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GOE 670 AIRFOIL (goe670-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 670 AIRFOIL (goe670-il)
Reynolds number: 500,000
Max Cl/Cd: 81.9 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe670-il-500000-n5.txt
Download as CSV file: xf-goe670-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 670 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -15.250  -0.4726   0.16345   0.16085  -0.0187   1.0000   0.0090
 -15.000  -0.4682   0.15997   0.15738  -0.0199   1.0000   0.0091
 -11.500  -0.8265   0.03204   0.02894  -0.0828   0.9871   0.0195
 -11.250  -0.7922   0.03286   0.02986  -0.0836   0.9860   0.0202
 -11.000  -0.7611   0.03307   0.03010  -0.0844   0.9841   0.0207
 -10.750  -0.7366   0.03206   0.02901  -0.0852   0.9807   0.0213
 -10.500  -0.7169   0.02919   0.02584  -0.0868   0.9776   0.0221
 -10.250  -0.6942   0.02669   0.02303  -0.0884   0.9756   0.0230
 -10.000  -0.6746   0.02502   0.02107  -0.0883   0.9709   0.0238
  -9.750  -0.6493   0.02363   0.01943  -0.0890   0.9683   0.0244
  -9.500  -0.6231   0.02215   0.01769  -0.0900   0.9664   0.0250
  -9.250  -0.5970   0.02098   0.01640  -0.0906   0.9642   0.0258
  -9.000  -0.5725   0.02051   0.01587  -0.0904   0.9600   0.0264
  -8.750  -0.5437   0.02014   0.01545  -0.0910   0.9574   0.0271
  -8.500  -0.5146   0.01950   0.01469  -0.0917   0.9552   0.0278
  -8.250  -0.4877   0.01876   0.01381  -0.0920   0.9523   0.0285
  -8.000  -0.4640   0.01795   0.01283  -0.0916   0.9480   0.0291
  -7.750  -0.4368   0.01724   0.01197  -0.0918   0.9449   0.0298
  -7.500  -0.4084   0.01645   0.01102  -0.0922   0.9425   0.0303
  -7.250  -0.3840   0.01575   0.01015  -0.0917   0.9380   0.0307
  -7.000  -0.3581   0.01512   0.00940  -0.0915   0.9338   0.0310
  -6.750  -0.3300   0.01455   0.00870  -0.0917   0.9307   0.0313
  -6.500  -0.3040   0.01377   0.00779  -0.0915   0.9271   0.0319
  -6.250  -0.2802   0.01311   0.00705  -0.0908   0.9218   0.0328
  -6.000  -0.2529   0.01264   0.00651  -0.0907   0.9178   0.0336
  -5.750  -0.2246   0.01223   0.00603  -0.0909   0.9148   0.0342
  -5.500  -0.2003   0.01189   0.00564  -0.0901   0.9094   0.0347
  -5.250  -0.1737   0.01154   0.00524  -0.0898   0.9045   0.0354
  -5.000  -0.1456   0.01121   0.00483  -0.0898   0.9009   0.0360
  -4.750  -0.1204   0.01093   0.00451  -0.0893   0.8960   0.0368
  -4.500  -0.0942   0.01065   0.00418  -0.0888   0.8910   0.0375
  -4.250  -0.0668   0.01039   0.00386  -0.0887   0.8867   0.0383
  -4.000  -0.0403   0.01016   0.00359  -0.0883   0.8822   0.0391
  -3.750  -0.0143   0.00996   0.00336  -0.0878   0.8771   0.0397
  -3.500   0.0122   0.00966   0.00304  -0.0875   0.8723   0.0422
  -3.250   0.0391   0.00947   0.00285  -0.0872   0.8678   0.0448
  -3.000   0.0650   0.00931   0.00268  -0.0867   0.8617   0.0474
  -2.750   0.0923   0.00916   0.00248  -0.0864   0.8553   0.0497
  -2.500   0.1177   0.00898   0.00232  -0.0858   0.8464   0.0548
  -2.250   0.1446   0.00885   0.00217  -0.0855   0.8381   0.0606
  -2.000   0.1703   0.00872   0.00207  -0.0849   0.8289   0.0685
  -1.750   0.1966   0.00863   0.00198  -0.0844   0.8188   0.0768
  -1.500   0.2229   0.00856   0.00190  -0.0839   0.8070   0.0852
  -1.250   0.2486   0.00850   0.00180  -0.0833   0.7920   0.0916
  -1.000   0.2737   0.00847   0.00173  -0.0826   0.7706   0.0990
  -0.750   0.2980   0.00848   0.00163  -0.0816   0.7418   0.1044
  -0.500   0.3207   0.00853   0.00155  -0.0804   0.7051   0.1119
  -0.250   0.3433   0.00865   0.00152  -0.0791   0.6735   0.1180
   0.000   0.3665   0.00870   0.00150  -0.0780   0.6512   0.1267
   0.500   0.4154   0.00878   0.00151  -0.0765   0.6229   0.1471
   0.750   0.4396   0.00873   0.00154  -0.0757   0.6113   0.1816
   1.000   0.4636   0.00857   0.00160  -0.0749   0.6013   0.2656
   1.250   0.4870   0.00842   0.00164  -0.0741   0.5913   0.3470
   1.500   0.4923   0.00710   0.00176  -0.0693   0.5821   0.8361
   1.750   0.5648   0.00717   0.00200  -0.0790   0.5618   0.9600
   2.000   0.6041   0.00742   0.00209  -0.0815   0.5223   0.9785
   2.250   0.6358   0.00787   0.00222  -0.0825   0.4544   0.9898
   2.500   0.6709   0.00836   0.00241  -0.0844   0.3975   0.9979
   2.750   0.6978   0.00872   0.00258  -0.0845   0.3584   1.0000
   3.000   0.7167   0.00904   0.00273  -0.0827   0.3256   1.0000
   3.250   0.7359   0.00934   0.00289  -0.0810   0.2976   1.0000
   3.500   0.7560   0.00960   0.00305  -0.0794   0.2772   1.0000
   3.750   0.7767   0.00983   0.00322  -0.0779   0.2623   1.0000
   4.000   0.7976   0.01006   0.00338  -0.0765   0.2500   1.0000
   4.250   0.8184   0.01030   0.00356  -0.0751   0.2402   1.0000
   4.500   0.8401   0.01048   0.00374  -0.0739   0.2323   1.0000
   4.750   0.8610   0.01072   0.00393  -0.0725   0.2239   1.0000
   5.000   0.8830   0.01090   0.00412  -0.0713   0.2187   1.0000
   5.250   0.9045   0.01111   0.00432  -0.0700   0.2128   1.0000
   5.500   0.9256   0.01134   0.00453  -0.0687   0.2038   1.0000
   5.750   0.9460   0.01162   0.00475  -0.0672   0.1929   1.0000
   6.000   0.9675   0.01183   0.00496  -0.0660   0.1836   1.0000
   6.250   0.9885   0.01207   0.00518  -0.0647   0.1754   1.0000
   6.500   1.0089   0.01234   0.00542  -0.0633   0.1630   1.0000
   6.750   1.0286   0.01267   0.00568  -0.0618   0.1443   1.0000
   7.000   1.0446   0.01323   0.00604  -0.0597   0.1084   1.0000
   7.250   1.0595   0.01388   0.00652  -0.0574   0.0829   1.0000
   7.500   1.0769   0.01436   0.00696  -0.0556   0.0690   1.0000
   8.000   1.1036   0.01584   0.00819  -0.0506   0.0260   1.0000
   8.250   1.1201   0.01628   0.00865  -0.0486   0.0223   1.0000
   8.500   1.1351   0.01680   0.00919  -0.0463   0.0192   1.0000
   8.750   1.1517   0.01723   0.00967  -0.0444   0.0177   1.0000
   9.000   1.1678   0.01771   0.01020  -0.0424   0.0164   1.0000
   9.250   1.1831   0.01826   0.01078  -0.0404   0.0152   1.0000
   9.500   1.1968   0.01893   0.01148  -0.0381   0.0138   1.0000
   9.750   1.2124   0.01946   0.01208  -0.0362   0.0131   1.0000
  10.000   1.2271   0.02005   0.01274  -0.0343   0.0126   1.0000
  10.250   1.2412   0.02068   0.01343  -0.0323   0.0119   1.0000
  10.500   1.2547   0.02136   0.01417  -0.0303   0.0113   1.0000
  10.750   1.2665   0.02216   0.01503  -0.0281   0.0109   1.0000
  11.000   1.2760   0.02312   0.01605  -0.0257   0.0104   1.0000
  11.250   1.2843   0.02416   0.01717  -0.0233   0.0100   1.0000
  11.500   1.2948   0.02507   0.01817  -0.0212   0.0097   1.0000
  11.750   1.3043   0.02607   0.01926  -0.0192   0.0094   1.0000
  12.000   1.3139   0.02708   0.02035  -0.0173   0.0090   1.0000
  12.250   1.3210   0.02830   0.02166  -0.0152   0.0088   1.0000
  12.500   1.3279   0.02957   0.02303  -0.0133   0.0086   1.0000
  12.750   1.3379   0.03064   0.02416  -0.0118   0.0082   1.0000
  13.000   1.3413   0.03227   0.02588  -0.0099   0.0080   1.0000
  13.250   1.3461   0.03384   0.02753  -0.0084   0.0078   1.0000
  13.500   1.3479   0.03574   0.02953  -0.0068   0.0076   1.0000
  13.750   1.3468   0.03799   0.03188  -0.0053   0.0075   1.0000
  14.000   1.3417   0.04076   0.03476  -0.0040   0.0073   1.0000
  14.250   1.3448   0.04285   0.03697  -0.0033   0.0071   1.0000
  14.500   1.3419   0.04570   0.03994  -0.0027   0.0071   1.0000
  14.750   1.3402   0.04858   0.04295  -0.0024   0.0070   1.0000
  15.000   1.3363   0.05185   0.04636  -0.0024   0.0069   1.0000
  15.250   1.3334   0.05515   0.04979  -0.0027   0.0068   1.0000
  15.500   1.3274   0.05900   0.05377  -0.0032   0.0068   1.0000
  15.750   1.3217   0.06293   0.05783  -0.0040   0.0066   1.0000
  16.000   1.3152   0.06715   0.06218  -0.0051   0.0065   1.0000
  16.250   1.3071   0.07176   0.06692  -0.0065   0.0065   1.0000
  16.500   1.2960   0.07698   0.07228  -0.0083   0.0064   1.0000
  16.750   1.2879   0.08200   0.07743  -0.0103   0.0063   1.0000
  17.000   1.2764   0.08766   0.08322  -0.0125   0.0064   1.0000
  17.250   1.2676   0.09310   0.08878  -0.0150   0.0062   1.0000
  17.500   1.2556   0.09912   0.09493  -0.0176   0.0062   1.0000
  17.750   1.2450   0.10505   0.10097  -0.0204   0.0061   1.0000
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