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GOE 647 AIRFOIL (goe647-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 647 AIRFOIL (goe647-il)
Reynolds number: 100,000
Max Cl/Cd: 44.5 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe647-il-100000-n5.txt
Download as CSV file: xf-goe647-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 647 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.2641   0.08523   0.08034  -0.0649   0.9756   0.0531
  -9.750  -0.2800   0.07458   0.06967  -0.0742   0.9653   0.0530
  -9.500  -0.3514   0.05421   0.04893  -0.0972   0.9420   0.0522
  -9.250  -0.3713   0.04658   0.04070  -0.1035   0.9258   0.0524
  -9.000  -0.3764   0.04175   0.03521  -0.1050   0.9120   0.0531
  -8.750  -0.3510   0.03932   0.03260  -0.1070   0.9060   0.0539
  -8.500  -0.3358   0.03752   0.03063  -0.1065   0.8943   0.0545
  -8.250  -0.3092   0.03531   0.02813  -0.1080   0.8881   0.0552
  -8.000  -0.2932   0.03367   0.02626  -0.1070   0.8761   0.0559
  -7.750  -0.2653   0.03179   0.02408  -0.1081   0.8696   0.0570
  -7.500  -0.2471   0.03044   0.02247  -0.1069   0.8578   0.0582
  -7.250  -0.2195   0.02887   0.02050  -0.1074   0.8503   0.0599
  -7.000  -0.1977   0.02786   0.01942  -0.1065   0.8391   0.0610
  -6.750  -0.1687   0.02683   0.01830  -0.1068   0.8311   0.0624
  -6.500  -0.1456   0.02595   0.01732  -0.1060   0.8199   0.0636
  -6.250  -0.1184   0.02502   0.01623  -0.1058   0.8109   0.0652
  -6.000  -0.0936   0.02421   0.01525  -0.1051   0.8001   0.0671
  -5.750  -0.0687   0.02349   0.01448  -0.1045   0.7894   0.0692
  -5.500  -0.0419   0.02284   0.01378  -0.1041   0.7788   0.0719
  -5.250  -0.0191   0.02228   0.01312  -0.1029   0.7655   0.0749
  -5.000   0.0057   0.02166   0.01239  -0.1021   0.7534   0.0778
  -4.750   0.0310   0.02109   0.01177  -0.1014   0.7417   0.0816
  -4.500   0.0538   0.02066   0.01123  -0.1002   0.7287   0.0870
  -4.250   0.0780   0.02015   0.01069  -0.0994   0.7176   0.0937
  -4.000   0.1023   0.01964   0.01013  -0.0985   0.7068   0.1029
  -3.750   0.1253   0.01918   0.00965  -0.0975   0.6953   0.1151
  -3.500   0.1504   0.01867   0.00917  -0.0968   0.6852   0.1348
  -3.250   0.1735   0.01832   0.00899  -0.0959   0.6735   0.1680
  -3.000   0.1986   0.01813   0.00883  -0.0952   0.6629   0.2097
  -2.750   0.2243   0.01800   0.00866  -0.0945   0.6521   0.2436
  -2.500   0.2482   0.01792   0.00859  -0.0936   0.6404   0.2727
  -2.250   0.2741   0.01786   0.00846  -0.0929   0.6300   0.2998
  -2.000   0.2980   0.01780   0.00841  -0.0919   0.6184   0.3224
  -1.750   0.3226   0.01775   0.00832  -0.0911   0.6071   0.3421
  -1.500   0.3479   0.01771   0.00821  -0.0903   0.5964   0.3612
  -1.250   0.3715   0.01769   0.00819  -0.0893   0.5843   0.3819
  -1.000   0.3963   0.01767   0.00813  -0.0885   0.5733   0.4034
  -0.750   0.4205   0.01765   0.00808  -0.0875   0.5615   0.4265
  -0.500   0.4444   0.01765   0.00807  -0.0866   0.5493   0.4519
  -0.250   0.4691   0.01761   0.00800  -0.0858   0.5380   0.4783
   0.000   0.4936   0.01759   0.00797  -0.0850   0.5258   0.5055
   0.250   0.5174   0.01756   0.00798  -0.0840   0.5138   0.5350
   0.500   0.5409   0.01750   0.00796  -0.0830   0.5024   0.5746
   1.000   0.6132   0.01703   0.00820  -0.0854   0.4763   0.8599
   1.250   0.6733   0.01728   0.00827  -0.0920   0.4618   1.0000
   1.500   0.6941   0.01754   0.00831  -0.0906   0.4520   1.0000
   1.750   0.7145   0.01780   0.00844  -0.0892   0.4414   1.0000
   2.000   0.7353   0.01808   0.00853  -0.0879   0.4326   1.0000
   2.250   0.7560   0.01837   0.00871  -0.0865   0.4234   1.0000
   2.500   0.7772   0.01868   0.00884  -0.0853   0.4161   1.0000
   2.750   0.7981   0.01899   0.00907  -0.0841   0.4080   1.0000
   3.000   0.8192   0.01932   0.00925  -0.0828   0.4012   1.0000
   3.250   0.8403   0.01966   0.00950  -0.0817   0.3942   1.0000
   3.500   0.8611   0.02000   0.00975  -0.0804   0.3874   1.0000
   3.750   0.8828   0.02037   0.00996  -0.0794   0.3820   1.0000
   4.000   0.9035   0.02074   0.01031  -0.0782   0.3758   1.0000
   4.250   0.9247   0.02112   0.01062  -0.0771   0.3704   1.0000
   4.500   0.9469   0.02151   0.01089  -0.0762   0.3660   1.0000
   4.750   0.9681   0.02193   0.01127  -0.0751   0.3613   1.0000
   5.000   0.9887   0.02234   0.01167  -0.0740   0.3564   1.0000
   5.250   1.0097   0.02276   0.01203  -0.0730   0.3519   1.0000
   5.500   1.0325   0.02320   0.01234  -0.0722   0.3481   1.0000
   5.750   1.0521   0.02366   0.01283  -0.0710   0.3438   1.0000
   6.000   1.0717   0.02414   0.01331  -0.0698   0.3395   1.0000
   6.250   1.0925   0.02461   0.01376  -0.0688   0.3359   1.0000
   6.500   1.1144   0.02508   0.01419  -0.0680   0.3327   1.0000
   6.750   1.1385   0.02560   0.01461  -0.0676   0.3299   1.0000
   7.000   1.1556   0.02616   0.01526  -0.0661   0.3265   1.0000
   7.250   1.1732   0.02672   0.01588  -0.0647   0.3231   1.0000
   7.500   1.1914   0.02726   0.01643  -0.0634   0.3199   1.0000
   7.750   1.2111   0.02779   0.01694  -0.0624   0.3168   1.0000
   8.000   1.2339   0.02832   0.01741  -0.0618   0.3141   1.0000
   8.250   1.2517   0.02897   0.01810  -0.0606   0.3115   1.0000
   8.500   1.2646   0.02969   0.01893  -0.0586   0.3087   1.0000
   8.750   1.2788   0.03041   0.01973  -0.0569   0.3060   1.0000
   9.000   1.2947   0.03112   0.02051  -0.0555   0.3035   1.0000
   9.250   1.3124   0.03180   0.02122  -0.0544   0.3011   1.0000
   9.500   1.3324   0.03245   0.02188  -0.0537   0.2989   1.0000
   9.750   1.3560   0.03307   0.02246  -0.0534   0.2968   1.0000
  10.000   1.3668   0.03398   0.02349  -0.0515   0.2945   1.0000
  10.250   1.3703   0.03510   0.02478  -0.0488   0.2920   1.0000
  10.500   1.3762   0.03621   0.02603  -0.0466   0.2894   1.0000
  10.750   1.3849   0.03730   0.02723  -0.0449   0.2872   1.0000
  11.000   1.3960   0.03835   0.02837  -0.0434   0.2851   1.0000
  11.250   1.4100   0.03931   0.02938  -0.0423   0.2832   1.0000
  11.500   1.4281   0.04014   0.03024  -0.0416   0.2815   1.0000
  11.750   1.4528   0.04077   0.03087  -0.0416   0.2797   1.0000
  12.000   1.4440   0.04275   0.03306  -0.0387   0.2776   1.0000
  12.250   1.4248   0.04545   0.03601  -0.0355   0.2751   1.0000
  12.500   1.4078   0.04840   0.03918  -0.0331   0.2725   1.0000
  12.750   1.3938   0.05146   0.04241  -0.0313   0.2702   1.0000
  13.000   1.3855   0.05432   0.04540  -0.0301   0.2680   1.0000
  13.250   1.3910   0.05615   0.04731  -0.0294   0.2660   1.0000
  13.500   1.4118   0.05676   0.04794  -0.0290   0.2644   1.0000
  13.750   1.4469   0.05631   0.04746  -0.0291   0.2629   1.0000
  14.750   0.9877   0.13329   0.12544  -0.0489   0.2181   1.0000
  15.000   0.9609   0.14186   0.13408  -0.0525   0.2103   1.0000
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