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GOE 573 AIRFOIL (goe573-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 573 AIRFOIL (goe573-il)
Reynolds number: 1,000,000
Max Cl/Cd: 127.67 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe573-il-1000000-n5.txt
Download as CSV file: xf-goe573-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 573 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -15.250  -0.2359   0.15724   0.15548  -0.0472   0.9839   0.0048
 -15.000  -0.2428   0.15509   0.15337  -0.0444   0.9736   0.0048
 -11.000  -0.4713   0.02282   0.01868  -0.1255   0.6682   0.0138
  -9.500  -0.3611   0.01880   0.01390  -0.1168   0.6070   0.0165
  -9.250  -0.3456   0.01760   0.01244  -0.1148   0.5995   0.0171
  -9.000  -0.3245   0.01721   0.01196  -0.1136   0.5922   0.0174
  -8.750  -0.2994   0.01727   0.01201  -0.1130   0.5848   0.0177
  -8.500  -0.2759   0.01718   0.01185  -0.1121   0.5776   0.0179
  -8.250  -0.2515   0.01710   0.01175  -0.1114   0.5708   0.0182
  -8.000  -0.2275   0.01706   0.01165  -0.1106   0.5634   0.0185
  -7.750  -0.2021   0.01715   0.01172  -0.1101   0.5567   0.0189
  -7.500  -0.1811   0.01665   0.01108  -0.1088   0.5490   0.0193
  -7.250  -0.1597   0.01615   0.01043  -0.1076   0.5419   0.0199
  -7.000  -0.1386   0.01559   0.00971  -0.1063   0.5336   0.0204
  -6.750  -0.1165   0.01515   0.00913  -0.1052   0.5270   0.0208
  -6.500  -0.0932   0.01486   0.00872  -0.1043   0.5194   0.0211
  -6.250  -0.0725   0.01421   0.00792  -0.1030   0.5129   0.0215
  -6.000  -0.0488   0.01401   0.00766  -0.1021   0.5059   0.0219
  -5.750  -0.0249   0.01392   0.00752  -0.1013   0.4990   0.0222
  -5.500  -0.0008   0.01376   0.00730  -0.1005   0.4927   0.0225
  -5.250   0.0229   0.01356   0.00702  -0.0996   0.4860   0.0229
  -5.000   0.0469   0.01333   0.00672  -0.0988   0.4805   0.0233
  -4.750   0.0707   0.01308   0.00638  -0.0980   0.4743   0.0237
  -4.250   0.1182   0.01247   0.00558  -0.0962   0.4628   0.0245
  -4.000   0.1421   0.01217   0.00520  -0.0954   0.4578   0.0248
  -3.750   0.1659   0.01194   0.00489  -0.0945   0.4530   0.0252
  -3.500   0.1904   0.01172   0.00461  -0.0938   0.4494   0.0254
  -3.250   0.2148   0.01153   0.00437  -0.0930   0.4456   0.0257
  -3.000   0.2393   0.01141   0.00419  -0.0923   0.4417   0.0259
  -2.750   0.2624   0.01112   0.00384  -0.0913   0.4380   0.0264
  -2.500   0.2857   0.01085   0.00353  -0.0903   0.4352   0.0269
  -2.250   0.3098   0.01069   0.00334  -0.0895   0.4324   0.0273
  -2.000   0.3337   0.01055   0.00318  -0.0887   0.4295   0.0277
  -1.750   0.3575   0.01044   0.00304  -0.0878   0.4265   0.0280
  -1.500   0.3813   0.01035   0.00292  -0.0869   0.4237   0.0283
  -1.250   0.4050   0.01028   0.00283  -0.0861   0.4208   0.0288
  -1.000   0.4293   0.01019   0.00271  -0.0853   0.4188   0.0293
  -0.750   0.4534   0.01011   0.00263  -0.0845   0.4163   0.0297
  -0.500   0.4774   0.01005   0.00255  -0.0837   0.4141   0.0302
  -0.250   0.5013   0.01001   0.00249  -0.0829   0.4117   0.0309
   0.000   0.5251   0.00999   0.00244  -0.0820   0.4095   0.0315
   0.250   0.5486   0.00998   0.00241  -0.0811   0.4072   0.0320
   0.500   0.5720   0.00995   0.00237  -0.0802   0.4052   0.0326
   0.750   0.5959   0.00990   0.00232  -0.0794   0.4040   0.0341
   1.000   0.6199   0.00987   0.00231  -0.0786   0.4024   0.0354
   1.250   0.6436   0.00986   0.00231  -0.0778   0.4007   0.0368
   1.500   0.6670   0.00986   0.00231  -0.0769   0.3990   0.0387
   1.750   0.6896   0.00987   0.00232  -0.0758   0.3970   0.0413
   2.000   0.7116   0.00987   0.00234  -0.0747   0.3950   0.0485
   2.500   0.7533   0.00982   0.00245  -0.0719   0.3912   0.1224
   2.750   0.7733   0.00973   0.00251  -0.0704   0.3896   0.1948
   3.000   0.7802   0.00901   0.00269  -0.0663   0.3885   0.5764
   3.500   1.0182   0.00938   0.00394  -0.1076   0.3797   0.9890
   3.750   1.0541   0.00952   0.00404  -0.1097   0.3770   0.9913
   4.000   1.0857   0.00967   0.00416  -0.1108   0.3744   0.9933
   4.250   1.1104   0.00974   0.00425  -0.1103   0.3726   0.9941
   4.500   1.1370   0.00981   0.00431  -0.1103   0.3708   0.9945
   4.750   1.1637   0.00988   0.00440  -0.1104   0.3692   0.9949
   5.000   1.1889   0.00997   0.00448  -0.1101   0.3674   0.9953
   5.250   1.2139   0.01006   0.00458  -0.1098   0.3656   0.9957
   5.500   1.2385   0.01016   0.00469  -0.1094   0.3638   0.9962
   5.750   1.2625   0.01029   0.00481  -0.1089   0.3616   0.9968
   6.000   1.2865   0.01041   0.00494  -0.1085   0.3596   0.9973
   6.250   1.3116   0.01048   0.00504  -0.1082   0.3565   0.9978
   6.500   1.3356   0.01060   0.00516  -0.1077   0.3511   0.9983
   6.750   1.3584   0.01074   0.00530  -0.1071   0.3474   0.9989
   7.000   1.3814   0.01087   0.00544  -0.1064   0.3428   0.9994
   7.250   1.4044   0.01100   0.00558  -0.1058   0.3367   0.9999
   7.500   1.4189   0.01119   0.00574  -0.1034   0.3295   1.0000
   7.750   1.4322   0.01135   0.00590  -0.1007   0.3212   1.0000
   8.000   1.4431   0.01159   0.00611  -0.0976   0.3109   1.0000
   8.250   1.4528   0.01187   0.00636  -0.0942   0.2997   1.0000
   8.500   1.4587   0.01230   0.00671  -0.0903   0.2818   1.0000
   8.750   1.4585   0.01293   0.00722  -0.0852   0.2600   1.0000
   9.000   1.4551   0.01372   0.00787  -0.0798   0.2351   1.0000
   9.250   1.4561   0.01441   0.00849  -0.0752   0.2187   1.0000
   9.500   1.4496   0.01542   0.00938  -0.0697   0.1942   1.0000
   9.750   1.4403   0.01665   0.01047  -0.0640   0.1669   1.0000
  10.000   1.4109   0.01897   0.01254  -0.0560   0.1213   1.0000
  10.250   1.3799   0.02191   0.01531  -0.0492   0.0791   1.0000
  10.500   1.3518   0.02530   0.01857  -0.0440   0.0404   1.0000
  10.750   1.3386   0.02812   0.02135  -0.0410   0.0204   1.0000
  11.000   1.3401   0.03000   0.02326  -0.0394   0.0170   1.0000
  11.250   1.3418   0.03194   0.02525  -0.0381   0.0149   1.0000
  11.500   1.3449   0.03384   0.02721  -0.0369   0.0138   1.0000
  11.750   1.3463   0.03598   0.02940  -0.0358   0.0128   1.0000
  12.000   1.3469   0.03823   0.03172  -0.0348   0.0121   1.0000
  12.250   1.3455   0.04073   0.03428  -0.0338   0.0111   1.0000
  12.500   1.3459   0.04313   0.03674  -0.0330   0.0108   1.0000
  12.750   1.3454   0.04563   0.03931  -0.0323   0.0102   1.0000
  13.000   1.3451   0.04817   0.04191  -0.0316   0.0099   1.0000
  13.250   1.3428   0.05098   0.04479  -0.0310   0.0096   1.0000
  13.500   1.3398   0.05393   0.04780  -0.0305   0.0089   1.0000
  13.750   1.3362   0.05696   0.05090  -0.0300   0.0086   1.0000
  14.000   1.3323   0.06011   0.05412  -0.0296   0.0083   1.0000
  14.250   1.3298   0.06315   0.05723  -0.0294   0.0081   1.0000
  14.500   1.3281   0.06616   0.06030  -0.0291   0.0079   1.0000
  14.750   1.3263   0.06916   0.06337  -0.0290   0.0076   1.0000
  15.000   1.3240   0.07226   0.06654  -0.0289   0.0073   1.0000
  15.250   1.3213   0.07549   0.06983  -0.0289   0.0071   1.0000
  15.500   1.3186   0.07873   0.07314  -0.0289   0.0070   1.0000
  15.750   1.3166   0.08190   0.07637  -0.0290   0.0069   1.0000
  16.000   1.3132   0.08528   0.07980  -0.0291   0.0066   1.0000
  16.250   1.3107   0.08856   0.08314  -0.0293   0.0064   1.0000
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