   0.01434   0.00629  -0.0044   1.0000   0.0692
  -5.500  -0.6033   0.01383   0.00580  -0.0042   1.0000   0.0809
  -5.250  -0.5772   0.01331   0.00534  -0.0040   1.0000   0.0964
  -5.000  -0.5509   0.01284   0.00493  -0.0039   1.0000   0.1156
  -4.750  -0.5246   0.01236   0.00455  -0.0037   1.0000   0.1391
  -4.500  -0.4982   0.01192   0.00422  -0.0036   1.0000   0.1666
  -4.250  -0.4718   0.01149   0.00391  -0.0035   1.0000   0.1976
  -4.000  -0.4453   0.01110   0.00365  -0.0034   1.0000   0.2311
  -3.750  -0.4188   0.01074   0.00342  -0.0032   1.0000   0.2653
  -3.500  -0.3923   0.01040   0.00321  -0.0030   1.0000   0.3007
  -3.250  -0.3659   0.01009   0.00304  -0.0028   1.0000   0.3360
  -3.000  -0.3395   0.00982   0.00290  -0.0026   1.0000   0.3700
  -2.750  -0.3133   0.00957   0.00278  -0.0023   1.0000   0.4033
  -2.500  -0.2839   0.00935   0.00269  -0.0027   0.9894   0.4373
  -2.250  -0.2472   0.00918   0.00263  -0.0045   0.9614   0.4729
  -2.000  -0.2122   0.00903   0.00259  -0.0058   0.9338   0.5060
  -1.750  -0.1810   0.00893   0.00254  -0.0062   0.9053   0.5365
  -1.500  -0.1531   0.00885   0.00250  -0.0057   0.8770   0.5648
  -1.250  -0.1272   0.00879   0.00247  -0.0048   0.8495   0.5919
  -1.000  -0.1020   0.00874   0.00244  -0.0038   0.8227   0.6179
  -0.750  -0.0766   0.00870   0.00241  -0.0028   0.7963   0.6437
  -0.500  -0.0511   0.00868   0.00239  -0.0018   0.7707   0.6695
  -0.250  -0.0257   0.00867   0.00238  -0.0009   0.7455   0.6947
   0.000   0.0000   0.00866   0.00238   0.0000   0.7200   0.7200
   0.250   0.0257   0.00867   0.00238   0.0009   0.6947   0.7455
   0.500   0.0511   0.00868   0.00239   0.0018   0.6696   0.7707
   0.750   0.0766   0.00870   0.00241   0.0028   0.6437   0.7963
   1.000   0.1020   0.00874   0.00244   0.0038   0.6179   0.8227
   1.250   0.1272   0.00879   0.00247   0.0048   0.5919   0.8494
   1.500   0.1531   0.00885   0.00250   0.0057   0.5648   0.8770
   1.750   0.1810   0.00893   0.00254   0.0062   0.5364   0.9053
   2.000   0.2122   0.00903   0.00259   0.0058   0.5059   0.9338
   2.250   0.2472   0.00918   0.00263   0.0045   0.4730   0.9613
   2.500   0.2840   0.00935   0.00269   0.0027   0.4374   0.9894
   2.750   0.3134   0.00957   0.00278   0.0023   0.4032   1.0000
   3.000   0.3396   0.00982   0.00290   0.0026   0.3700   1.0000
   3.250   0.3660   0.01009   0.00304   0.0028   0.3359   1.0000
   3.500   0.3924   0.01040   0.00321   0.0030   0.3007   1.0000
   3.750   0.4188   0.01074   0.00342   0.0032   0.2652   1.0000
   4.000   0.4453   0.01110   0.00365   0.0033   0.2310   1.0000
   4.250   0.4718   0.01149   0.00391   0.0035   0.1976   1.0000
   4.500   0.4982   0.01192   0.00422   0.0036   0.1667   1.0000
   4.750   0.5246   0.01236   0.00455   0.0037   0.1389   1.0000
   5.000   0.5509   0.01284   0.00493   0.0039   0.1155   1.0000
   5.250   0.5771   0.01331   0.00534   0.0040   0.0963   1.0000
   5.500   0.6033   0.01383   0.00580   0.0042   0.0808   1.0000
   5.750   0.6294   0.01434   0.00629   0.0044   0.0692   1.0000
   6.000   0.6554   0.01487   0.00683   0.0046   0.0601   1.0000
   6.250   0.6810   0.01550   0.00744   0.0048   0.0531   1.0000
   6.500   0.7068   0.01606   0.00808   0.0050   0.0475   1.0000
   6.750   0.7318   0.01678   0.00880   0.0053   0.0427   1.0000
   7.000   0.7571   0.01741   0.00952   0.0056   0.0390   1.0000
   7.250   0.7814   0.01819   0.01033   0.0059   0.0360   1.0000
   7.500   0.8056   0.01903   0.01127   0.0063   0.0333   1.0000
   7.750   0.8300   0.01977   0.01210   0.0066   0.0307   1.0000
   8.000   0.8536   0.02063   0.01301   0.0070   0.0289   1.0000
   8.250   0.8756   0.02182   0.01425   0.0074   0.0273   1.0000
   8.500   0.8987   0.02277   0.01539   0.0079   0.0257   1.0000
   8.750   0.9213   0.02372   0.01647   0.0084   0.0241   1.0000
   9.000   0.9432   0.02471   0.01754   0.0088   0.0228   1.0000
   9.250   0.9633   0.02601   0.01891   0.0093   0.0219   1.0000
   9.500   0.9824   0.02763   0.02068   0.0099   0.0211   1.0000
   9.750   1.0011   0.02928   0.02260   0.0105   0.0204   1.0000
  10.000   1.0183   0.03104   0.02463   0.0112   0.0196   1.0000
  10.250   1.0345   0.03272   0.02653   0.0117   0.0187   1.0000
  10.500   1.0497   0.03430   0.02828   0.0123   0.0180   1.0000
  10.750   1.0635   0.03581   0.02991   0.0128   0.0174   1.0000
  11.000   1.0745   0.03756   0.03175   0.0134   0.0169   1.0000
  11.250   1.0778   0.04021   0.03461   0.0141   0.0166   1.0000
  11.500   1.0734   0.04303   0.03774   0.0152   0.0164   1.0000
  11.750   1.0621   0.04634   0.04132   0.0155   0.0162   1.0000
  12.000   1.0494   0.05045   0.04566   0.0139   0.0162   1.0000
  12.250   1.0332   0.05583   0.05127   0.0104   0.0161   1.0000
  12.500   1.0147   0.06249   0.05815   0.0054   0.0161   1.0000
  12.750   0.9920   0.07085   0.06673  -0.0013   0.0161   1.0000
  13.000   0.9665   0.08056   0.07661  -0.0086   0.0163   1.0000
  13.250   0.9363   0.09209   0.08827  -0.0168   0.0165   1.0000
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