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S2091-101-83 (s2091-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: S2091-101-83 (s2091-il)
Reynolds number: 50,000
Max Cl/Cd: 28.86 at α=9.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s2091-il-50000.txt
Download as CSV file: xf-s2091-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S2091-101-83                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3270   0.10842   0.10191  -0.0263   1.0000   0.2003
  -8.250  -0.3010   0.10237   0.09585  -0.0245   1.0000   0.2099
  -8.000  -0.3214   0.10279   0.09646  -0.0263   1.0000   0.2160
  -7.750  -0.2957   0.09707   0.09072  -0.0246   1.0000   0.2249
  -7.500  -0.3200   0.09760   0.09148  -0.0250   1.0000   0.2315
  -7.250  -0.2974   0.09253   0.08640  -0.0233   1.0000   0.2420
  -7.000  -0.3294   0.09346   0.08760  -0.0211   1.0000   0.2470
  -6.750  -0.3133   0.08933   0.08349  -0.0189   1.0000   0.2582
  -6.500  -0.3451   0.08992   0.08428  -0.0155   1.0000   0.2622
  -6.250  -0.3415   0.08704   0.08148  -0.0121   1.0000   0.2722
  -6.000  -0.3712   0.08733   0.08193  -0.0102   1.0000   0.2783
  -5.750  -0.3683   0.08458   0.07924  -0.0064   1.0000   0.2905
  -5.500  -0.3788   0.08287   0.07765  -0.0039   1.0000   0.3009
  -5.250  -0.4010   0.08237   0.07726  -0.0042   1.0000   0.3120
  -5.000  -0.4060   0.08041   0.07537  -0.0020   1.0000   0.3278
  -4.750  -0.4071   0.07804   0.07307   0.0012   1.0000   0.3444
  -4.500  -0.4074   0.07568   0.07076   0.0044   1.0000   0.3615
  -4.250  -0.4068   0.07340   0.06855   0.0079   1.0000   0.3803
  -4.000  -0.4131   0.07183   0.06703   0.0091   1.0000   0.4077
  -3.750  -0.4096   0.06934   0.06461   0.0146   1.0000   0.4319
  -3.500  -0.2821   0.04782   0.04090  -0.0461   1.0000   0.1696
  -3.250  -0.2605   0.04444   0.03743  -0.0468   1.0000   0.1641
  -3.000  -0.2229   0.03987   0.03191  -0.0511   1.0000   0.1522
  -2.750  -0.1943   0.03728   0.02869  -0.0527   1.0000   0.1543
  -2.500  -0.1716   0.03535   0.02662  -0.0530   1.0000   0.1582
  -2.250  -0.1467   0.03379   0.02468  -0.0535   1.0000   0.1643
  -2.000  -0.1223   0.03246   0.02302  -0.0538   1.0000   0.1736
  -1.750  -0.0787   0.03136   0.02163  -0.0573   0.9921   0.1923
  -1.500  -0.0320   0.03053   0.02061  -0.0611   0.9820   0.2214
  -1.250   0.0141   0.02995   0.01998  -0.0646   0.9717   0.2661
  -1.000   0.0565   0.02931   0.01958  -0.0675   0.9606   0.3397
  -0.750   0.0871   0.02700   0.01944  -0.0666   0.9520   0.6951
  -0.500   0.1326   0.02714   0.01911  -0.0699   0.9383   1.0000
  -0.250   0.1743   0.02807   0.01954  -0.0732   0.9254   1.0000
   0.000   0.2163   0.02899   0.02009  -0.0765   0.9124   1.0000
   0.250   0.2537   0.02983   0.02063  -0.0789   0.8987   1.0000
   0.500   0.2862   0.03063   0.02121  -0.0804   0.8847   1.0000
   0.750   0.3179   0.03146   0.02184  -0.0818   0.8707   1.0000
   1.000   0.3498   0.03228   0.02249  -0.0831   0.8565   1.0000
   1.250   0.3814   0.03310   0.02317  -0.0843   0.8424   1.0000
   1.500   0.4131   0.03391   0.02386  -0.0854   0.8283   1.0000
   1.750   0.4452   0.03470   0.02454  -0.0864   0.8144   1.0000
   2.000   0.4782   0.03545   0.02521  -0.0875   0.8004   1.0000
   2.250   0.5132   0.03612   0.02581  -0.0886   0.7866   1.0000
   2.500   0.5545   0.03658   0.02623  -0.0904   0.7735   1.0000
   2.750   0.5824   0.03728   0.02691  -0.0905   0.7589   1.0000
   3.000   0.6095   0.03799   0.02760  -0.0904   0.7441   1.0000
   3.250   0.6362   0.03871   0.02832  -0.0902   0.7294   1.0000
   3.500   0.6626   0.03940   0.02901  -0.0898   0.7147   1.0000
   3.750   0.6881   0.04011   0.02973  -0.0893   0.7001   1.0000
   4.000   0.7137   0.04078   0.03044  -0.0888   0.6854   1.0000
   4.250   0.7392   0.04144   0.03113  -0.0881   0.6709   1.0000
   4.500   0.7648   0.04204   0.03177  -0.0873   0.6563   1.0000
   4.750   0.7902   0.04264   0.03242  -0.0865   0.6419   1.0000
   5.000   0.8165   0.04312   0.03299  -0.0856   0.6276   1.0000
   5.250   0.8434   0.04353   0.03346  -0.0847   0.6137   1.0000
   5.500   0.8731   0.04362   0.03363  -0.0837   0.6000   1.0000
   5.750   0.9227   0.04194   0.03207  -0.0830   0.5895   1.0000
   6.000   0.9470   0.04235   0.03257  -0.0817   0.5747   1.0000
   6.250   0.9707   0.04282   0.03312  -0.0803   0.5598   1.0000
   6.500   0.9957   0.04313   0.03356  -0.0790   0.5450   1.0000
   6.750   1.0198   0.04355   0.03408  -0.0776   0.5301   1.0000
   7.000   1.0456   0.04377   0.03440  -0.0762   0.5151   1.0000
   7.250   1.0709   0.04406   0.03483  -0.0748   0.5001   1.0000
   7.500   1.0991   0.04403   0.03490  -0.0734   0.4849   1.0000
   7.750   1.1276   0.04398   0.03496  -0.0720   0.4694   1.0000
   8.000   1.1600   0.04355   0.03464  -0.0707   0.4534   1.0000
   8.250   1.1933   0.04305   0.03418  -0.0694   0.4368   1.0000
   8.500   1.2071   0.04439   0.03568  -0.0676   0.4199   1.0000
   8.750   1.2225   0.04551   0.03694  -0.0658   0.4028   1.0000
   9.000   1.2411   0.04635   0.03791  -0.0641   0.3853   1.0000
   9.250   1.2696   0.04618   0.03780  -0.0626   0.3662   1.0000
   9.500   1.3071   0.04529   0.03681  -0.0614   0.3453   1.0000
   9.750   1.3160   0.04694   0.03866  -0.0593   0.3276   1.0000
  10.000   1.3304   0.04802   0.03984  -0.0573   0.3085   1.0000
  10.250   1.3649   0.04756   0.03917  -0.0562   0.2857   1.0000
  10.500   1.3701   0.04950   0.04129  -0.0538   0.2688   1.0000
  10.750   1.3768   0.05138   0.04329  -0.0516   0.2522   1.0000
  11.000   1.3837   0.05330   0.04532  -0.0494   0.2363   1.0000
  11.250   1.3893   0.05543   0.04754  -0.0473   0.2220   1.0000
  11.500   1.3943   0.05764   0.04983  -0.0452   0.2088   1.0000
  11.750   1.4022   0.05987   0.05209  -0.0434   0.1963   1.0000
  12.000   1.3719   0.06432   0.05687  -0.0402   0.1937   1.0000
  12.250   1.3495   0.06860   0.06134  -0.0383   0.1895   1.0000
  12.500   1.3176   0.07441   0.06734  -0.0377   0.1881   1.0000
  12.750   1.2876   0.08096   0.07403  -0.0383   0.1864   1.0000
  13.000   1.2577   0.08852   0.08167  -0.0401   0.1849   1.0000
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