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GOE 550 AIRFOIL (goe550-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 550 AIRFOIL (goe550-il)
Reynolds number: 100,000
Max Cl/Cd: 56.28 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe550-il-100000-n5.txt
Download as CSV file: xf-goe550-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 550 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.6814   0.05083   0.04553  -0.0728   1.0000   0.0660
 -10.000  -0.7196   0.04381   0.03815  -0.0757   1.0000   0.0662
  -9.750  -0.7226   0.03876   0.03252  -0.0788   0.9971   0.0679
  -9.500  -0.6923   0.03758   0.03137  -0.0811   0.9921   0.0700
  -9.250  -0.6631   0.03597   0.02962  -0.0838   0.9862   0.0724
  -9.000  -0.6357   0.03370   0.02702  -0.0867   0.9800   0.0751
  -8.750  -0.6078   0.03127   0.02410  -0.0896   0.9737   0.0787
  -8.500  -0.5783   0.03042   0.02328  -0.0909   0.9675   0.0813
  -8.250  -0.5477   0.02926   0.02196  -0.0927   0.9616   0.0849
  -8.000  -0.5186   0.02780   0.02016  -0.0943   0.9552   0.0889
  -7.750  -0.4885   0.02682   0.01910  -0.0956   0.9487   0.0929
  -7.500  -0.4543   0.02594   0.01809  -0.0976   0.9440   0.0983
  -7.250  -0.4278   0.02488   0.01676  -0.0980   0.9357   0.1037
  -7.000  -0.3932   0.02419   0.01608  -0.0999   0.9310   0.1096
  -6.750  -0.3651   0.02338   0.01503  -0.1004   0.9232   0.1168
  -6.500  -0.3322   0.02282   0.01450  -0.1017   0.9175   0.1236
  -6.250  -0.2948   0.02211   0.01363  -0.1038   0.9139   0.1327
  -6.000  -0.2690   0.02184   0.01337  -0.1036   0.9048   0.1398
  -5.750  -0.2331   0.02137   0.01279  -0.1052   0.9002   0.1487
  -5.500  -0.2016   0.02108   0.01240  -0.1060   0.8936   0.1577
  -5.250  -0.1702   0.02088   0.01217  -0.1066   0.8868   0.1657
  -5.000  -0.1334   0.02053   0.01166  -0.1083   0.8824   0.1759
  -4.750  -0.1062   0.02047   0.01157  -0.1081   0.8737   0.1843
  -4.500  -0.0719   0.02025   0.01126  -0.1092   0.8681   0.1937
  -4.250  -0.0404   0.02003   0.01088  -0.1098   0.8612   0.2038
  -4.000  -0.0100   0.01984   0.01070  -0.1102   0.8538   0.2106
  -3.750   0.0264   0.01953   0.01016  -0.1117   0.8489   0.2208
  -3.500   0.0520   0.01941   0.01009  -0.1111   0.8395   0.2269
  -3.250   0.0865   0.01914   0.00966  -0.1122   0.8336   0.2357
  -3.000   0.1137   0.01896   0.00945  -0.1119   0.8249   0.2417
  -2.750   0.1460   0.01876   0.00918  -0.1126   0.8180   0.2494
  -2.500   0.1746   0.01860   0.00893  -0.1126   0.8098   0.2567
  -2.250   0.2049   0.01843   0.00874  -0.1128   0.8021   0.2636
  -2.000   0.2341   0.01829   0.00845  -0.1129   0.7939   0.2709
  -1.750   0.2629   0.01810   0.00831  -0.1129   0.7856   0.2767
  -1.500   0.2915   0.01799   0.00813  -0.1128   0.7772   0.2845
  -1.250   0.3199   0.01785   0.00798  -0.1127   0.7684   0.2920
  -1.000   0.3472   0.01775   0.00786  -0.1124   0.7591   0.3002
  -0.750   0.3766   0.01757   0.00763  -0.1124   0.7495   0.3072
  -0.500   0.4018   0.01745   0.00753  -0.1117   0.7380   0.3136
  -0.250   0.4300   0.01733   0.00733  -0.1114   0.7278   0.3205
   0.000   0.4568   0.01717   0.00722  -0.1109   0.7173   0.3260
   0.250   0.4827   0.01710   0.00715  -0.1103   0.7070   0.3328
   0.500   0.5115   0.01698   0.00702  -0.1102   0.6983   0.3404
   0.750   0.5362   0.01694   0.00704  -0.1095   0.6874   0.3485
   1.000   0.5633   0.01687   0.00700  -0.1091   0.6784   0.3572
   1.250   0.5891   0.01684   0.00700  -0.1084   0.6682   0.3671
   1.500   0.6150   0.01682   0.00705  -0.1079   0.6581   0.3789
   1.750   0.6429   0.01677   0.00704  -0.1076   0.6489   0.3958
   2.000   0.6674   0.01678   0.00717  -0.1069   0.6379   0.4187
   2.250   0.6938   0.01674   0.00724  -0.1064   0.6283   0.4535
   2.500   0.7193   0.01666   0.00732  -0.1057   0.6181   0.5036
   2.750   0.7417   0.01640   0.00749  -0.1045   0.6077   0.6030
   3.000   0.7805   0.01583   0.00752  -0.1060   0.5971   1.0000
   3.250   0.8052   0.01604   0.00765  -0.1052   0.5863   1.0000
   3.500   0.8299   0.01625   0.00781  -0.1045   0.5759   1.0000
   3.750   0.8558   0.01645   0.00791  -0.1039   0.5661   1.0000
   4.000   0.8793   0.01670   0.00814  -0.1029   0.5546   1.0000
   4.250   0.9036   0.01695   0.00834  -0.1021   0.5439   1.0000
   4.500   0.9287   0.01720   0.00853  -0.1014   0.5341   1.0000
   4.750   0.9518   0.01749   0.00884  -0.1005   0.5231   1.0000
   5.000   0.9760   0.01778   0.00909  -0.0997   0.5131   1.0000
   5.250   0.9996   0.01807   0.00936  -0.0987   0.5022   1.0000
   5.500   1.0218   0.01840   0.00970  -0.0976   0.4905   1.0000
   5.750   1.0446   0.01872   0.01000  -0.0966   0.4794   1.0000
   6.000   1.0672   0.01903   0.01028  -0.0955   0.4681   1.0000
   6.250   1.0881   0.01939   0.01069  -0.0942   0.4561   1.0000
   6.500   1.1097   0.01975   0.01106  -0.0930   0.4455   1.0000
   6.750   1.1318   0.02011   0.01141  -0.0919   0.4358   1.0000
   7.000   1.1519   0.02051   0.01189  -0.0905   0.4247   1.0000
   7.250   1.1722   0.02091   0.01230  -0.0892   0.4141   1.0000
   7.500   1.1923   0.02131   0.01270  -0.0878   0.4040   1.0000
   7.750   1.2108   0.02175   0.01321  -0.0862   0.3930   1.0000
   8.000   1.2296   0.02220   0.01370  -0.0846   0.3828   1.0000
   8.250   1.2477   0.02266   0.01420  -0.0830   0.3729   1.0000
   8.500   1.2639   0.02316   0.01477  -0.0811   0.3616   1.0000
   8.750   1.2778   0.02367   0.01530  -0.0788   0.3488   1.0000
   9.000   1.2888   0.02421   0.01584  -0.0760   0.3353   1.0000
   9.250   1.2981   0.02482   0.01646  -0.0731   0.3215   1.0000
   9.500   1.3067   0.02549   0.01717  -0.0701   0.3075   1.0000
   9.750   1.3146   0.02623   0.01797  -0.0673   0.2929   1.0000
  10.000   1.3215   0.02706   0.01885  -0.0644   0.2774   1.0000
  10.250   1.3268   0.02801   0.01984  -0.0616   0.2604   1.0000
  10.500   1.3306   0.02911   0.02099  -0.0588   0.2407   1.0000
  10.750   1.3324   0.03043   0.02229  -0.0560   0.2179   1.0000
  11.000   1.3308   0.03207   0.02386  -0.0532   0.1941   1.0000
  11.250   1.3266   0.03405   0.02573  -0.0506   0.1721   1.0000
  11.500   1.3212   0.03633   0.02790  -0.0483   0.1549   1.0000
  11.750   1.3158   0.03880   0.03030  -0.0463   0.1415   1.0000
  12.000   1.3116   0.04133   0.03282  -0.0447   0.1306   1.0000
  12.250   1.3077   0.04398   0.03550  -0.0433   0.1212   1.0000
  12.500   1.3008   0.04702   0.03852  -0.0421   0.1135   1.0000
  12.750   1.2992   0.04972   0.04135  -0.0413   0.1051   1.0000
  13.000   1.2919   0.05308   0.04472  -0.0407   0.0989   1.0000
  13.250   1.2913   0.05591   0.04770  -0.0402   0.0912   1.0000
  13.500   1.2851   0.05947   0.05127  -0.0401   0.0855   1.0000
  13.750   1.2834   0.06264   0.05458  -0.0400   0.0793   1.0000
  14.000   1.2769   0.06649   0.05847  -0.0404   0.0748   1.0000
  14.250   1.2745   0.06996   0.06205  -0.0406   0.0698   1.0000
  14.500   1.2690   0.07394   0.06608  -0.0412   0.0659   1.0000
  14.750   1.2642   0.07789   0.07007  -0.0419   0.0625   1.0000
  15.000   1.2618   0.08159   0.07388  -0.0425   0.0589   1.0000
  15.250   1.2571   0.08572   0.07807  -0.0434   0.0561   1.0000
  15.500   1.2540   0.08959   0.08198  -0.0442   0.0534   1.0000
  15.750   1.2534   0.09318   0.08569  -0.0449   0.0505   1.0000
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