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S2091-101-83 (s2091-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: S2091-101-83 (s2091-il)
Reynolds number: 200,000
Max Cl/Cd: 77.91 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s2091-il-200000.txt
Download as CSV file: xf-s2091-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3043   0.08947   0.08617  -0.0336   1.0000   0.0494
  -8.000  -0.3026   0.08657   0.08333  -0.0348   1.0000   0.0509
  -7.750  -0.3067   0.08400   0.08085  -0.0358   1.0000   0.0522
  -7.500  -0.3306   0.08346   0.08045  -0.0322   1.0000   0.0528
  -7.250  -0.3254   0.07658   0.07357  -0.0530   0.9872   0.0546
  -7.000  -0.3062   0.06982   0.06681  -0.0580   0.9822   0.0556
  -6.750  -0.2835   0.06744   0.06444  -0.0572   0.9773   0.0570
  -6.500  -0.2524   0.06330   0.06026  -0.0633   0.9727   0.0597
  -6.250  -0.2159   0.05134   0.04774  -0.0866   0.9599   0.0671
  -6.000  -0.1914   0.04970   0.04632  -0.0854   0.9548   0.0694
  -5.750  -0.1651   0.04661   0.04313  -0.0883   0.9462   0.0733
  -5.500  -0.1487   0.02886   0.02373  -0.0967   0.9321   0.0434
  -5.250  -0.1257   0.02518   0.01952  -0.0969   0.9230   0.0429
  -5.000  -0.1000   0.02313   0.01682  -0.0965   0.9148   0.0450
  -4.750  -0.0774   0.02088   0.01436  -0.0959   0.9053   0.0470
  -4.500  -0.0519   0.01964   0.01293  -0.0951   0.8982   0.0490
  -4.250  -0.0270   0.01881   0.01187  -0.0943   0.8883   0.0527
  -4.000  -0.0017   0.01755   0.01032  -0.0933   0.8809   0.0560
  -3.750   0.0232   0.01670   0.00946  -0.0926   0.8716   0.0601
  -3.500   0.0492   0.01623   0.00882  -0.0917   0.8635   0.0657
  -3.250   0.0741   0.01521   0.00781  -0.0909   0.8550   0.0719
  -3.000   0.1000   0.01463   0.00716  -0.0901   0.8465   0.0814
  -2.750   0.1260   0.01417   0.00665  -0.0893   0.8384   0.0935
  -2.500   0.1516   0.01358   0.00613  -0.0888   0.8294   0.1107
  -2.250   0.1776   0.01314   0.00572  -0.0881   0.8217   0.1311
  -2.000   0.2039   0.01273   0.00542  -0.0877   0.8121   0.1598
  -1.750   0.2299   0.01221   0.00507  -0.0871   0.8049   0.2155
  -1.500   0.2549   0.01149   0.00495  -0.0868   0.7946   0.3620
  -1.250   0.2786   0.01087   0.00490  -0.0858   0.7865   0.5381
  -1.000   0.2998   0.01033   0.00487  -0.0838   0.7771   0.6981
  -0.750   0.3246   0.00977   0.00477  -0.0817   0.7683   0.9113
  -0.500   0.3653   0.00967   0.00447  -0.0839   0.7595   1.0000
  -0.250   0.3922   0.00973   0.00439  -0.0836   0.7490   1.0000
   0.000   0.4193   0.00978   0.00428  -0.0832   0.7398   1.0000
   0.250   0.4464   0.00983   0.00419  -0.0828   0.7297   1.0000
   0.500   0.4735   0.00990   0.00415  -0.0824   0.7190   1.0000
   0.750   0.5007   0.00997   0.00407  -0.0820   0.7094   1.0000
   1.000   0.5279   0.01004   0.00403  -0.0817   0.6986   1.0000
   1.250   0.5551   0.01012   0.00403  -0.0814   0.6872   1.0000
   1.500   0.5823   0.01021   0.00402  -0.0810   0.6764   1.0000
   1.750   0.6096   0.01030   0.00398  -0.0806   0.6660   1.0000
   2.000   0.6366   0.01040   0.00403  -0.0803   0.6536   1.0000
   2.250   0.6637   0.01051   0.00408  -0.0800   0.6415   1.0000
   2.500   0.6908   0.01063   0.00412  -0.0797   0.6296   1.0000
   2.750   0.7178   0.01076   0.00416  -0.0793   0.6178   1.0000
   3.000   0.7448   0.01089   0.00422  -0.0790   0.6053   1.0000
   3.250   0.7715   0.01103   0.00433  -0.0787   0.5918   1.0000
   3.500   0.7982   0.01119   0.00444  -0.0783   0.5782   1.0000
   3.750   0.8248   0.01136   0.00456  -0.0780   0.5646   1.0000
   4.000   0.8513   0.01154   0.00471  -0.0776   0.5506   1.0000
   4.250   0.8776   0.01174   0.00486  -0.0773   0.5365   1.0000
   4.500   0.9038   0.01195   0.00502  -0.0769   0.5220   1.0000
   4.750   0.9298   0.01217   0.00522  -0.0765   0.5073   1.0000
   5.000   0.9556   0.01242   0.00542  -0.0761   0.4921   1.0000
   5.250   0.9812   0.01267   0.00565  -0.0757   0.4768   1.0000
   5.500   1.0066   0.01295   0.00589  -0.0752   0.4611   1.0000
   5.750   1.0317   0.01325   0.00617  -0.0747   0.4453   1.0000
   6.000   1.0565   0.01356   0.00646  -0.0742   0.4292   1.0000
   6.250   1.0811   0.01390   0.00676  -0.0737   0.4131   1.0000
   6.500   1.1053   0.01426   0.00711  -0.0731   0.3969   1.0000
   6.750   1.1291   0.01464   0.00746  -0.0725   0.3805   1.0000
   7.000   1.1526   0.01504   0.00784  -0.0719   0.3643   1.0000
   7.250   1.1757   0.01547   0.00825  -0.0712   0.3483   1.0000
   7.500   1.1983   0.01593   0.00868  -0.0705   0.3323   1.0000
   7.750   1.2203   0.01642   0.00914  -0.0697   0.3164   1.0000
   8.000   1.2421   0.01690   0.00963  -0.0689   0.3002   1.0000
   8.250   1.2633   0.01740   0.01016  -0.0681   0.2842   1.0000
   8.500   1.2838   0.01794   0.01071  -0.0671   0.2684   1.0000
   8.750   1.3037   0.01851   0.01129  -0.0661   0.2529   1.0000
   9.000   1.3227   0.01912   0.01191  -0.0650   0.2375   1.0000
   9.250   1.3408   0.01976   0.01258  -0.0638   0.2220   1.0000
   9.500   1.3577   0.02045   0.01328  -0.0625   0.2065   1.0000
   9.750   1.3731   0.02120   0.01403  -0.0610   0.1909   1.0000
  10.000   1.3867   0.02203   0.01486  -0.0592   0.1754   1.0000
  10.250   1.3973   0.02294   0.01576  -0.0571   0.1603   1.0000
  10.500   1.4047   0.02394   0.01675  -0.0547   0.1462   1.0000
  10.750   1.4107   0.02510   0.01789  -0.0522   0.1326   1.0000
  11.000   1.4157   0.02640   0.01919  -0.0500   0.1201   1.0000
  11.250   1.4199   0.02787   0.02067  -0.0479   0.1089   1.0000
  11.500   1.4226   0.02956   0.02235  -0.0459   0.0995   1.0000
  11.750   1.4228   0.03153   0.02427  -0.0440   0.0916   1.0000
  12.000   1.4279   0.03324   0.02611  -0.0426   0.0840   1.0000
  12.250   1.4266   0.03559   0.02842  -0.0411   0.0784   1.0000
  12.500   1.4310   0.03751   0.03048  -0.0400   0.0727   1.0000
  12.750   1.4290   0.04011   0.03304  -0.0389   0.0684   1.0000
  13.000   1.4320   0.04236   0.03545  -0.0380   0.0641   1.0000
  13.250   1.4334   0.04482   0.03799  -0.0374   0.0604   1.0000
  13.500   1.4311   0.04779   0.04088  -0.0366   0.0570   1.0000
  13.750   1.4335   0.05032   0.04364  -0.0363   0.0542   1.0000
  14.000   1.4344   0.05306   0.04650  -0.0361   0.0514   1.0000
  14.250   1.4339   0.05602   0.04949  -0.0360   0.0490   1.0000
  14.500   1.4348   0.05896   0.05246  -0.0355   0.0466   1.0000
  14.750   1.4341   0.06215   0.05587  -0.0358   0.0447   1.0000
  15.000   1.4336   0.06539   0.05924  -0.0361   0.0427   1.0000
  15.250   1.4338   0.06858   0.06249  -0.0365   0.0411   1.0000
  15.500   1.4369   0.07146   0.06534  -0.0361   0.0390   1.0000
  15.750   1.4338   0.07537   0.06946  -0.0368   0.0379   1.0000
  16.000   1.4295   0.07952   0.07382  -0.0380   0.0367   1.0000
  16.250   1.4246   0.08385   0.07833  -0.0394   0.0355   1.0000
  16.500   1.4207   0.08810   0.08272  -0.0408   0.0343   1.0000
  16.750   1.4181   0.09221   0.08695  -0.0422   0.0333   1.0000
  17.000   1.4181   0.09585   0.09062  -0.0431   0.0322   1.0000
  17.250   1.4124   0.10068   0.09558  -0.0442   0.0312   1.0000
  17.500   1.3998   0.10686   0.10201  -0.0474   0.0308   1.0000
  17.750   1.3863   0.11345   0.10884  -0.0510   0.0304   1.0000
  18.000   1.3722   0.12037   0.11599  -0.0549   0.0300   1.0000
  18.250   1.3565   0.12786   0.12371  -0.0594   0.0297   1.0000
  18.500   1.3392   0.13597   0.13203  -0.0644   0.0294   1.0000
  18.750   1.3189   0.14510   0.14138  -0.0704   0.0294   1.0000
  19.000   1.2937   0.15588   0.15238  -0.0777   0.0296   1.0000
  19.250   1.2606   0.16937   0.16607  -0.0870   0.0303   1.0000
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