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GOE 615 AIRFOIL (goe615-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 615 AIRFOIL (goe615-il)
Reynolds number: 500,000
Max Cl/Cd: 104.09 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe615-il-500000.txt
Download as CSV file: xf-goe615-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 615 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.1736   0.08992   0.08759  -0.0768   0.9732   0.0383
  -9.750  -0.1575   0.08616   0.08383  -0.0786   0.9698   0.0387
  -9.500  -0.1406   0.08378   0.08145  -0.0799   0.9617   0.0390
  -9.250  -0.1185   0.08110   0.07876  -0.0829   0.9570   0.0394
  -9.000  -0.0982   0.07796   0.07560  -0.0868   0.9498   0.0401
  -8.750  -0.0981   0.06167   0.05924  -0.1143   0.9339   0.0442
  -8.500  -0.0704   0.05989   0.05743  -0.1162   0.9264   0.0445
  -8.250  -0.0475   0.05794   0.05542  -0.1189   0.9140   0.0450
  -8.000  -0.0345   0.05535   0.05277  -0.1219   0.8986   0.0454
  -7.750  -0.0281   0.05205   0.04937  -0.1249   0.8830   0.0460
  -7.500  -0.0773   0.03991   0.03640  -0.1320   0.8598   0.0505
  -7.250  -0.0786   0.03473   0.03104  -0.1313   0.8495   0.0512
  -7.000  -0.0584   0.03341   0.02973  -0.1309   0.8412   0.0518
  -6.750  -0.0715   0.02539   0.02075  -0.1275   0.8305   0.0434
  -6.500  -0.0555   0.02299   0.01808  -0.1263   0.8227   0.0428
  -6.250  -0.0386   0.02114   0.01594  -0.1248   0.8139   0.0427
  -6.000  -0.0179   0.01981   0.01430  -0.1236   0.8059   0.0432
  -5.750   0.0029   0.01857   0.01282  -0.1224   0.7970   0.0432
  -5.500   0.0260   0.01759   0.01159  -0.1214   0.7886   0.0435
  -5.250   0.0494   0.01685   0.01066  -0.1204   0.7797   0.0438
  -5.000   0.0735   0.01603   0.00962  -0.1196   0.7712   0.0442
  -4.750   0.0969   0.01482   0.00834  -0.1188   0.7619   0.0447
  -4.500   0.1220   0.01425   0.00771  -0.1181   0.7530   0.0456
  -4.250   0.1469   0.01383   0.00726  -0.1174   0.7425   0.0465
  -4.000   0.1721   0.01341   0.00675  -0.1167   0.7326   0.0473
  -3.750   0.1971   0.01300   0.00626  -0.1159   0.7215   0.0481
  -3.500   0.2220   0.01263   0.00581  -0.1151   0.7094   0.0489
  -3.250   0.2469   0.01234   0.00542  -0.1142   0.6964   0.0497
  -3.000   0.2717   0.01217   0.00513  -0.1133   0.6825   0.0504
  -2.750   0.2947   0.01160   0.00452  -0.1122   0.6689   0.0519
  -2.500   0.3189   0.01135   0.00425  -0.1114   0.6556   0.0534
  -2.250   0.3436   0.01117   0.00402  -0.1105   0.6434   0.0549
  -2.000   0.3680   0.01103   0.00379  -0.1097   0.6318   0.0564
  -1.750   0.3930   0.01092   0.00362  -0.1089   0.6207   0.0579
  -1.500   0.4171   0.01065   0.00331  -0.1080   0.6112   0.0603
  -1.250   0.4418   0.01055   0.00316  -0.1072   0.6018   0.0631
  -1.000   0.4674   0.01048   0.00305  -0.1066   0.5933   0.0664
  -0.750   0.4923   0.01036   0.00291  -0.1058   0.5858   0.0712
  -0.500   0.5181   0.01029   0.00283  -0.1053   0.5794   0.0778
  -0.250   0.5432   0.01014   0.00277  -0.1046   0.5730   0.1046
   0.000   0.5657   0.00975   0.00280  -0.1037   0.5671   0.2531
   0.250   0.5904   0.00957   0.00285  -0.1030   0.5618   0.3286
   0.500   0.6138   0.00935   0.00291  -0.1022   0.5559   0.4315
   0.750   0.6324   0.00892   0.00302  -0.1003   0.5507   0.6275
   1.000   0.7322   0.00839   0.00328  -0.1154   0.5430   0.9966
   1.250   0.7643   0.00851   0.00331  -0.1162   0.5369   1.0000
   1.500   0.7873   0.00866   0.00337  -0.1151   0.5314   1.0000
   1.750   0.8108   0.00873   0.00343  -0.1141   0.5261   1.0000
   2.000   0.8338   0.00884   0.00348  -0.1130   0.5200   1.0000
   2.250   0.8563   0.00899   0.00355  -0.1119   0.5132   1.0000
   2.500   0.8793   0.00907   0.00362  -0.1108   0.5061   1.0000
   2.750   0.9011   0.00923   0.00369  -0.1094   0.4980   1.0000
   3.000   0.9237   0.00930   0.00376  -0.1083   0.4893   1.0000
   3.250   0.9455   0.00945   0.00384  -0.1070   0.4814   1.0000
   3.500   0.9683   0.00953   0.00392  -0.1059   0.4730   1.0000
   3.750   0.9893   0.00969   0.00401  -0.1044   0.4638   1.0000
   4.000   1.0116   0.00979   0.00410  -0.1032   0.4528   1.0000
   4.250   1.0325   0.00993   0.00420  -0.1018   0.4404   1.0000
   4.500   1.0523   0.01011   0.00432  -0.1001   0.4243   1.0000
   4.750   1.0703   0.01034   0.00446  -0.0982   0.4034   1.0000
   5.000   1.0855   0.01068   0.00465  -0.0958   0.3788   1.0000
   5.250   1.1005   0.01107   0.00490  -0.0933   0.3574   1.0000
   5.500   1.1152   0.01146   0.00518  -0.0909   0.3402   1.0000
   5.750   1.1293   0.01182   0.00546  -0.0883   0.3270   1.0000
   6.000   1.1435   0.01219   0.00575  -0.0857   0.3163   1.0000
   6.250   1.1602   0.01250   0.00603  -0.0837   0.3071   1.0000
   6.500   1.1761   0.01284   0.00634  -0.0816   0.2991   1.0000
   6.750   1.1937   0.01315   0.00663  -0.0798   0.2914   1.0000
   7.000   1.2094   0.01354   0.00697  -0.0777   0.2840   1.0000
   7.250   1.2280   0.01383   0.00726  -0.0762   0.2769   1.0000
   7.500   1.2433   0.01425   0.00764  -0.0741   0.2698   1.0000
   7.750   1.2620   0.01455   0.00796  -0.0727   0.2635   1.0000
   8.000   1.2785   0.01495   0.00835  -0.0710   0.2569   1.0000
   8.250   1.2949   0.01537   0.00876  -0.0693   0.2510   1.0000
   8.500   1.3121   0.01576   0.00915  -0.0678   0.2435   1.0000
   8.750   1.3263   0.01630   0.00965  -0.0659   0.2373   1.0000
   9.000   1.3444   0.01668   0.01007  -0.0646   0.2313   1.0000
   9.250   1.3590   0.01723   0.01061  -0.0628   0.2244   1.0000
   9.500   1.3750   0.01774   0.01113  -0.0614   0.2186   1.0000
   9.750   1.3897   0.01833   0.01171  -0.0598   0.2112   1.0000
  10.000   1.4036   0.01898   0.01237  -0.0582   0.2043   1.0000
  10.250   1.4166   0.01971   0.01307  -0.0566   0.1950   1.0000
  10.500   1.4287   0.02051   0.01385  -0.0549   0.1844   1.0000
  10.750   1.4388   0.02147   0.01477  -0.0532   0.1730   1.0000
  11.000   1.4476   0.02255   0.01580  -0.0514   0.1608   1.0000
  11.250   1.4557   0.02372   0.01693  -0.0496   0.1491   1.0000
  11.500   1.4601   0.02519   0.01832  -0.0477   0.1318   1.0000
  11.750   1.4555   0.02738   0.02034  -0.0452   0.1058   1.0000
  12.000   1.4476   0.02993   0.02274  -0.0428   0.0820   1.0000
  12.250   1.4476   0.03199   0.02477  -0.0411   0.0742   1.0000
  12.500   1.4528   0.03371   0.02651  -0.0399   0.0708   1.0000
  12.750   1.4567   0.03558   0.02843  -0.0388   0.0683   1.0000
  13.000   1.4609   0.03749   0.03038  -0.0378   0.0666   1.0000
  13.250   1.4645   0.03952   0.03246  -0.0369   0.0652   1.0000
  13.500   1.4661   0.04182   0.03481  -0.0361   0.0635   1.0000
  13.750   1.4685   0.04408   0.03715  -0.0354   0.0626   1.0000
  14.000   1.4728   0.04622   0.03937  -0.0349   0.0617   1.0000
  14.250   1.4770   0.04841   0.04165  -0.0344   0.0612   1.0000
  14.500   1.4800   0.05079   0.04411  -0.0341   0.0604   1.0000
  14.750   1.4821   0.05329   0.04670  -0.0338   0.0597   1.0000
  15.000   1.4824   0.05605   0.04954  -0.0336   0.0590   1.0000
  15.250   1.4828   0.05885   0.05243  -0.0335   0.0584   1.0000
  15.500   1.4798   0.06210   0.05575  -0.0335   0.0575   1.0000
  15.750   1.4758   0.06549   0.05922  -0.0336   0.0567   1.0000
  16.000   1.4709   0.06905   0.06285  -0.0337   0.0558   1.0000
  16.250   1.4626   0.07309   0.06697  -0.0340   0.0548   1.0000
  16.500   1.4554   0.07705   0.07102  -0.0344   0.0541   1.0000
  16.750   1.4581   0.07976   0.07382  -0.0347   0.0536   1.0000
  17.000   1.4586   0.08280   0.07696  -0.0351   0.0529   1.0000
  17.250   1.4578   0.08604   0.08029  -0.0356   0.0521   1.0000
  17.500   1.4558   0.08948   0.08382  -0.0362   0.0513   1.0000
  17.750   1.4528   0.09311   0.08754  -0.0370   0.0504   1.0000
  18.000   1.4472   0.09712   0.09163  -0.0378   0.0495   1.0000
  18.250   1.4398   0.10146   0.09603  -0.0389   0.0484   1.0000
  18.500   1.4304   0.10616   0.10081  -0.0402   0.0475   1.0000
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