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GOE 600 AIRFOIL (goe600-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 600 AIRFOIL (goe600-il)
Reynolds number: 500,000
Max Cl/Cd: 91.25 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe600-il-500000.txt
Download as CSV file: xf-goe600-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 600 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -15.250  -0.8983   0.08606   0.08313  -0.0307   1.0000   0.0147
 -15.000  -0.9405   0.07381   0.07059  -0.0390   1.0000   0.0145
 -14.750  -0.9630   0.06592   0.06251  -0.0444   1.0000   0.0144
 -14.500  -0.9801   0.05938   0.05579  -0.0488   1.0000   0.0144
 -14.250  -0.9934   0.05376   0.04999  -0.0525   1.0000   0.0145
 -14.000  -1.0027   0.04899   0.04508  -0.0554   1.0000   0.0146
 -13.750  -1.0087   0.04494   0.04088  -0.0576   1.0000   0.0147
 -13.500  -1.0115   0.04159   0.03740  -0.0592   1.0000   0.0149
 -13.250  -1.0126   0.03873   0.03442  -0.0601   1.0000   0.0151
 -13.000  -1.0123   0.03635   0.03191  -0.0603   1.0000   0.0153
 -12.750  -1.0104   0.03440   0.02983  -0.0596   1.0000   0.0155
 -12.500  -1.0080   0.03272   0.02803  -0.0582   1.0000   0.0158
 -12.250  -1.0043   0.03131   0.02649  -0.0562   1.0000   0.0162
 -12.000  -0.9962   0.02991   0.02495  -0.0546   1.0000   0.0166
 -11.750  -0.9850   0.02859   0.02346  -0.0532   1.0000   0.0170
 -11.500  -0.9714   0.02743   0.02213  -0.0519   1.0000   0.0174
 -11.250  -0.9615   0.02554   0.02007  -0.0502   1.0000   0.0178
 -11.000  -0.9489   0.02410   0.01856  -0.0487   1.0000   0.0183
 -10.750  -0.9331   0.02320   0.01762  -0.0474   1.0000   0.0189
 -10.500  -0.9178   0.02243   0.01680  -0.0458   1.0000   0.0194
 -10.250  -0.9047   0.02171   0.01601  -0.0436   1.0000   0.0201
 -10.000  -0.8946   0.02107   0.01529  -0.0409   1.0000   0.0207
  -9.750  -0.8794   0.02047   0.01458  -0.0390   0.9994   0.0213
  -9.500  -0.8496   0.01914   0.01318  -0.0405   0.9965   0.0226
  -9.250  -0.8158   0.01846   0.01248  -0.0425   0.9941   0.0239
  -9.000  -0.7830   0.01780   0.01176  -0.0440   0.9907   0.0254
  -8.750  -0.7503   0.01698   0.01083  -0.0456   0.9873   0.0269
  -8.500  -0.7170   0.01615   0.01001  -0.0474   0.9846   0.0291
  -8.250  -0.6833   0.01570   0.00951  -0.0489   0.9809   0.0315
  -8.000  -0.6535   0.01494   0.00872  -0.0498   0.9750   0.0345
  -7.750  -0.6206   0.01451   0.00827  -0.0512   0.9703   0.0378
  -7.500  -0.5938   0.01393   0.00763  -0.0512   0.9618   0.0412
  -7.250  -0.5659   0.01346   0.00715  -0.0514   0.9549   0.0453
  -7.000  -0.5405   0.01322   0.00683  -0.0509   0.9452   0.0484
  -6.750  -0.5175   0.01256   0.00615  -0.0501   0.9364   0.0536
  -6.500  -0.4929   0.01224   0.00576  -0.0495   0.9271   0.0575
  -6.250  -0.4688   0.01179   0.00529  -0.0488   0.9176   0.0637
  -5.750  -0.4190   0.01105   0.00465  -0.0476   0.8986   0.0916
  -5.500  -0.3931   0.01081   0.00447  -0.0473   0.8896   0.1153
  -5.250  -0.3665   0.01062   0.00427  -0.0470   0.8802   0.1303
  -5.000  -0.3394   0.01045   0.00407  -0.0469   0.8709   0.1406
  -4.750  -0.3124   0.01030   0.00386  -0.0466   0.8623   0.1497
  -4.500  -0.2851   0.01007   0.00364  -0.0466   0.8523   0.1585
  -4.000  -0.2305   0.00966   0.00320  -0.0464   0.8345   0.1814
  -3.750  -0.2038   0.00928   0.00297  -0.0464   0.8263   0.2172
  -3.500  -0.1776   0.00880   0.00278  -0.0464   0.8181   0.2997
  -3.250  -0.1504   0.00850   0.00264  -0.0464   0.8106   0.3549
  -3.000  -0.1230   0.00825   0.00253  -0.0464   0.8030   0.4046
  -2.750  -0.0952   0.00809   0.00245  -0.0465   0.7958   0.4433
  -2.500  -0.0672   0.00796   0.00239  -0.0465   0.7878   0.4766
  -2.250  -0.0393   0.00786   0.00234  -0.0465   0.7801   0.5087
  -2.000  -0.0112   0.00777   0.00230  -0.0465   0.7723   0.5399
  -1.750   0.0171   0.00772   0.00227  -0.0466   0.7652   0.5636
  -1.500   0.0456   0.00767   0.00224  -0.0467   0.7579   0.5837
  -1.250   0.0741   0.00766   0.00221  -0.0467   0.7515   0.6028
  -1.000   0.1026   0.00760   0.00220  -0.0468   0.7441   0.6198
  -0.750   0.1309   0.00758   0.00217  -0.0469   0.7380   0.6382
  -0.500   0.1594   0.00752   0.00219  -0.0470   0.7319   0.6588
  -0.250   0.1877   0.00747   0.00219  -0.0470   0.7261   0.6804
   0.000   0.2160   0.00745   0.00220  -0.0470   0.7207   0.7011
   0.250   0.2442   0.00738   0.00223  -0.0471   0.7146   0.7249
   0.500   0.2719   0.00732   0.00226  -0.0469   0.7089   0.7534
   0.750   0.2993   0.00727   0.00230  -0.0467   0.7031   0.7852
   1.000   0.3261   0.00719   0.00236  -0.0463   0.6967   0.8207
   1.250   0.3517   0.00716   0.00242  -0.0455   0.6907   0.8625
   1.500   0.3766   0.00709   0.00249  -0.0445   0.6835   0.9057
   1.750   0.4040   0.00711   0.00252  -0.0440   0.6754   0.9404
   2.000   0.4376   0.00712   0.00256  -0.0451   0.6646   0.9625
   2.250   0.4743   0.00717   0.00258  -0.0469   0.6542   0.9773
   2.500   0.5132   0.00724   0.00261  -0.0493   0.6442   0.9878
   2.750   0.5549   0.00729   0.00267  -0.0523   0.6319   0.9953
   3.000   0.5936   0.00735   0.00271  -0.0548   0.6187   1.0000
   3.250   0.6183   0.00739   0.00273  -0.0542   0.6066   1.0000
   3.500   0.6431   0.00745   0.00276  -0.0537   0.5927   1.0000
   3.750   0.6680   0.00753   0.00281  -0.0531   0.5754   1.0000
   4.000   0.6924   0.00766   0.00286  -0.0524   0.5521   1.0000
   4.250   0.7163   0.00785   0.00295  -0.0517   0.5186   1.0000
   4.500   0.7390   0.00818   0.00309  -0.0508   0.4753   1.0000
   4.750   0.7617   0.00858   0.00330  -0.0500   0.4370   1.0000
   5.000   0.7846   0.00900   0.00356  -0.0492   0.4031   1.0000
   5.250   0.8084   0.00937   0.00380  -0.0487   0.3755   1.0000
   5.750   0.8573   0.01003   0.00430  -0.0477   0.3292   1.0000
   6.000   0.8814   0.01039   0.00456  -0.0472   0.3055   1.0000
   6.250   0.9054   0.01077   0.00484  -0.0467   0.2785   1.0000
   6.500   0.9289   0.01119   0.00515  -0.0461   0.2518   1.0000
   6.750   0.9519   0.01164   0.00549  -0.0455   0.2259   1.0000
   7.000   0.9744   0.01213   0.00586  -0.0448   0.2006   1.0000
   7.250   0.9967   0.01264   0.00625  -0.0441   0.1752   1.0000
   7.500   1.0184   0.01318   0.00668  -0.0433   0.1507   1.0000
   7.750   1.0397   0.01375   0.00713  -0.0425   0.1278   1.0000
   8.000   1.0605   0.01434   0.00761  -0.0416   0.1060   1.0000
   8.250   1.0806   0.01497   0.00814  -0.0406   0.0894   1.0000
   8.500   1.1006   0.01558   0.00870  -0.0395   0.0748   1.0000
   8.750   1.1188   0.01633   0.00933  -0.0382   0.0540   1.0000
   9.000   1.1354   0.01715   0.01003  -0.0367   0.0408   1.0000
   9.250   1.1527   0.01789   0.01078  -0.0352   0.0358   1.0000
   9.500   1.1677   0.01874   0.01163  -0.0335   0.0325   1.0000
   9.750   1.1814   0.01953   0.01250  -0.0314   0.0303   1.0000
  10.000   1.1945   0.02027   0.01330  -0.0293   0.0286   1.0000
  10.250   1.2054   0.02118   0.01426  -0.0271   0.0271   1.0000
  10.500   1.2089   0.02264   0.01577  -0.0241   0.0255   1.0000
  10.750   1.2221   0.02351   0.01673  -0.0225   0.0245   1.0000
  11.000   1.2345   0.02448   0.01777  -0.0209   0.0234   1.0000
  11.250   1.2452   0.02560   0.01895  -0.0193   0.0224   1.0000
  11.500   1.2534   0.02694   0.02035  -0.0177   0.0215   1.0000
  11.750   1.2548   0.02889   0.02235  -0.0156   0.0207   1.0000
  12.000   1.2596   0.03065   0.02421  -0.0139   0.0202   1.0000
  12.250   1.2696   0.03202   0.02568  -0.0128   0.0196   1.0000
  12.500   1.2782   0.03356   0.02731  -0.0118   0.0190   1.0000
  12.750   1.2859   0.03520   0.02903  -0.0108   0.0184   1.0000
  13.000   1.2929   0.03695   0.03085  -0.0099   0.0178   1.0000
  13.250   1.2986   0.03886   0.03282  -0.0092   0.0173   1.0000
  13.500   1.3004   0.04117   0.03519  -0.0083   0.0168   1.0000
  13.750   1.2956   0.04420   0.03829  -0.0069   0.0163   1.0000
  14.000   1.3014   0.04627   0.04048  -0.0066   0.0160   1.0000
  14.250   1.3051   0.04857   0.04291  -0.0061   0.0157   1.0000
  14.500   1.3074   0.05107   0.04553  -0.0058   0.0154   1.0000
  14.750   1.3088   0.05373   0.04830  -0.0056   0.0151   1.0000
  15.000   1.3092   0.05656   0.05124  -0.0055   0.0148   1.0000
  15.250   1.3090   0.05956   0.05436  -0.0056   0.0145   1.0000
  15.500   1.3081   0.06274   0.05764  -0.0059   0.0143   1.0000
  15.750   1.3067   0.06608   0.06108  -0.0065   0.0140   1.0000
  16.000   1.3044   0.06959   0.06468  -0.0071   0.0138   1.0000
  16.250   1.3015   0.07327   0.06846  -0.0079   0.0136   1.0000
  16.500   1.2978   0.07713   0.07240  -0.0088   0.0134   1.0000
  16.750   1.2927   0.08121   0.07657  -0.0098   0.0132   1.0000
  17.000   1.2843   0.08572   0.08118  -0.0106   0.0130   1.0000
  17.250   1.2727   0.09098   0.08661  -0.0121   0.0129   1.0000
  17.500   1.2638   0.09639   0.09218  -0.0146   0.0128   1.0000
  17.750   1.2537   0.10209   0.09804  -0.0173   0.0127   1.0000
  18.000   1.2426   0.10807   0.10418  -0.0203   0.0126   1.0000
  18.250   1.2305   0.11438   0.11065  -0.0235   0.0125   1.0000
  18.500   1.2174   0.12107   0.11751  -0.0272   0.0125   1.0000
  18.750   1.2033   0.12811   0.12471  -0.0311   0.0124   1.0000
  19.000   1.1878   0.13561   0.13236  -0.0355   0.0123   1.0000
  19.250   1.1710   0.14367   0.14059  -0.0404   0.0123   1.0000
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