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GOE 602 AIRFOIL (goe602-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 602 AIRFOIL (goe602-il)
Reynolds number: 1,000,000
Max Cl/Cd: 119.06 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe602-il-1000000.txt
Download as CSV file: xf-goe602-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 602 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.2976   0.11069   0.10915  -0.0341   1.0000   0.0127
 -11.000  -0.2995   0.10775   0.10623  -0.0338   1.0000   0.0131
 -10.250  -0.6880   0.02929   0.02688  -0.0841   0.9879   0.0083
 -10.000  -0.6535   0.03013   0.02782  -0.0852   0.9870   0.0087
  -9.750  -0.6376   0.02424   0.02132  -0.0890   0.9844   0.0089
  -9.500  -0.6051   0.02381   0.02084  -0.0907   0.9836   0.0093
  -9.250  -0.5889   0.02128   0.01798  -0.0904   0.9782   0.0095
  -9.000  -0.5623   0.01951   0.01595  -0.0915   0.9758   0.0099
  -8.750  -0.5333   0.01802   0.01422  -0.0927   0.9742   0.0104
  -8.500  -0.5024   0.01690   0.01291  -0.0941   0.9730   0.0107
  -8.250  -0.4734   0.01483   0.01050  -0.0954   0.9719   0.0114
  -8.000  -0.4400   0.01417   0.00976  -0.0971   0.9710   0.0121
  -7.750  -0.4151   0.01398   0.00956  -0.0966   0.9665   0.0126
  -7.500  -0.3843   0.01372   0.00926  -0.0973   0.9638   0.0134
  -7.250  -0.3527   0.01331   0.00877  -0.0983   0.9615   0.0142
  -7.000  -0.3205   0.01296   0.00834  -0.0993   0.9594   0.0147
  -6.750  -0.2913   0.01181   0.00707  -0.1001   0.9567   0.0161
  -6.500  -0.2656   0.01166   0.00690  -0.0997   0.9510   0.0169
  -6.250  -0.2362   0.01136   0.00656  -0.1000   0.9469   0.0180
  -6.000  -0.2042   0.01113   0.00626  -0.1009   0.9434   0.0190
  -5.750  -0.1806   0.01055   0.00560  -0.1001   0.9364   0.0203
  -5.500  -0.1522   0.01017   0.00519  -0.1003   0.9310   0.0217
  -5.250  -0.1252   0.00997   0.00497  -0.1001   0.9247   0.0230
  -5.000  -0.0981   0.00971   0.00467  -0.1000   0.9184   0.0244
  -4.750  -0.0696   0.00963   0.00454  -0.1000   0.9128   0.0256
  -4.500  -0.0446   0.00920   0.00403  -0.0995   0.9059   0.0268
  -4.250  -0.0189   0.00859   0.00335  -0.0991   0.8998   0.0288
  -4.000   0.0066   0.00834   0.00308  -0.0986   0.8925   0.0303
  -3.750   0.0340   0.00815   0.00283  -0.0984   0.8862   0.0321
  -3.500   0.0599   0.00794   0.00259  -0.0979   0.8786   0.0333
  -3.000   0.1134   0.00766   0.00221  -0.0974   0.8632   0.0349
  -2.750   0.1395   0.00737   0.00182  -0.0969   0.8551   0.0372
  -2.500   0.1659   0.00719   0.00161  -0.0965   0.8458   0.0402
  -2.250   0.1924   0.00706   0.00145  -0.0961   0.8360   0.0435
  -2.000   0.2190   0.00695   0.00130  -0.0958   0.8257   0.0507
  -1.750   0.2439   0.00663   0.00119  -0.0952   0.8138   0.1175
  -1.500   0.2682   0.00625   0.00108  -0.0946   0.8008   0.2161
  -1.250   0.2932   0.00603   0.00104  -0.0941   0.7868   0.2975
  -1.000   0.3184   0.00591   0.00100  -0.0936   0.7718   0.3491
  -0.750   0.3430   0.00575   0.00098  -0.0929   0.7561   0.4151
  -0.500   0.3665   0.00551   0.00098  -0.0921   0.7383   0.5199
  -0.250   0.3885   0.00528   0.00101  -0.0909   0.7174   0.6459
   0.000   0.4104   0.00515   0.00105  -0.0896   0.6962   0.7310
   0.250   0.4318   0.00501   0.00109  -0.0880   0.6770   0.8128
   0.500   0.4528   0.00491   0.00117  -0.0862   0.6578   0.9076
   0.750   0.4955   0.00499   0.00124  -0.0894   0.6373   0.9697
   1.000   0.5439   0.00515   0.00128  -0.0940   0.6131   0.9880
   1.250   0.5845   0.00532   0.00133  -0.0969   0.5892   0.9982
   1.500   0.6135   0.00546   0.00137  -0.0973   0.5701   1.0000
   1.750   0.6355   0.00559   0.00142  -0.0960   0.5527   1.0000
   2.000   0.6580   0.00573   0.00148  -0.0949   0.5344   1.0000
   2.250   0.6804   0.00589   0.00155  -0.0938   0.5145   1.0000
   2.500   0.7032   0.00604   0.00163  -0.0928   0.4976   1.0000
   2.750   0.7261   0.00620   0.00172  -0.0917   0.4808   1.0000
   3.000   0.7494   0.00636   0.00181  -0.0908   0.4645   1.0000
   3.250   0.7730   0.00651   0.00191  -0.0899   0.4497   1.0000
   3.500   0.7965   0.00669   0.00202  -0.0891   0.4326   1.0000
   3.750   0.8188   0.00693   0.00215  -0.0880   0.4074   1.0000
   4.000   0.8412   0.00720   0.00231  -0.0869   0.3801   1.0000
   4.250   0.8637   0.00747   0.00246  -0.0859   0.3519   1.0000
   4.500   0.8854   0.00781   0.00265  -0.0848   0.3178   1.0000
   4.750   0.9056   0.00827   0.00289  -0.0835   0.2730   1.0000
   5.000   0.9256   0.00876   0.00317  -0.0821   0.2308   1.0000
   5.250   0.9446   0.00934   0.00351  -0.0806   0.1836   1.0000
   5.500   0.9594   0.01024   0.00401  -0.0784   0.1111   1.0000
   5.750   0.9788   0.01081   0.00442  -0.0770   0.0808   1.0000
   6.000   0.9940   0.01171   0.00503  -0.0748   0.0255   1.0000
   6.250   1.0157   0.01211   0.00544  -0.0737   0.0206   1.0000
   6.500   1.0369   0.01254   0.00592  -0.0724   0.0175   1.0000
   6.750   1.0590   0.01287   0.00627  -0.0715   0.0162   1.0000
   7.000   1.0803   0.01326   0.00669  -0.0703   0.0149   1.0000
   7.250   1.0996   0.01379   0.00727  -0.0688   0.0136   1.0000
   7.500   1.1164   0.01448   0.00805  -0.0669   0.0127   1.0000
   7.750   1.1367   0.01488   0.00848  -0.0656   0.0122   1.0000
   8.000   1.1561   0.01531   0.00896  -0.0642   0.0116   1.0000
   8.250   1.1752   0.01575   0.00942  -0.0628   0.0109   1.0000
   8.500   1.1915   0.01627   0.00998  -0.0608   0.0102   1.0000
   8.750   1.2042   0.01690   0.01066  -0.0583   0.0098   1.0000
   9.000   1.2081   0.01800   0.01185  -0.0542   0.0093   1.0000
   9.250   1.2148   0.01898   0.01291  -0.0508   0.0090   1.0000
   9.500   1.2267   0.01969   0.01369  -0.0483   0.0088   1.0000
   9.750   1.2389   0.02040   0.01446  -0.0460   0.0086   1.0000
  10.000   1.2511   0.02112   0.01524  -0.0438   0.0083   1.0000
  10.250   1.2603   0.02205   0.01624  -0.0413   0.0080   1.0000
  10.500   1.2704   0.02295   0.01720  -0.0390   0.0077   1.0000
  10.750   1.2790   0.02398   0.01830  -0.0366   0.0075   1.0000
  11.000   1.2899   0.02486   0.01923  -0.0347   0.0073   1.0000
  11.250   1.2975   0.02601   0.02044  -0.0326   0.0070   1.0000
  11.500   1.3052   0.02718   0.02165  -0.0306   0.0067   1.0000
  11.750   1.3050   0.02912   0.02367  -0.0280   0.0065   1.0000
  12.000   1.2996   0.03195   0.02664  -0.0250   0.0063   1.0000
  12.250   1.3062   0.03350   0.02829  -0.0234   0.0062   1.0000
  12.500   1.3127   0.03502   0.02992  -0.0219   0.0061   1.0000
  12.750   1.3168   0.03698   0.03199  -0.0203   0.0060   1.0000
  13.000   1.3206   0.03895   0.03409  -0.0190   0.0059   1.0000
  13.250   1.3237   0.04104   0.03628  -0.0178   0.0058   1.0000
  13.500   1.3258   0.04328   0.03864  -0.0168   0.0057   1.0000
  13.750   1.3245   0.04614   0.04166  -0.0158   0.0057   1.0000
  14.000   1.3224   0.04909   0.04475  -0.0150   0.0056   1.0000
  14.250   1.3190   0.05230   0.04812  -0.0145   0.0055   1.0000
  14.500   1.3136   0.05584   0.05181  -0.0143   0.0055   1.0000
  14.750   1.3076   0.05956   0.05568  -0.0145   0.0054   1.0000
  15.000   1.2992   0.06384   0.06012  -0.0151   0.0054   1.0000
  15.250   1.2879   0.06871   0.06517  -0.0161   0.0053   1.0000
  15.500   1.2797   0.07326   0.06985  -0.0175   0.0053   1.0000
  15.750   1.2641   0.07931   0.07609  -0.0195   0.0052   1.0000
  16.000   1.2535   0.08471   0.08162  -0.0219   0.0052   1.0000
  16.250   1.2380   0.09129   0.08837  -0.0249   0.0052   1.0000
  16.500   1.2129   0.10010   0.09740  -0.0291   0.0052   1.0000
  16.750   1.2003   0.10678   0.10421  -0.0329   0.0052   1.0000
  17.000   1.1800   0.11540   0.11299  -0.0378   0.0052   1.0000
  17.250   1.1516   0.12641   0.12420  -0.0442   0.0053   1.0000
  17.500   1.1344   0.13528   0.13320  -0.0497   0.0053   1.0000
  17.750   1.1065   0.14745   0.14554  -0.0573   0.0054   1.0000
  18.000   1.0840   0.15907   0.15730  -0.0646   0.0054   1.0000
  18.250   1.0530   0.17422   0.17258  -0.0737   0.0058   1.0000
  18.500   1.0072   0.19768   0.19614  -0.0856   0.0067   1.0000
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