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S2091-101-83 (s2091-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: S2091-101-83 (s2091-il)
Reynolds number: 200,000
Max Cl/Cd: 76.35 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s2091-il-200000-n5.txt
Download as CSV file: xf-s2091-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3328   0.08790   0.08447  -0.0335   1.0000   0.0167
  -8.500  -0.3334   0.08382   0.08045  -0.0355   1.0000   0.0166
  -8.250  -0.3359   0.07990   0.07660  -0.0373   1.0000   0.0167
  -8.000  -0.3381   0.07571   0.07248  -0.0399   0.9925   0.0165
  -7.750  -0.3264   0.06913   0.06591  -0.0489   0.9645   0.0167
  -7.500  -0.3136   0.06069   0.05742  -0.0615   0.9444   0.0171
  -7.250  -0.3110   0.04723   0.04372  -0.0769   0.9219   0.0173
  -7.000  -0.3243   0.02832   0.02329  -0.0870   0.9029   0.0180
  -6.750  -0.3069   0.02396   0.01804  -0.0874   0.8931   0.0188
  -6.500  -0.2841   0.02263   0.01654  -0.0871   0.8845   0.0194
  -6.250  -0.2602   0.02141   0.01509  -0.0868   0.8757   0.0203
  -6.000  -0.2360   0.02013   0.01350  -0.0863   0.8680   0.0216
  -5.750  -0.2108   0.01892   0.01197  -0.0860   0.8592   0.0235
  -5.500  -0.1857   0.01829   0.01125  -0.0856   0.8519   0.0250
  -5.250  -0.1597   0.01742   0.01021  -0.0853   0.8431   0.0266
  -5.000  -0.1339   0.01660   0.00915  -0.0847   0.8360   0.0286
  -4.750  -0.1075   0.01608   0.00861  -0.0845   0.8271   0.0309
  -4.500  -0.0813   0.01550   0.00787  -0.0840   0.8200   0.0333
  -4.250  -0.0545   0.01490   0.00719  -0.0838   0.8112   0.0360
  -4.000  -0.0279   0.01450   0.00672  -0.0834   0.8039   0.0392
  -3.750  -0.0008   0.01404   0.00614  -0.0831   0.7950   0.0423
  -3.500   0.0260   0.01362   0.00570  -0.0828   0.7875   0.0470
  -3.250   0.0533   0.01327   0.00527  -0.0825   0.7787   0.0527
  -3.000   0.0805   0.01291   0.00488  -0.0823   0.7709   0.0600
  -2.750   0.1078   0.01262   0.00456  -0.0821   0.7621   0.0698
  -2.500   0.1353   0.01237   0.00428  -0.0818   0.7539   0.0810
  -2.250   0.1627   0.01214   0.00403  -0.0816   0.7452   0.0952
  -2.000   0.1902   0.01192   0.00383  -0.0815   0.7365   0.1149
  -1.750   0.2176   0.01168   0.00363  -0.0813   0.7279   0.1416
  -1.500   0.2451   0.01143   0.00348  -0.0812   0.7185   0.1807
  -1.250   0.2722   0.01116   0.00334  -0.0810   0.7099   0.2380
  -1.000   0.2992   0.01086   0.00326  -0.0809   0.7001   0.3174
  -0.750   0.3260   0.01057   0.00321  -0.0807   0.6907   0.4065
  -0.500   0.3520   0.01028   0.00317  -0.0803   0.6813   0.5075
  -0.250   0.3771   0.00997   0.00319  -0.0795   0.6711   0.6177
   0.000   0.3994   0.00960   0.00319  -0.0778   0.6616   0.7490
   0.250   0.4367   0.00919   0.00305  -0.0788   0.6510   1.0000
   0.500   0.4642   0.00928   0.00301  -0.0787   0.6400   1.0000
   0.750   0.4917   0.00937   0.00298  -0.0785   0.6293   1.0000
   1.000   0.5190   0.00948   0.00296  -0.0782   0.6185   1.0000
   1.250   0.5464   0.00959   0.00297  -0.0780   0.6066   1.0000
   1.500   0.5738   0.00971   0.00300  -0.0778   0.5949   1.0000
   1.750   0.6010   0.00984   0.00303  -0.0776   0.5832   1.0000
   2.000   0.6282   0.00998   0.00307  -0.0774   0.5715   1.0000
   2.250   0.6553   0.01013   0.00314  -0.0771   0.5590   1.0000
   2.500   0.6824   0.01028   0.00322  -0.0769   0.5462   1.0000
   2.750   0.7093   0.01044   0.00331  -0.0767   0.5334   1.0000
   3.000   0.7362   0.01062   0.00343  -0.0765   0.5205   1.0000
   3.250   0.7629   0.01081   0.00355  -0.0762   0.5075   1.0000
   3.500   0.7894   0.01101   0.00368  -0.0759   0.4940   1.0000
   3.750   0.8158   0.01122   0.00384  -0.0756   0.4804   1.0000
   4.000   0.8421   0.01144   0.00401  -0.0753   0.4664   1.0000
   4.250   0.8683   0.01167   0.00419  -0.0751   0.4523   1.0000
   4.500   0.8943   0.01192   0.00441  -0.0747   0.4381   1.0000
   4.750   0.9201   0.01218   0.00463  -0.0744   0.4239   1.0000
   5.000   0.9458   0.01245   0.00486  -0.0741   0.4095   1.0000
   5.250   0.9712   0.01275   0.00512  -0.0737   0.3951   1.0000
   5.500   0.9964   0.01305   0.00541  -0.0733   0.3806   1.0000
   5.750   1.0213   0.01338   0.00570  -0.0729   0.3660   1.0000
   6.000   1.0459   0.01372   0.00602  -0.0724   0.3513   1.0000
   6.250   1.0703   0.01408   0.00636  -0.0720   0.3366   1.0000
   6.500   1.0944   0.01446   0.00672  -0.0715   0.3219   1.0000
   6.750   1.1181   0.01486   0.00710  -0.0709   0.3072   1.0000
   7.000   1.1414   0.01528   0.00751  -0.0703   0.2925   1.0000
   7.250   1.1644   0.01573   0.00795  -0.0697   0.2779   1.0000
   7.500   1.1869   0.01619   0.00840  -0.0691   0.2633   1.0000
   7.750   1.2089   0.01669   0.00888  -0.0683   0.2487   1.0000
   8.000   1.2304   0.01721   0.00941  -0.0676   0.2340   1.0000
   8.250   1.2513   0.01776   0.00994  -0.0667   0.2195   1.0000
   8.500   1.2716   0.01833   0.01052  -0.0658   0.2051   1.0000
   8.750   1.2912   0.01894   0.01112  -0.0648   0.1910   1.0000
   9.000   1.3100   0.01958   0.01177  -0.0638   0.1775   1.0000
   9.250   1.3278   0.02027   0.01246  -0.0626   0.1639   1.0000
   9.500   1.3445   0.02100   0.01319  -0.0613   0.1508   1.0000
   9.750   1.3597   0.02179   0.01397  -0.0598   0.1376   1.0000
  10.000   1.3728   0.02263   0.01482  -0.0581   0.1253   1.0000
  10.250   1.3830   0.02354   0.01572  -0.0560   0.1138   1.0000
  10.500   1.3924   0.02453   0.01672  -0.0539   0.1030   1.0000
  10.750   1.4015   0.02558   0.01780  -0.0520   0.0934   1.0000
  11.000   1.4095   0.02677   0.01901  -0.0501   0.0850   1.0000
  11.250   1.4155   0.02815   0.02040  -0.0483   0.0775   1.0000
  11.500   1.4231   0.02949   0.02183  -0.0468   0.0708   1.0000
  11.750   1.4281   0.03109   0.02347  -0.0453   0.0652   1.0000
  12.000   1.4337   0.03272   0.02516  -0.0440   0.0598   1.0000
  12.250   1.4364   0.03467   0.02716  -0.0427   0.0557   1.0000
  12.500   1.4416   0.03649   0.02910  -0.0417   0.0519   1.0000
  12.750   1.4434   0.03869   0.03136  -0.0408   0.0483   1.0000
  13.000   1.4442   0.04111   0.03386  -0.0401   0.0458   1.0000
  13.250   1.4469   0.04341   0.03631  -0.0396   0.0432   1.0000
  13.500   1.4470   0.04607   0.03907  -0.0392   0.0408   1.0000
  13.750   1.4439   0.04921   0.04228  -0.0391   0.0389   1.0000
  14.000   1.4424   0.05228   0.04548  -0.0392   0.0372   1.0000
  14.250   1.4413   0.05540   0.04875  -0.0394   0.0355   1.0000
  14.500   1.4387   0.05883   0.05231  -0.0398   0.0340   1.0000
  14.750   1.4342   0.06264   0.05623  -0.0406   0.0328   1.0000
  15.000   1.4273   0.06695   0.06063  -0.0416   0.0316   1.0000
  15.250   1.4207   0.07135   0.06514  -0.0429   0.0306   1.0000
  15.500   1.4173   0.07543   0.06938  -0.0440   0.0295   1.0000
  15.750   1.4124   0.07983   0.07394  -0.0455   0.0284   1.0000
  16.000   1.4068   0.08450   0.07874  -0.0471   0.0274   1.0000
  16.250   1.4001   0.08947   0.08384  -0.0491   0.0266   1.0000
  16.500   1.3923   0.09468   0.08916  -0.0512   0.0259   1.0000
  16.750   1.3835   0.10016   0.09474  -0.0535   0.0253   1.0000
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