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GOE 478 AIRFOIL (goe478-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 478 AIRFOIL (goe478-il)
Reynolds number: 1,000,000
Max Cl/Cd: 125.54 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe478-il-1000000.txt
Download as CSV file: xf-goe478-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 478 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
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.6440   0.03653   0.03394  -0.1126   0.9833   0.0279
 -11.500  -0.6489   0.03199   0.02908  -0.1147   0.9709   0.0280
 -11.250  -0.6369   0.02918   0.02601  -0.1160   0.9596   0.0283
 -11.000  -0.6138   0.02625   0.02279  -0.1190   0.9512   0.0285
 -10.750  -0.5826   0.02393   0.02019  -0.1224   0.9423   0.0287
 -10.500  -0.5528   0.02208   0.01807  -0.1248   0.9284   0.0289
 -10.250  -0.5265   0.02077   0.01652  -0.1258   0.9109   0.0291
 -10.000  -0.5059   0.01981   0.01534  -0.1251   0.8918   0.0293
  -9.750  -0.4873   0.01909   0.01441  -0.1238   0.8728   0.0294
  -9.250  -0.4490   0.01798   0.01296  -0.1209   0.8398   0.0297
  -9.000  -0.4320   0.01686   0.01165  -0.1193   0.8269   0.0300
  -8.750  -0.4137   0.01586   0.01052  -0.1179   0.8158   0.0303
  -8.500  -0.3924   0.01525   0.00982  -0.1167   0.8059   0.0305
  -8.250  -0.3698   0.01482   0.00932  -0.1158   0.7978   0.0308
  -8.000  -0.3463   0.01441   0.00886  -0.1150   0.7912   0.0311
  -7.750  -0.3225   0.01406   0.00843  -0.1142   0.7850   0.0314
  -7.500  -0.2981   0.01375   0.00807  -0.1135   0.7797   0.0318
  -7.250  -0.2735   0.01337   0.00763  -0.1128   0.7750   0.0322
  -7.000  -0.2490   0.01300   0.00720  -0.1121   0.7701   0.0325
  -6.750  -0.2245   0.01267   0.00679  -0.1114   0.7651   0.0328
  -6.500  -0.1993   0.01233   0.00640  -0.1108   0.7613   0.0331
  -6.250  -0.1738   0.01200   0.00604  -0.1102   0.7581   0.0334
  -6.000  -0.1480   0.01173   0.00572  -0.1097   0.7548   0.0337
  -5.750  -0.1224   0.01143   0.00537  -0.1091   0.7514   0.0340
  -5.500  -0.0990   0.01090   0.00479  -0.1083   0.7475   0.0346
  -5.250  -0.0733   0.01063   0.00451  -0.1077   0.7437   0.0352
  -5.000  -0.0471   0.01040   0.00428  -0.1073   0.7409   0.0358
  -4.750  -0.0208   0.01018   0.00406  -0.1068   0.7377   0.0364
  -4.500   0.0055   0.00999   0.00384  -0.1063   0.7343   0.0370
  -4.250   0.0318   0.00983   0.00364  -0.1058   0.7303   0.0377
  -4.000   0.0589   0.00974   0.00351  -0.1055   0.7260   0.0383
  -3.750   0.0842   0.00941   0.00318  -0.1049   0.7234   0.0394
  -3.500   0.1108   0.00922   0.00301  -0.1044   0.7203   0.0404
  -3.250   0.1375   0.00907   0.00286  -0.1040   0.7170   0.0415
  -3.000   0.1643   0.00895   0.00272  -0.1036   0.7133   0.0427
  -2.750   0.1907   0.00881   0.00254  -0.1031   0.7090   0.0442
  -2.500   0.2173   0.00865   0.00240  -0.1027   0.7053   0.0462
  -2.250   0.2441   0.00852   0.00229  -0.1022   0.7014   0.0483
  -2.000   0.2705   0.00836   0.00214  -0.1017   0.6971   0.0518
  -1.750   0.2967   0.00823   0.00202  -0.1012   0.6924   0.0572
  -1.500   0.3227   0.00808   0.00192  -0.1007   0.6876   0.0700
  -1.250   0.3488   0.00790   0.00188  -0.1002   0.6825   0.0994
  -1.000   0.3752   0.00782   0.00182  -0.0997   0.6759   0.1110
  -0.750   0.4011   0.00775   0.00177  -0.0991   0.6690   0.1210
  -0.500   0.4276   0.00765   0.00172  -0.0986   0.6609   0.1322
  -0.250   0.4529   0.00758   0.00168  -0.0979   0.6514   0.1515
   0.000   0.4781   0.00750   0.00167  -0.0972   0.6376   0.1813
   0.250   0.5022   0.00750   0.00165  -0.0962   0.6163   0.1988
   0.500   0.5235   0.00760   0.00165  -0.0947   0.5795   0.2133
   0.750   0.5442   0.00777   0.00170  -0.0931   0.5493   0.2286
   1.000   0.5668   0.00787   0.00177  -0.0919   0.5311   0.2478
   1.500   0.6085   0.00746   0.00192  -0.0892   0.5086   0.4854
   1.750   0.6227   0.00703   0.00205  -0.0863   0.4991   0.6986
   2.000   0.6371   0.00664   0.00219  -0.0831   0.4907   0.8818
   2.250   0.7039   0.00686   0.00245  -0.0914   0.4777   0.9677
   2.500   0.7517   0.00702   0.00257  -0.0956   0.4694   0.9822
   3.000   0.8401   0.00736   0.00280  -0.1026   0.4534   0.9959
   3.250   0.8883   0.00754   0.00290  -0.1070   0.4448   0.9999
   3.500   0.9107   0.00762   0.00296  -0.1058   0.4399   1.0000
   3.750   0.9319   0.00769   0.00303  -0.1043   0.4343   1.0000
   4.000   0.9516   0.00782   0.00311  -0.1026   0.4277   1.0000
   4.250   0.9722   0.00792   0.00320  -0.1010   0.4216   1.0000
   4.500   0.9930   0.00802   0.00328  -0.0995   0.4144   1.0000
   4.750   1.0119   0.00818   0.00339  -0.0975   0.4069   1.0000
   5.000   1.0335   0.00827   0.00348  -0.0962   0.4000   1.0000
   5.250   1.0524   0.00844   0.00359  -0.0943   0.3907   1.0000
   5.500   1.0734   0.00855   0.00370  -0.0928   0.3830   1.0000
   5.750   1.0923   0.00873   0.00383  -0.0909   0.3737   1.0000
   6.000   1.1125   0.00888   0.00395  -0.0893   0.3634   1.0000
   6.250   1.1308   0.00909   0.00410  -0.0873   0.3509   1.0000
   6.500   1.1485   0.00932   0.00428  -0.0853   0.3375   1.0000
   6.750   1.1647   0.00958   0.00447  -0.0829   0.3221   1.0000
   7.000   1.1781   0.00987   0.00467  -0.0800   0.3044   1.0000
   7.250   1.1902   0.01021   0.00492  -0.0769   0.2837   1.0000
   7.500   1.2012   0.01063   0.00523  -0.0737   0.2615   1.0000
   7.750   1.2128   0.01109   0.00557  -0.0707   0.2409   1.0000
   8.000   1.2259   0.01153   0.00592  -0.0680   0.2232   1.0000
   8.250   1.2395   0.01198   0.00629  -0.0656   0.2073   1.0000
   8.500   1.2536   0.01244   0.00668  -0.0632   0.1935   1.0000
   8.750   1.2683   0.01289   0.00707  -0.0610   0.1812   1.0000
   9.000   1.2839   0.01332   0.00745  -0.0590   0.1705   1.0000
   9.250   1.2993   0.01378   0.00787  -0.0571   0.1608   1.0000
   9.750   1.3296   0.01477   0.00879  -0.0533   0.1428   1.0000
  10.000   1.3442   0.01532   0.00931  -0.0515   0.1346   1.0000
  10.250   1.3584   0.01591   0.00986  -0.0496   0.1265   1.0000
  10.500   1.3731   0.01650   0.01043  -0.0479   0.1189   1.0000
  10.750   1.3860   0.01721   0.01110  -0.0461   0.1109   1.0000
  11.000   1.3995   0.01791   0.01178  -0.0444   0.1034   1.0000
  11.250   1.4123   0.01867   0.01252  -0.0427   0.0962   1.0000
  11.500   1.4236   0.01956   0.01337  -0.0409   0.0887   1.0000
  11.750   1.4350   0.02046   0.01425  -0.0392   0.0823   1.0000
  12.000   1.4465   0.02139   0.01517  -0.0376   0.0770   1.0000
  12.250   1.4564   0.02245   0.01621  -0.0360   0.0727   1.0000
  12.500   1.4684   0.02340   0.01720  -0.0346   0.0699   1.0000
  12.750   1.4796   0.02443   0.01824  -0.0333   0.0676   1.0000
  13.000   1.4887   0.02563   0.01945  -0.0318   0.0653   1.0000
  13.250   1.4972   0.02692   0.02077  -0.0304   0.0634   1.0000
  13.500   1.5093   0.02797   0.02187  -0.0294   0.0622   1.0000
  13.750   1.5190   0.02921   0.02316  -0.0282   0.0610   1.0000
  14.000   1.5277   0.03055   0.02453  -0.0271   0.0595   1.0000
  14.250   1.5340   0.03213   0.02612  -0.0259   0.0577   1.0000
  14.500   1.5383   0.03392   0.02795  -0.0246   0.0563   1.0000
  14.750   1.5486   0.03521   0.02931  -0.0238   0.0555   1.0000
  15.000   1.5569   0.03671   0.03086  -0.0229   0.0547   1.0000
  15.250   1.5641   0.03834   0.03255  -0.0221   0.0538   1.0000
  15.500   1.5699   0.04012   0.03438  -0.0213   0.0530   1.0000
  15.750   1.5741   0.04210   0.03641  -0.0205   0.0521   1.0000
  16.000   1.5756   0.04439   0.03874  -0.0197   0.0511   1.0000
  16.250   1.5743   0.04702   0.04144  -0.0190   0.0503   1.0000
  16.500   1.5777   0.04925   0.04373  -0.0185   0.0496   1.0000
  16.750   1.5844   0.05118   0.04573  -0.0182   0.0490   1.0000
  17.000   1.5871   0.05357   0.04820  -0.0179   0.0486   1.0000
  17.250   1.5906   0.05592   0.05062  -0.0177   0.0478   1.0000
  17.500   1.5926   0.05850   0.05327  -0.0176   0.0473   1.0000
  17.750   1.5937   0.06123   0.05606  -0.0176   0.0466   1.0000
  18.000   1.5929   0.06421   0.05909  -0.0177   0.0458   1.0000
  18.250   1.5898   0.06751   0.06245  -0.0179   0.0452   1.0000
  18.500   1.5816   0.07146   0.06648  -0.0183   0.0443   1.0000
  18.750   1.5775   0.07496   0.07006  -0.0187   0.0439   1.0000
  19.000   1.5794   0.07772   0.07289  -0.0190   0.0434   1.0000
  19.250   1.5803   0.08056   0.07581  -0.0194   0.0429   1.0000
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