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S2091-101-83 (s2091-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: S2091-101-83 (s2091-il)
Reynolds number: 50,000
Max Cl/Cd: 38.19 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s2091-il-50000-n5.txt
Download as CSV file: xf-s2091-il-50000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3383   0.11811   0.11114  -0.0259   1.0000   0.1029
  -9.500  -0.3444   0.11634   0.10948  -0.0290   1.0000   0.1041
  -9.250  -0.3485   0.11402   0.10726  -0.0318   1.0000   0.1045
  -9.000  -0.3226   0.10796   0.10117  -0.0290   1.0000   0.1077
  -8.750  -0.3167   0.10472   0.09798  -0.0297   1.0000   0.1088
  -8.500  -0.3146   0.10159   0.09494  -0.0310   1.0000   0.1085
  -8.250  -0.3303   0.09451   0.08791  -0.0380   1.0000   0.0631
  -8.000  -0.3205   0.09134   0.08479  -0.0368   1.0000   0.0614
  -7.750  -0.3213   0.08840   0.08196  -0.0367   1.0000   0.0601
  -7.500  -0.3279   0.08584   0.07954  -0.0363   1.0000   0.0589
  -7.250  -0.3375   0.08339   0.07723  -0.0359   1.0000   0.0578
  -7.000  -0.3491   0.08082   0.07479  -0.0357   1.0000   0.0568
  -6.750  -0.3613   0.07818   0.07225  -0.0356   1.0000   0.0560
  -6.500  -0.3723   0.07503   0.06916  -0.0362   1.0000   0.0551
  -6.250  -0.3803   0.07118   0.06532  -0.0378   1.0000   0.0543
  -6.000  -0.3612   0.06626   0.06030  -0.0437   0.9925   0.0553
  -5.750  -0.3334   0.06050   0.05433  -0.0514   0.9829   0.0568
  -5.500  -0.3048   0.05423   0.04771  -0.0590   0.9734   0.0574
  -5.250  -0.2753   0.04828   0.04128  -0.0653   0.9642   0.0577
  -5.000  -0.2405   0.04308   0.03542  -0.0710   0.9567   0.0605
  -4.750  -0.2074   0.03845   0.02984  -0.0749   0.9481   0.0635
  -4.500  -0.1734   0.03579   0.02694  -0.0775   0.9413   0.0661
  -4.250  -0.1406   0.03384   0.02463  -0.0794   0.9330   0.0716
  -4.000  -0.1022   0.03128   0.02132  -0.0818   0.9266   0.0766
  -3.750  -0.0704   0.02992   0.01988  -0.0831   0.9182   0.0829
  -3.500  -0.0332   0.02838   0.01791  -0.0847   0.9115   0.0914
  -3.250  -0.0024   0.02738   0.01677  -0.0853   0.9026   0.1018
  -3.000   0.0312   0.02640   0.01568  -0.0863   0.8949   0.1150
  -2.750   0.0630   0.02561   0.01475  -0.0869   0.8862   0.1325
  -2.500   0.0938   0.02491   0.01402  -0.0874   0.8774   0.1539
  -2.250   0.1268   0.02420   0.01333  -0.0882   0.8693   0.1846
  -2.000   0.1548   0.02360   0.01285  -0.0883   0.8594   0.2279
  -1.750   0.1877   0.02273   0.01241  -0.0892   0.8521   0.3161
  -1.500   0.2097   0.02202   0.01236  -0.0881   0.8413   0.4678
  -1.250   0.2300   0.02122   0.01231  -0.0853   0.8328   0.6770
  -1.000   0.2747   0.02058   0.01189  -0.0870   0.8241   1.0000
  -0.750   0.3024   0.02076   0.01172  -0.0869   0.8137   1.0000
  -0.500   0.3340   0.02083   0.01148  -0.0872   0.8052   1.0000
  -0.250   0.3588   0.02107   0.01148  -0.0867   0.7935   1.0000
   0.000   0.3859   0.02125   0.01144  -0.0864   0.7831   1.0000
   0.250   0.4158   0.02133   0.01130  -0.0863   0.7742   1.0000
   0.500   0.4403   0.02159   0.01139  -0.0856   0.7623   1.0000
   0.750   0.4668   0.02178   0.01142  -0.0851   0.7515   1.0000
   1.000   0.4963   0.02182   0.01131  -0.0848   0.7426   1.0000
   1.250   0.5206   0.02209   0.01147  -0.0841   0.7303   1.0000
   1.500   0.5461   0.02231   0.01159  -0.0835   0.7189   1.0000
   1.750   0.5740   0.02241   0.01158  -0.0830   0.7089   1.0000
   2.000   0.6003   0.02257   0.01166  -0.0823   0.6976   1.0000
   2.250   0.6249   0.02283   0.01187  -0.0816   0.6853   1.0000
   2.500   0.6506   0.02303   0.01202  -0.0809   0.6735   1.0000
   2.750   0.6781   0.02312   0.01204  -0.0803   0.6629   1.0000
   3.000   0.7041   0.02329   0.01217  -0.0796   0.6510   1.0000
   3.250   0.7286   0.02356   0.01243  -0.0788   0.6379   1.0000
   3.500   0.7536   0.02380   0.01267  -0.0780   0.6252   1.0000
   3.750   0.7791   0.02401   0.01286  -0.0773   0.6126   1.0000
   4.000   0.8053   0.02417   0.01302  -0.0765   0.6005   1.0000
   4.250   0.8320   0.02430   0.01313  -0.0758   0.5884   1.0000
   4.500   0.8560   0.02461   0.01346  -0.0750   0.5744   1.0000
   4.750   0.8802   0.02493   0.01381  -0.0742   0.5604   1.0000
   5.000   0.9044   0.02525   0.01418  -0.0733   0.5464   1.0000
   5.250   0.9285   0.02558   0.01455  -0.0725   0.5323   1.0000
   5.500   0.9525   0.02592   0.01493  -0.0716   0.5181   1.0000
   5.750   0.9763   0.02629   0.01535  -0.0708   0.5037   1.0000
   6.000   0.9999   0.02668   0.01579  -0.0699   0.4892   1.0000
   6.250   1.0232   0.02710   0.01625  -0.0690   0.4746   1.0000
   6.500   1.0461   0.02755   0.01678  -0.0680   0.4599   1.0000
   6.750   1.0686   0.02804   0.01732  -0.0671   0.4451   1.0000
   7.000   1.0907   0.02856   0.01791  -0.0661   0.4302   1.0000
   7.250   1.1122   0.02913   0.01854  -0.0651   0.4153   1.0000
   7.500   1.1332   0.02974   0.01924  -0.0640   0.4002   1.0000
   7.750   1.1535   0.03039   0.01997  -0.0629   0.3852   1.0000
   8.000   1.1731   0.03109   0.02075  -0.0618   0.3702   1.0000
   8.250   1.1918   0.03184   0.02157  -0.0606   0.3551   1.0000
   8.500   1.2097   0.03263   0.02247  -0.0593   0.3401   1.0000
   8.750   1.2264   0.03348   0.02341  -0.0579   0.3251   1.0000
   9.000   1.2420   0.03439   0.02440  -0.0565   0.3102   1.0000
   9.250   1.2562   0.03536   0.02546  -0.0549   0.2953   1.0000
   9.500   1.2689   0.03640   0.02661  -0.0533   0.2807   1.0000
   9.750   1.2800   0.03752   0.02781  -0.0515   0.2664   1.0000
  10.000   1.2892   0.03872   0.02908  -0.0497   0.2525   1.0000
  10.250   1.2958   0.03998   0.03038  -0.0476   0.2393   1.0000
  10.500   1.3001   0.04142   0.03191  -0.0455   0.2266   1.0000
  10.750   1.3017   0.04316   0.03377  -0.0435   0.2141   1.0000
  11.000   1.3030   0.04506   0.03581  -0.0418   0.2022   1.0000
  11.250   1.3037   0.04709   0.03792  -0.0403   0.1909   1.0000
  11.500   1.3049   0.04917   0.04004  -0.0390   0.1803   1.0000
  11.750   1.3046   0.05152   0.04246  -0.0379   0.1700   1.0000
  12.000   1.3014   0.05437   0.04547  -0.0372   0.1601   1.0000
  12.250   1.3006   0.05709   0.04825  -0.0366   0.1514   1.0000
  12.500   1.2989   0.05995   0.05118  -0.0362   0.1428   1.0000
  12.750   1.2940   0.06350   0.05491  -0.0361   0.1351   1.0000
  13.000   1.2952   0.06616   0.05754  -0.0359   0.1279   1.0000
  13.250   1.2864   0.07062   0.06229  -0.0365   0.1217   1.0000
  13.500   1.2869   0.07356   0.06520  -0.0365   0.1154   1.0000
  13.750   1.2760   0.07862   0.07053  -0.0378   0.1104   1.0000
  14.000   1.2695   0.08300   0.07506  -0.0388   0.1055   1.0000
  14.250   1.2685   0.08654   0.07861  -0.0394   0.1009   1.0000
  14.500   1.2508   0.09335   0.08575  -0.0420   0.0978   1.0000
  14.750   1.2356   0.09994   0.09255  -0.0448   0.0948   1.0000
  15.000   1.2474   0.10112   0.09359  -0.0442   0.0896   1.0000
  15.250   1.2207   0.11053   0.10332  -0.0490   0.0884   1.0000
  15.500   1.1858   0.12252   0.11558  -0.0558   0.0878   1.0000
  15.750   1.1318   0.14082   0.13399  -0.0668   0.0879   1.0000
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