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GOE 591 AIRFOIL (goe591-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 591 AIRFOIL (goe591-il)
Reynolds number: 100,000
Max Cl/Cd: 52.75 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe591-il-100000.txt
Download as CSV file: xf-goe591-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 591 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3588   0.09947   0.09541  -0.0218   1.0000   0.0945
  -7.250  -0.3740   0.09845   0.09447  -0.0190   1.0000   0.0957
  -7.000  -0.3922   0.09754   0.09365  -0.0161   1.0000   0.0968
  -6.750  -0.3833   0.09408   0.09019  -0.0229   0.9939   0.1013
  -6.500  -0.3626   0.08771   0.08373  -0.0408   0.9815   0.1052
  -6.250  -0.3416   0.08415   0.08020  -0.0375   0.9767   0.1081
  -6.000  -0.3134   0.08006   0.07603  -0.0448   0.9688   0.1165
  -5.750  -0.2930   0.07495   0.07085  -0.0522   0.9590   0.1220
  -5.500  -0.2699   0.07179   0.06766  -0.0539   0.9514   0.1282
  -5.250  -0.2401   0.06666   0.06235  -0.0630   0.9428   0.1373
  -5.000  -0.2199   0.06392   0.05958  -0.0637   0.9336   0.1441
  -4.750  -0.1864   0.05987   0.05540  -0.0693   0.9274   0.1566
  -4.500  -0.1657   0.05675   0.05214  -0.0720   0.9168   0.1694
  -4.250  -0.1275   0.05314   0.04835  -0.0770   0.9117   0.1851
  -4.000  -0.1075   0.05064   0.04572  -0.0782   0.9008   0.1996
  -3.750  -0.0688   0.04760   0.04260  -0.0816   0.8966   0.2188
  -3.500  -0.0494   0.04577   0.04059  -0.0821   0.8853   0.2454
  -3.250   0.0191   0.03301   0.02551  -0.0909   0.8825   0.1015
  -3.000   0.0450   0.03116   0.02329  -0.0905   0.8727   0.1012
  -2.750   0.0904   0.02914   0.02071  -0.0932   0.8682   0.1033
  -2.500   0.1204   0.02786   0.01906  -0.0931   0.8591   0.1042
  -2.250   0.1645   0.02593   0.01703  -0.0958   0.8543   0.1082
  -2.000   0.2145   0.02461   0.01550  -0.0990   0.8511   0.1185
  -1.750   0.2385   0.02382   0.01479  -0.0981   0.8400   0.1267
  -1.500   0.2844   0.02246   0.01342  -0.1005   0.8361   0.1502
  -1.250   0.3073   0.02189   0.01308  -0.0993   0.8248   0.1875
  -1.000   0.3492   0.02056   0.01208  -0.1012   0.8205   0.2663
  -0.750   0.4343   0.01784   0.01138  -0.1114   0.8152   1.0000
  -0.500   0.4688   0.01766   0.01089  -0.1120   0.8068   1.0000
  -0.250   0.4920   0.01777   0.01080  -0.1108   0.7951   1.0000
   0.000   0.5247   0.01765   0.01047  -0.1111   0.7866   1.0000
   0.250   0.5515   0.01766   0.01031  -0.1104   0.7760   1.0000
   0.500   0.5741   0.01783   0.01034  -0.1091   0.7642   1.0000
   0.750   0.6033   0.01781   0.01017  -0.1089   0.7550   1.0000
   1.000   0.6306   0.01783   0.01006  -0.1084   0.7447   1.0000
   1.250   0.6525   0.01805   0.01018  -0.1070   0.7329   1.0000
   1.500   0.6792   0.01813   0.01014  -0.1064   0.7230   1.0000
   1.750   0.7080   0.01812   0.01001  -0.1061   0.7135   1.0000
   2.000   0.7293   0.01837   0.01021  -0.1047   0.7017   1.0000
   2.250   0.7547   0.01850   0.01026  -0.1040   0.6915   1.0000
   2.500   0.7846   0.01848   0.01012  -0.1038   0.6825   1.0000
   2.750   0.8057   0.01876   0.01036  -0.1025   0.6707   1.0000
   3.000   0.8300   0.01893   0.01050  -0.1016   0.6601   1.0000
   3.250   0.8609   0.01890   0.01034  -0.1016   0.6513   1.0000
   3.500   0.8814   0.01922   0.01066  -0.1002   0.6396   1.0000
   3.750   0.9048   0.01948   0.01091  -0.0993   0.6292   1.0000
   4.000   0.9353   0.01953   0.01085  -0.0993   0.6208   1.0000
   4.250   0.9551   0.01993   0.01129  -0.0979   0.6095   1.0000
   4.500   0.9788   0.02024   0.01161  -0.0970   0.5996   1.0000
   4.750   1.0077   0.02037   0.01166  -0.0969   0.5907   1.0000
   5.000   1.0274   0.02081   0.01218  -0.0955   0.5798   1.0000
   5.250   1.0519   0.02114   0.01250  -0.0948   0.5703   1.0000
   5.500   1.0789   0.02136   0.01271  -0.0944   0.5608   1.0000
   5.750   1.0987   0.02183   0.01325  -0.0930   0.5498   1.0000
   6.000   1.1228   0.02216   0.01359  -0.0923   0.5396   1.0000
   6.250   1.1512   0.02231   0.01369  -0.0921   0.5293   1.0000
   6.500   1.1704   0.02266   0.01412  -0.0904   0.5165   1.0000
   6.750   1.1911   0.02296   0.01446  -0.0891   0.5037   1.0000
   7.000   1.2130   0.02326   0.01478  -0.0879   0.4914   1.0000
   7.250   1.2374   0.02357   0.01510  -0.0871   0.4802   1.0000
   7.500   1.2612   0.02391   0.01546  -0.0863   0.4690   1.0000
   7.750   1.2787   0.02442   0.01609  -0.0846   0.4568   1.0000
   8.000   1.2986   0.02490   0.01664  -0.0832   0.4449   1.0000
   8.250   1.3207   0.02532   0.01711  -0.0822   0.4334   1.0000
   8.500   1.3462   0.02567   0.01743  -0.0817   0.4220   1.0000
   8.750   1.3612   0.02616   0.01804  -0.0796   0.4090   1.0000
   9.000   1.3767   0.02652   0.01848  -0.0774   0.3950   1.0000
   9.250   1.3910   0.02678   0.01881  -0.0751   0.3803   1.0000
   9.500   1.4039   0.02710   0.01919  -0.0726   0.3659   1.0000
   9.750   1.4155   0.02750   0.01967  -0.0700   0.3521   1.0000
  10.000   1.4249   0.02790   0.02013  -0.0670   0.3381   1.0000
  10.250   1.4312   0.02832   0.02061  -0.0636   0.3239   1.0000
  10.500   1.4349   0.02882   0.02118  -0.0599   0.3106   1.0000
  10.750   1.4365   0.02942   0.02182  -0.0560   0.2976   1.0000
  11.000   1.4364   0.03015   0.02259  -0.0521   0.2843   1.0000
  11.250   1.4361   0.03104   0.02352  -0.0486   0.2711   1.0000
  11.500   1.4337   0.03214   0.02467  -0.0451   0.2576   1.0000
  11.750   1.4285   0.03351   0.02610  -0.0418   0.2430   1.0000
  12.000   1.4240   0.03510   0.02776  -0.0389   0.2290   1.0000
  12.250   1.4159   0.03711   0.02988  -0.0362   0.2123   1.0000
  12.500   1.4064   0.03954   0.03241  -0.0340   0.1937   1.0000
  12.750   1.3926   0.04261   0.03548  -0.0321   0.1719   1.0000
  13.000   1.3750   0.04645   0.03925  -0.0307   0.1461   1.0000
  13.250   1.3538   0.05108   0.04375  -0.0298   0.1215   1.0000
  13.500   1.3317   0.05626   0.04882  -0.0295   0.0983   1.0000
  13.750   1.3117   0.06158   0.05405  -0.0296   0.0815   1.0000
  14.000   1.2947   0.06683   0.05925  -0.0301   0.0728   1.0000
  14.250   1.2804   0.07195   0.06439  -0.0308   0.0675   1.0000
  14.500   1.2658   0.07727   0.06972  -0.0318   0.0635   1.0000
  14.750   1.2538   0.08231   0.07476  -0.0327   0.0605   1.0000
  15.000   1.2475   0.08658   0.07914  -0.0334   0.0570   1.0000
  15.250   1.2427   0.09059   0.08320  -0.0340   0.0543   1.0000
  15.500   1.2426   0.09343   0.08592  -0.0336   0.0510   1.0000
  15.750   1.2470   0.09613   0.08878  -0.0335   0.0487   1.0000
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