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S1091 (s1091-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: S1091 (s1091-il)
Reynolds number: 500,000
Max Cl/Cd: 111.04 at α=2.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s1091-il-500000-n5.txt
Download as CSV file: xf-s1091-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S1091                                           
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3146   0.11242   0.11010  -0.0178   1.0000   0.0063
  -8.500  -0.3127   0.11032   0.10804  -0.0180   1.0000   0.0063
  -8.250  -0.3100   0.10809   0.10583  -0.0178   1.0000   0.0063
  -8.000  -0.3005   0.10528   0.10303  -0.0198   0.9992   0.0063
  -7.750  -0.2851   0.10193   0.09968  -0.0232   0.9973   0.0063
  -7.500  -0.2710   0.09758   0.09535  -0.0247   0.9960   0.0064
  -7.250  -0.2557   0.09429   0.09206  -0.0276   0.9940   0.0065
  -7.000  -0.2417   0.09122   0.08901  -0.0302   0.9911   0.0066
  -6.750  -0.2257   0.08810   0.08589  -0.0335   0.9878   0.0067
  -6.500  -0.2037   0.08451   0.08230  -0.0384   0.9853   0.0068
  -6.250  -0.1862   0.08129   0.07910  -0.0419   0.9805   0.0068
  -6.000  -0.1641   0.07787   0.07567  -0.0466   0.9763   0.0069
  -5.750  -0.1377   0.07424   0.07204  -0.0523   0.9735   0.0072
  -5.500  -0.1188   0.07120   0.06901  -0.0558   0.9667   0.0072
  -5.250  -0.0920   0.06770   0.06549  -0.0612   0.9620   0.0073
  -5.000  -0.0686   0.06449   0.06228  -0.0654   0.9546   0.0075
  -4.750  -0.0401   0.06101   0.05878  -0.0707   0.9477   0.0078
  -4.500  -0.0156   0.05786   0.05562  -0.0746   0.9370   0.0080
  -4.250   0.0171   0.05434   0.05206  -0.0803   0.9289   0.0083
  -4.000   0.0604   0.05027   0.04793  -0.0884   0.9216   0.0089
  -3.750   0.1135   0.04574   0.04331  -0.0986   0.9141   0.0092
  -3.500   0.1691   0.04122   0.03869  -0.1086   0.9074   0.0093
  -3.250   0.2254   0.03667   0.03399  -0.1183   0.8959   0.0093
  -3.000   0.2804   0.03225   0.02938  -0.1271   0.8785   0.0093
  -2.750   0.3074   0.01082   0.00762  -0.1225   0.7906   0.0093
  -2.500   0.3658   0.02331   0.01982  -0.1379   0.8285   0.0059
  -2.250   0.4024   0.01906   0.01512  -0.1405   0.8049   0.0057
  -2.000   0.4368   0.01420   0.00952  -0.1418   0.7858   0.0058
  -1.750   0.4659   0.01198   0.00661  -0.1416   0.7675   0.0063
  -1.500   0.4924   0.01096   0.00524  -0.1412   0.7508   0.0068
  -1.250   0.5184   0.01076   0.00489  -0.1406   0.7352   0.0080
  -1.000   0.5449   0.01036   0.00424  -0.1400   0.7207   0.0090
  -0.750   0.5714   0.00979   0.00347  -0.1394   0.7073   0.0090
  -0.500   0.5978   0.00937   0.00291  -0.1388   0.6946   0.0091
  -0.250   0.6242   0.00908   0.00251  -0.1382   0.6825   0.0093
   0.000   0.6505   0.00877   0.00211  -0.1377   0.6709   0.0099
   0.250   0.6768   0.00864   0.00188  -0.1371   0.6588   0.0115
   0.750   0.7288   0.00834   0.00166  -0.1360   0.6324   0.0932
   1.000   0.7545   0.00830   0.00169  -0.1354   0.6175   0.1483
   1.250   0.7799   0.00827   0.00175  -0.1348   0.6012   0.2204
   1.500   0.8052   0.00828   0.00181  -0.1342   0.5828   0.2800
   1.750   0.8301   0.00835   0.00188  -0.1335   0.5606   0.3316
   2.000   0.8548   0.00843   0.00198  -0.1327   0.5337   0.3970
   2.250   0.8784   0.00856   0.00211  -0.1318   0.4985   0.4759
   2.500   0.9001   0.00854   0.00224  -0.1307   0.4585   0.6381
   2.750   0.9283   0.00836   0.00238  -0.1307   0.4196   1.0000
   3.250   0.9756   0.00910   0.00271  -0.1290   0.3511   1.0000
   3.500   0.9992   0.00949   0.00291  -0.1282   0.3170   1.0000
   3.750   1.0233   0.00982   0.00312  -0.1274   0.2910   1.0000
   4.000   1.0475   0.01014   0.00331  -0.1267   0.2687   1.0000
   4.250   1.0714   0.01049   0.00353  -0.1259   0.2437   1.0000
   4.500   1.0948   0.01089   0.00378  -0.1251   0.2161   1.0000
   4.750   1.1181   0.01131   0.00405  -0.1243   0.1895   1.0000
   5.000   1.1415   0.01170   0.00435  -0.1234   0.1687   1.0000
   5.250   1.1649   0.01208   0.00465  -0.1226   0.1503   1.0000
   5.500   1.1882   0.01247   0.00495  -0.1218   0.1340   1.0000
   5.750   1.2114   0.01286   0.00527  -0.1210   0.1201   1.0000
   6.000   1.2347   0.01323   0.00560  -0.1202   0.1084   1.0000
   6.250   1.2579   0.01361   0.00596  -0.1193   0.0984   1.0000
   6.500   1.2807   0.01401   0.00632  -0.1184   0.0897   1.0000
   6.750   1.3036   0.01440   0.00670  -0.1176   0.0821   1.0000
   7.000   1.3263   0.01480   0.00709  -0.1167   0.0757   1.0000
   7.250   1.3488   0.01520   0.00750  -0.1158   0.0705   1.0000
   7.500   1.3708   0.01565   0.00796  -0.1148   0.0659   1.0000
   7.750   1.3933   0.01601   0.00838  -0.1139   0.0634   1.0000
   8.000   1.4153   0.01642   0.00883  -0.1129   0.0607   1.0000
   8.250   1.4367   0.01689   0.00934  -0.1118   0.0582   1.0000
   8.500   1.4572   0.01742   0.00990  -0.1106   0.0556   1.0000
   8.750   1.4776   0.01793   0.01048  -0.1094   0.0541   1.0000
   9.000   1.4984   0.01838   0.01102  -0.1082   0.0530   1.0000
   9.250   1.5185   0.01887   0.01162  -0.1069   0.0519   1.0000
   9.500   1.5382   0.01938   0.01222  -0.1056   0.0504   1.0000
   9.750   1.5573   0.01992   0.01281  -0.1043   0.0486   1.0000
  10.000   1.5755   0.02050   0.01344  -0.1028   0.0464   1.0000
  10.250   1.5923   0.02117   0.01415  -0.1011   0.0433   1.0000
  10.500   1.6122   0.02153   0.01461  -0.1000   0.0413   1.0000
  10.750   1.6299   0.02200   0.01514  -0.0985   0.0381   1.0000
  11.000   1.6444   0.02265   0.01578  -0.0965   0.0339   1.0000
  11.250   1.6600   0.02317   0.01638  -0.0946   0.0307   1.0000
  11.500   1.6727   0.02391   0.01712  -0.0924   0.0257   1.0000
  11.750   1.6816   0.02492   0.01810  -0.0898   0.0174   1.0000
  12.000   1.6836   0.02649   0.01963  -0.0863   0.0096   1.0000
  12.250   1.6856   0.02808   0.02129  -0.0829   0.0052   1.0000
  12.500   1.6861   0.02985   0.02316  -0.0797   0.0024   1.0000
  12.750   1.6883   0.03153   0.02496  -0.0768   0.0016   1.0000
  13.000   1.6911   0.03322   0.02680  -0.0743   0.0013   1.0000
  13.250   1.6935   0.03500   0.02876  -0.0720   0.0011   1.0000
  13.500   1.6944   0.03701   0.03093  -0.0699   0.0010   1.0000
  13.750   1.6946   0.03920   0.03328  -0.0680   0.0009   1.0000
  14.000   1.6921   0.04179   0.03605  -0.0664   0.0009   1.0000
  14.250   1.6879   0.04472   0.03916  -0.0650   0.0008   1.0000
  14.500   1.6827   0.04795   0.04257  -0.0641   0.0008   1.0000
  14.750   1.6734   0.05191   0.04673  -0.0637   0.0007   1.0000
  15.000   1.6647   0.05602   0.05102  -0.0637   0.0007   1.0000
  15.250   1.6558   0.06039   0.05557  -0.0642   0.0007   1.0000
  15.500   1.6447   0.06536   0.06071  -0.0653   0.0007   1.0000
  15.750   1.6321   0.07082   0.06636  -0.0668   0.0007   1.0000
  16.000   1.6164   0.07721   0.07293  -0.0691   0.0007   1.0000
  16.250   1.5998   0.08413   0.08004  -0.0721   0.0007   1.0000
  16.500   1.5809   0.09197   0.08807  -0.0758   0.0006   1.0000
  16.750   1.5583   0.10103   0.09732  -0.0804   0.0007   1.0000
  17.000   1.5342   0.11084   0.10732  -0.0857   0.0007   1.0000
  17.250   1.5082   0.12144   0.11810  -0.0915   0.0007   1.0000
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