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USA 27 AIRFOIL (usa27-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: USA 27 AIRFOIL (usa27-il)
Reynolds number: 200,000
Max Cl/Cd: 69.42 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-usa27-il-200000.txt
Download as CSV file: xf-usa27-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA 27 AIRFOIL                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3431   0.11122   0.10792  -0.0332   1.0000   0.0406
  -9.000  -0.3578   0.10962   0.10640  -0.0324   1.0000   0.0407
  -8.750  -0.3744   0.10806   0.10491  -0.0311   1.0000   0.0407
  -8.500  -0.3579   0.10295   0.09980  -0.0276   1.0000   0.0416
  -8.250  -0.3579   0.10085   0.09773  -0.0251   1.0000   0.0421
  -8.000  -0.3637   0.09906   0.09598  -0.0229   1.0000   0.0427
  -7.750  -0.3737   0.09743   0.09440  -0.0207   1.0000   0.0432
  -7.500  -0.3669   0.09430   0.09128  -0.0233   0.9970   0.0443
  -7.250  -0.3534   0.09022   0.08720  -0.0292   0.9916   0.0463
  -7.000  -0.3239   0.08241   0.07916  -0.0528   0.9784   0.0498
  -6.750  -0.3140   0.07791   0.07476  -0.0499   0.9760   0.0509
  -6.500  -0.2906   0.07489   0.07174  -0.0514   0.9729   0.0523
  -6.250  -0.2706   0.07159   0.06841  -0.0544   0.9664   0.0545
  -6.000  -0.2295   0.06351   0.05987  -0.0705   0.9585   0.0610
  -5.750  -0.2163   0.06043   0.05690  -0.0692   0.9512   0.0621
  -5.500  -0.1849   0.05784   0.05431  -0.0715   0.9466   0.0646
  -5.250  -0.1521   0.05200   0.04796  -0.0788   0.9363   0.0741
  -5.000  -0.1203   0.04902   0.04511  -0.0810   0.9322   0.0762
  -4.750  -0.0819   0.04636   0.04239  -0.0847   0.9295   0.0809
  -4.500  -0.0614   0.04233   0.03803  -0.0860   0.9189   0.0898
  -4.250  -0.0240   0.04030   0.03601  -0.0888   0.9161   0.0952
  -4.000  -0.0006   0.03757   0.03307  -0.0894   0.9072   0.1057
  -3.750   0.0353   0.03536   0.03071  -0.0920   0.9030   0.1198
  -3.500   0.0736   0.03329   0.02851  -0.0947   0.9002   0.1347
  -3.250   0.0961   0.03181   0.02691  -0.0940   0.8899   0.1489
  -3.000   0.1321   0.03001   0.02502  -0.0958   0.8856   0.1648
  -2.750   0.1611   0.02337   0.01701  -0.0937   0.8756   0.1003
  -2.500   0.1953   0.02330   0.01739  -0.0963   0.8698   0.1370
  -2.250   0.2197   0.02341   0.01769  -0.0958   0.8577   0.1675
  -2.000   0.2663   0.01718   0.00957  -0.0944   0.8515   0.0644
  -1.750   0.2982   0.01637   0.00857  -0.0944   0.8400   0.0624
  -1.500   0.3278   0.01572   0.00782  -0.0942   0.8264   0.0617
  -1.250   0.3573   0.01503   0.00707  -0.0940   0.8120   0.0615
  -1.000   0.3858   0.01437   0.00638  -0.0937   0.7965   0.0618
  -0.750   0.4128   0.01379   0.00579  -0.0932   0.7802   0.0632
  -0.500   0.4392   0.01340   0.00537  -0.0926   0.7632   0.0661
  -0.250   0.4654   0.01312   0.00501  -0.0919   0.7458   0.0679
   0.000   0.4904   0.01294   0.00472  -0.0910   0.7269   0.0698
   0.250   0.5156   0.01282   0.00446  -0.0901   0.7077   0.0726
   0.500   0.5405   0.01269   0.00422  -0.0892   0.6888   0.0799
   0.750   0.5621   0.01227   0.00418  -0.0879   0.6710   0.2186
   1.000   0.5839   0.01210   0.00425  -0.0866   0.6538   0.3463
   1.250   0.7089   0.01115   0.00456  -0.1069   0.6261   1.0000
   1.500   0.7309   0.01140   0.00461  -0.1056   0.6083   1.0000
   1.750   0.7523   0.01165   0.00468  -0.1042   0.5905   1.0000
   2.000   0.7732   0.01188   0.00475  -0.1028   0.5730   1.0000
   2.250   0.7935   0.01209   0.00484  -0.1012   0.5558   1.0000
   2.500   0.8140   0.01230   0.00493  -0.0997   0.5400   1.0000
   2.750   0.8346   0.01252   0.00502  -0.0982   0.5255   1.0000
   3.000   0.8550   0.01273   0.00514  -0.0968   0.5116   1.0000
   3.250   0.8758   0.01295   0.00529  -0.0953   0.4989   1.0000
   3.500   0.8968   0.01319   0.00545  -0.0940   0.4878   1.0000
   3.750   0.9182   0.01347   0.00560  -0.0928   0.4782   1.0000
   4.000   0.9393   0.01371   0.00581  -0.0915   0.4682   1.0000
   4.250   0.9610   0.01399   0.00602  -0.0903   0.4596   1.0000
   4.500   0.9823   0.01427   0.00623  -0.0891   0.4508   1.0000
   4.750   1.0037   0.01455   0.00648  -0.0879   0.4425   1.0000
   5.000   1.0253   0.01484   0.00672  -0.0867   0.4346   1.0000
   5.250   1.0469   0.01513   0.00701  -0.0856   0.4273   1.0000
   5.500   1.0688   0.01542   0.00729  -0.0845   0.4206   1.0000
   5.750   1.0916   0.01577   0.00760  -0.0837   0.4146   1.0000
   6.000   1.1125   0.01604   0.00793  -0.0824   0.4080   1.0000
   6.250   1.1356   0.01640   0.00823  -0.0817   0.4021   1.0000
   6.500   1.1560   0.01669   0.00860  -0.0803   0.3957   1.0000
   6.750   1.1760   0.01697   0.00888  -0.0789   0.3879   1.0000
   7.000   1.1935   0.01721   0.00918  -0.0770   0.3785   1.0000
   7.250   1.2120   0.01751   0.00941  -0.0754   0.3691   1.0000
   7.500   1.2274   0.01768   0.00969  -0.0731   0.3592   1.0000
   7.750   1.2433   0.01793   0.00998  -0.0709   0.3489   1.0000
   8.000   1.2595   0.01822   0.01022  -0.0689   0.3388   1.0000
   8.250   1.2745   0.01843   0.01057  -0.0666   0.3286   1.0000
   8.500   1.2899   0.01873   0.01090  -0.0645   0.3186   1.0000
   8.750   1.3020   0.01903   0.01121  -0.0618   0.3066   1.0000
   9.000   1.3116   0.01933   0.01155  -0.0586   0.2922   1.0000
   9.250   1.3224   0.01969   0.01195  -0.0558   0.2763   1.0000
   9.500   1.3339   0.02013   0.01242  -0.0532   0.2581   1.0000
   9.750   1.3423   0.02077   0.01298  -0.0503   0.2347   1.0000
  10.000   1.3485   0.02164   0.01372  -0.0473   0.2071   1.0000
  10.250   1.3523   0.02278   0.01472  -0.0442   0.1832   1.0000
  10.750   1.3608   0.02532   0.01707  -0.0386   0.1455   1.0000
  11.000   1.3672   0.02656   0.01826  -0.0363   0.1241   1.0000
  11.250   1.3583   0.02891   0.02026  -0.0327   0.0783   1.0000
  11.500   1.3395   0.03216   0.02323  -0.0288   0.0391   1.0000
  11.750   1.3374   0.03436   0.02545  -0.0265   0.0347   1.0000
  12.000   1.3370   0.03652   0.02772  -0.0247   0.0320   1.0000
  12.250   1.3386   0.03864   0.02998  -0.0232   0.0306   1.0000
  12.500   1.3383   0.04100   0.03251  -0.0219   0.0294   1.0000
  12.750   1.3361   0.04369   0.03536  -0.0208   0.0284   1.0000
  13.000   1.3317   0.04676   0.03860  -0.0200   0.0276   1.0000
  13.250   1.3255   0.05021   0.04221  -0.0196   0.0271   1.0000
  13.500   1.3175   0.05408   0.04624  -0.0195   0.0267   1.0000
  13.750   1.3077   0.05833   0.05065  -0.0197   0.0263   1.0000
  14.000   1.2964   0.06292   0.05539  -0.0202   0.0261   1.0000
  14.250   1.2844   0.06774   0.06036  -0.0209   0.0259   1.0000
  14.500   1.2721   0.07272   0.06548  -0.0218   0.0257   1.0000
  14.750   1.2600   0.07772   0.07060  -0.0227   0.0256   1.0000
  15.000   1.2520   0.08222   0.07521  -0.0236   0.0254   1.0000
  15.250   1.2455   0.08651   0.07959  -0.0244   0.0253   1.0000
  15.500   1.2408   0.09049   0.08366  -0.0251   0.0252   1.0000
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