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FX 60-100 (126) AIRFOIL (fx601001-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: FX 60-100 (126) AIRFOIL (fx601001-il)
Reynolds number: 100,000
Max Cl/Cd: 62.5 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx601001-il-100000-n5.txt
Download as CSV file: xf-fx601001-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 60-100 (126) AIRFOIL                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3899   0.08981   0.08491  -0.0417   1.0000   0.0221
  -9.000  -0.3918   0.08605   0.08123  -0.0425   1.0000   0.0219
  -8.750  -0.3960   0.08207   0.07732  -0.0435   1.0000   0.0218
  -8.500  -0.4021   0.07815   0.07349  -0.0443   1.0000   0.0216
  -8.250  -0.4116   0.07418   0.06963  -0.0449   1.0000   0.0215
  -8.000  -0.4255   0.07030   0.06586  -0.0449   1.0000   0.0213
  -7.750  -0.4400   0.06541   0.06106  -0.0465   1.0000   0.0211
  -7.500  -0.4544   0.05954   0.05522  -0.0511   1.0000   0.0209
  -7.250  -0.4622   0.05347   0.04902  -0.0576   1.0000   0.0207
  -7.000  -0.4624   0.04767   0.04294  -0.0627   1.0000   0.0205
  -6.750  -0.4502   0.04173   0.03652  -0.0681   0.9994   0.0205
  -6.500  -0.4114   0.03501   0.02897  -0.0768   0.9943   0.0207
  -6.250  -0.3727   0.03024   0.02341  -0.0821   0.9897   0.0213
  -6.000  -0.3345   0.02707   0.01971  -0.0859   0.9857   0.0228
  -5.750  -0.2990   0.02535   0.01771  -0.0886   0.9804   0.0252
  -5.500  -0.2615   0.02337   0.01543  -0.0910   0.9768   0.0273
  -5.250  -0.2281   0.02175   0.01356  -0.0924   0.9712   0.0299
  -5.000  -0.1910   0.02070   0.01246  -0.0947   0.9668   0.0354
  -4.750  -0.1567   0.01964   0.01131  -0.0964   0.9611   0.0440
  -4.500  -0.1198   0.01865   0.01019  -0.0986   0.9560   0.0631
  -4.250  -0.0814   0.01780   0.00934  -0.1014   0.9519   0.0912
  -4.000  -0.0479   0.01705   0.00868  -0.1031   0.9449   0.1211
  -3.750  -0.0085   0.01612   0.00797  -0.1062   0.9405   0.1807
  -3.500   0.0269   0.01529   0.00751  -0.1084   0.9345   0.2947
  -3.250   0.0603   0.01519   0.00777  -0.1094   0.9278   0.4023
  -3.000   0.0941   0.01532   0.00773  -0.1103   0.9208   0.4488
  -2.750   0.1278   0.01545   0.00766  -0.1112   0.9134   0.4799
  -2.500   0.1588   0.01563   0.00777  -0.1114   0.9053   0.5113
  -2.250   0.1912   0.01568   0.00775  -0.1119   0.8981   0.5362
  -2.000   0.2212   0.01564   0.00762  -0.1121   0.8893   0.5502
  -1.750   0.2548   0.01550   0.00741  -0.1129   0.8825   0.5595
  -1.500   0.2842   0.01541   0.00724  -0.1130   0.8726   0.5673
  -1.250   0.3157   0.01530   0.00704  -0.1135   0.8641   0.5750
  -1.000   0.3472   0.01518   0.00686  -0.1140   0.8556   0.5820
  -0.750   0.3765   0.01513   0.00677  -0.1140   0.8453   0.5912
  -0.500   0.4062   0.01506   0.00668  -0.1141   0.8358   0.6000
  -0.250   0.4373   0.01498   0.00655  -0.1145   0.8267   0.6085
   0.000   0.4655   0.01494   0.00650  -0.1143   0.8153   0.6136
   0.250   0.4948   0.01490   0.00643  -0.1144   0.8043   0.6188
   0.500   0.5241   0.01485   0.00634  -0.1145   0.7925   0.6238
   0.750   0.5523   0.01479   0.00627  -0.1142   0.7786   0.6284
   1.000   0.5805   0.01475   0.00620  -0.1139   0.7639   0.6336
   1.250   0.6085   0.01475   0.00617  -0.1137   0.7499   0.6388
   1.500   0.6365   0.01475   0.00619  -0.1135   0.7372   0.6438
   1.750   0.6646   0.01479   0.00621  -0.1133   0.7243   0.6495
   2.000   0.6919   0.01483   0.00628  -0.1130   0.7107   0.6552
   2.500   0.7461   0.01493   0.00642  -0.1122   0.6799   0.6684
   2.750   0.7723   0.01499   0.00650  -0.1116   0.6609   0.6756
   3.000   0.7987   0.01507   0.00660  -0.1110   0.6427   0.6841
   3.250   0.8251   0.01518   0.00676  -0.1105   0.6264   0.6942
   3.500   0.8513   0.01529   0.00695  -0.1100   0.6108   0.7052
   3.750   0.8772   0.01542   0.00714  -0.1094   0.5949   0.7185
   4.000   0.9025   0.01554   0.00740  -0.1088   0.5777   0.7362
   4.250   0.9269   0.01565   0.00765  -0.1079   0.5599   0.7607
   4.500   0.9495   0.01569   0.00789  -0.1066   0.5419   0.8018
   4.750   0.9711   0.01567   0.00807  -0.1050   0.5223   1.0000
   5.000   0.9969   0.01600   0.00842  -0.1046   0.4984   1.0000
   5.250   1.0219   0.01635   0.00883  -0.1041   0.4718   1.0000
   5.500   1.0462   0.01675   0.00923  -0.1034   0.4419   1.0000
   5.750   1.0689   0.01725   0.00963  -0.1025   0.4064   1.0000
   6.000   1.0904   0.01788   0.01012  -0.1014   0.3692   1.0000
   6.250   1.1115   0.01860   0.01073  -0.1004   0.3374   1.0000
   6.500   1.1323   0.01938   0.01142  -0.0994   0.3078   1.0000
   6.750   1.1512   0.02026   0.01223  -0.0981   0.2689   1.0000
   7.000   1.1691   0.02121   0.01300  -0.0969   0.2266   1.0000
   7.250   1.1865   0.02224   0.01383  -0.0957   0.1869   1.0000
   7.500   1.2028   0.02343   0.01479  -0.0943   0.1395   1.0000
   7.750   1.2147   0.02516   0.01606  -0.0926   0.0750   1.0000
   8.000   1.2247   0.02722   0.01782  -0.0905   0.0406   1.0000
   8.250   1.2368   0.02895   0.01956  -0.0885   0.0308   1.0000
   8.500   1.2484   0.03058   0.02126  -0.0865   0.0262   1.0000
   8.750   1.2598   0.03210   0.02296  -0.0844   0.0233   1.0000
   9.000   1.2675   0.03374   0.02478  -0.0820   0.0217   1.0000
   9.250   1.2715   0.03553   0.02673  -0.0792   0.0205   1.0000
   9.500   1.2721   0.03764   0.02897  -0.0763   0.0196   1.0000
   9.750   1.2705   0.04012   0.03156  -0.0736   0.0187   1.0000
  10.000   1.2764   0.04210   0.03373  -0.0717   0.0180   1.0000
  10.250   1.2820   0.04423   0.03607  -0.0699   0.0172   1.0000
  10.500   1.2872   0.04657   0.03860  -0.0683   0.0164   1.0000
  10.750   1.2924   0.04916   0.04149  -0.0667   0.0159   1.0000
  11.000   1.2976   0.05194   0.04449  -0.0654   0.0155   1.0000
  11.250   1.3017   0.05495   0.04773  -0.0641   0.0152   1.0000
  11.500   1.3039   0.05822   0.05126  -0.0631   0.0149   1.0000
  11.750   1.3034   0.06181   0.05512  -0.0622   0.0147   1.0000
  12.000   1.2999   0.06575   0.05934  -0.0617   0.0145   1.0000
  12.250   1.2936   0.07007   0.06393  -0.0617   0.0144   1.0000
  12.500   1.2845   0.07480   0.06894  -0.0622   0.0143   1.0000
  12.750   1.2730   0.08000   0.07441  -0.0633   0.0142   1.0000
  13.000   1.2594   0.08571   0.08038  -0.0652   0.0141   1.0000
  13.250   1.2440   0.09202   0.08695  -0.0678   0.0142   1.0000
  13.500   1.2270   0.09899   0.09417  -0.0713   0.0142   1.0000
  13.750   1.2084   0.10678   0.10219  -0.0757   0.0143   1.0000
  14.000   1.1888   0.11550   0.11113  -0.0811   0.0144   1.0000
  14.250   1.1682   0.12528   0.12112  -0.0876   0.0147   1.0000
  14.500   1.1463   0.13647   0.13248  -0.0953   0.0150   1.0000
  14.750   1.1233   0.14928   0.14541  -0.1039   0.0153   1.0000
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