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GOE 676 (= M 12) AIRFOIL (goe676-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 676 (= M 12) AIRFOIL (goe676-il)
Reynolds number: 1,000,000
Max Cl/Cd: 97.61 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe676-il-1000000.txt
Download as CSV file: xf-goe676-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 676 (= M 12) 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
  ------ -------- --------- --------- -------- -------- --------
 -16.750  -1.2297   0.05938   0.05679  -0.0412   1.0000   0.0132
 -16.500  -1.2669   0.04836   0.04548  -0.0502   1.0000   0.0131
 -16.250  -1.2862   0.04255   0.03949  -0.0534   1.0000   0.0132
 -16.000  -1.2965   0.03879   0.03559  -0.0543   1.0000   0.0133
 -15.750  -1.3000   0.03617   0.03285  -0.0540   1.0000   0.0135
 -15.500  -1.2985   0.03421   0.03081  -0.0531   1.0000   0.0138
 -15.250  -1.2941   0.03262   0.02913  -0.0519   1.0000   0.0140
 -15.000  -1.2874   0.03130   0.02772  -0.0505   1.0000   0.0143
 -14.750  -1.2797   0.03010   0.02643  -0.0489   1.0000   0.0146
 -14.500  -1.2705   0.02905   0.02528  -0.0472   1.0000   0.0149
 -14.250  -1.2600   0.02811   0.02424  -0.0453   1.0000   0.0153
 -14.000  -1.2474   0.02728   0.02330  -0.0436   1.0000   0.0155
 -13.750  -1.2368   0.02604   0.02193  -0.0419   1.0000   0.0159
 -13.500  -1.2252   0.02482   0.02063  -0.0403   1.0000   0.0164
 -13.250  -1.2065   0.02418   0.01996  -0.0393   1.0000   0.0169
 -13.000  -1.1861   0.02367   0.01942  -0.0385   1.0000   0.0173
 -12.750  -1.1654   0.02315   0.01884  -0.0377   1.0000   0.0178
 -12.500  -1.1448   0.02259   0.01821  -0.0369   1.0000   0.0183
 -12.250  -1.1237   0.02203   0.01757  -0.0362   1.0000   0.0187
 -12.000  -1.1015   0.02157   0.01702  -0.0355   1.0000   0.0191
 -11.750  -1.0852   0.02042   0.01575  -0.0342   1.0000   0.0197
 -11.500  -1.0638   0.01989   0.01521  -0.0334   1.0000   0.0203
 -11.250  -1.0405   0.01961   0.01491  -0.0328   1.0000   0.0209
 -11.000  -1.0175   0.01931   0.01459  -0.0322   1.0000   0.0215
 -10.750  -0.9953   0.01893   0.01416  -0.0314   1.0000   0.0221
 -10.500  -0.9740   0.01853   0.01369  -0.0303   1.0000   0.0226
 -10.250  -0.9536   0.01821   0.01330  -0.0291   1.0000   0.0230
 -10.000  -0.9337   0.01800   0.01304  -0.0276   1.0000   0.0233
  -9.750  -0.9219   0.01676   0.01171  -0.0251   0.9998   0.0243
  -9.500  -0.8890   0.01638   0.01133  -0.0266   0.9978   0.0251
  -9.250  -0.8556   0.01605   0.01098  -0.0280   0.9958   0.0258
  -9.000  -0.8222   0.01564   0.01052  -0.0295   0.9941   0.0266
  -8.750  -0.7899   0.01524   0.01006  -0.0307   0.9914   0.0273
  -8.500  -0.7572   0.01498   0.00976  -0.0319   0.9876   0.0279
  -8.250  -0.7266   0.01413   0.00881  -0.0328   0.9838   0.0287
  -8.000  -0.6992   0.01346   0.00811  -0.0330   0.9769   0.0297
  -7.750  -0.6700   0.01313   0.00777  -0.0335   0.9706   0.0305
  -7.500  -0.6444   0.01286   0.00748  -0.0330   0.9613   0.0313
  -7.250  -0.6195   0.01255   0.00712  -0.0324   0.9520   0.0321
  -7.000  -0.5954   0.01225   0.00676  -0.0315   0.9417   0.0328
  -6.750  -0.5702   0.01202   0.00648  -0.0309   0.9311   0.0334
  -6.500  -0.5447   0.01182   0.00623  -0.0304   0.9209   0.0338
  -6.250  -0.5222   0.01111   0.00542  -0.0293   0.9097   0.0350
  -6.000  -0.4970   0.01075   0.00503  -0.0288   0.8985   0.0361
  -5.750  -0.4710   0.01052   0.00476  -0.0284   0.8882   0.0372
  -5.250  -0.4181   0.01010   0.00424  -0.0277   0.8674   0.0393
  -5.000  -0.3913   0.00992   0.00400  -0.0274   0.8576   0.0402
  -4.750  -0.3649   0.00968   0.00368  -0.0271   0.8473   0.0413
  -4.500  -0.3385   0.00937   0.00335  -0.0267   0.8371   0.0436
  -4.250  -0.3114   0.00922   0.00317  -0.0265   0.8271   0.0457
  -4.000  -0.2839   0.00910   0.00300  -0.0264   0.8166   0.0478
  -3.750  -0.2566   0.00892   0.00277  -0.0262   0.8058   0.0504
  -3.500  -0.2295   0.00874   0.00259  -0.0260   0.7949   0.0547
  -3.250  -0.2017   0.00866   0.00246  -0.0260   0.7836   0.0580
  -3.000  -0.1742   0.00846   0.00228  -0.0259   0.7726   0.0641
  -2.750  -0.1464   0.00837   0.00215  -0.0258   0.7611   0.0688
  -2.500  -0.1188   0.00823   0.00199  -0.0257   0.7484   0.0757
  -2.250  -0.0911   0.00813   0.00186  -0.0257   0.7343   0.0821
  -2.000  -0.0635   0.00799   0.00174  -0.0256   0.7192   0.0941
  -1.750  -0.0365   0.00779   0.00164  -0.0255   0.7034   0.1316
  -1.500  -0.0090   0.00768   0.00156  -0.0254   0.6883   0.1593
  -1.250   0.0181   0.00752   0.00147  -0.0254   0.6740   0.1933
  -1.000   0.0432   0.00704   0.00136  -0.0251   0.6614   0.3137
  -0.750   0.0677   0.00652   0.00128  -0.0247   0.6508   0.4590
  -0.500   0.0911   0.00598   0.00121  -0.0240   0.6400   0.6067
  -0.250   0.1141   0.00552   0.00119  -0.0230   0.6285   0.7452
   0.000   0.1387   0.00535   0.00126  -0.0221   0.6180   0.8254
   0.250   0.1648   0.00535   0.00132  -0.0215   0.6088   0.8653
   0.500   0.1918   0.00537   0.00137  -0.0211   0.6001   0.8884
   0.750   0.2185   0.00544   0.00142  -0.0207   0.5899   0.9056
   1.000   0.2451   0.00549   0.00147  -0.0202   0.5795   0.9187
   1.250   0.2720   0.00555   0.00152  -0.0198   0.5702   0.9286
   1.500   0.2984   0.00564   0.00156  -0.0193   0.5602   0.9384
   1.750   0.3252   0.00570   0.00162  -0.0189   0.5491   0.9460
   2.000   0.3511   0.00579   0.00166  -0.0183   0.5360   0.9543
   2.250   0.3779   0.00591   0.00174  -0.0179   0.5200   0.9624
   2.500   0.4044   0.00603   0.00181  -0.0174   0.5034   0.9702
   2.750   0.4359   0.00617   0.00188  -0.0182   0.4849   0.9735
   3.000   0.4677   0.00634   0.00196  -0.0191   0.4637   0.9768
   3.250   0.4982   0.00651   0.00205  -0.0197   0.4442   0.9806
   3.500   0.5320   0.00670   0.00216  -0.0211   0.4249   0.9836
   3.750   0.5711   0.00691   0.00229  -0.0237   0.4070   0.9849
   4.000   0.6073   0.00709   0.00241  -0.0257   0.3910   0.9863
   4.250   0.6405   0.00726   0.00252  -0.0270   0.3754   0.9877
   4.500   0.6729   0.00743   0.00263  -0.0282   0.3597   0.9893
   5.000   0.7354   0.00783   0.00289  -0.0301   0.3243   0.9930
   5.250   0.7676   0.00803   0.00303  -0.0312   0.3069   0.9943
   5.500   0.8010   0.00825   0.00318  -0.0327   0.2867   0.9953
   5.750   0.8336   0.00854   0.00335  -0.0340   0.2606   0.9965
   6.000   0.8643   0.00902   0.00362  -0.0352   0.2143   0.9979
   6.250   0.8914   0.00997   0.00413  -0.0359   0.1388   0.9994
   6.500   0.9179   0.01034   0.00442  -0.0360   0.1241   1.0000
   6.750   0.9383   0.01056   0.00464  -0.0347   0.1177   1.0000
   7.000   0.9579   0.01081   0.00487  -0.0333   0.1116   1.0000
   7.250   0.9778   0.01104   0.00510  -0.0318   0.1064   1.0000
   7.500   0.9980   0.01122   0.00530  -0.0305   0.1019   1.0000
   7.750   1.0170   0.01153   0.00557  -0.0289   0.0942   1.0000
   8.000   1.0375   0.01174   0.00578  -0.0276   0.0860   1.0000
   8.250   1.0550   0.01223   0.00610  -0.0259   0.0630   1.0000
   8.500   1.0702   0.01293   0.00664  -0.0239   0.0413   1.0000
   8.750   1.0889   0.01345   0.00713  -0.0225   0.0343   1.0000
   9.000   1.1094   0.01388   0.00756  -0.0214   0.0309   1.0000
   9.250   1.1296   0.01437   0.00806  -0.0202   0.0277   1.0000
   9.500   1.1508   0.01479   0.00849  -0.0193   0.0256   1.0000
   9.750   1.1694   0.01542   0.00913  -0.0180   0.0231   1.0000
  10.000   1.1910   0.01580   0.00955  -0.0172   0.0220   1.0000
  10.250   1.2114   0.01626   0.01004  -0.0163   0.0206   1.0000
  10.500   1.2286   0.01694   0.01074  -0.0149   0.0191   1.0000
  10.750   1.2477   0.01746   0.01130  -0.0138   0.0183   1.0000
  11.000   1.2665   0.01795   0.01183  -0.0126   0.0174   1.0000
  11.250   1.2831   0.01850   0.01241  -0.0112   0.0167   1.0000
  11.500   1.2958   0.01919   0.01313  -0.0091   0.0159   1.0000
  11.750   1.3025   0.02027   0.01428  -0.0064   0.0152   1.0000
  12.000   1.3174   0.02092   0.01499  -0.0050   0.0148   1.0000
  12.250   1.3308   0.02170   0.01583  -0.0035   0.0144   1.0000
  12.500   1.3432   0.02258   0.01677  -0.0021   0.0140   1.0000
  12.750   1.3552   0.02352   0.01776  -0.0007   0.0135   1.0000
  13.000   1.3662   0.02458   0.01887   0.0005   0.0131   1.0000
  13.250   1.3740   0.02595   0.02030   0.0018   0.0127   1.0000
  13.500   1.3738   0.02805   0.02249   0.0034   0.0122   1.0000
  13.750   1.3804   0.02971   0.02423   0.0044   0.0120   1.0000
  14.000   1.3892   0.03123   0.02583   0.0050   0.0118   1.0000
  14.250   1.3959   0.03299   0.02767   0.0056   0.0115   1.0000
  14.500   1.4014   0.03495   0.02972   0.0061   0.0113   1.0000
  14.750   1.4059   0.03707   0.03192   0.0064   0.0111   1.0000
  15.000   1.4090   0.03941   0.03435   0.0066   0.0109   1.0000
  15.250   1.4113   0.04194   0.03696   0.0066   0.0107   1.0000
  15.500   1.4123   0.04466   0.03977   0.0064   0.0105   1.0000
  15.750   1.4120   0.04761   0.04281   0.0061   0.0103   1.0000
  16.000   1.4095   0.05089   0.04617   0.0056   0.0102   1.0000
  16.250   1.4041   0.05460   0.04997   0.0049   0.0100   1.0000
  16.500   1.3962   0.05875   0.05422   0.0039   0.0099   1.0000
  16.750   1.3856   0.06341   0.05898   0.0027   0.0098   1.0000
  17.000   1.3715   0.06861   0.06429   0.0013   0.0096   1.0000
  17.250   1.3556   0.07422   0.07003  -0.0004   0.0095   1.0000
  17.500   1.3477   0.07888   0.07479  -0.0020   0.0095   1.0000
  17.750   1.3411   0.08342   0.07944  -0.0036   0.0094   1.0000
  18.000   1.3336   0.08820   0.08432  -0.0054   0.0093   1.0000
  18.250   1.3252   0.09321   0.08944  -0.0074   0.0093   1.0000
  18.500   1.3161   0.09834   0.09467  -0.0094   0.0092   1.0000
  18.750   1.3064   0.10362   0.10005  -0.0116   0.0092   1.0000
  19.000   1.2966   0.10901   0.10554  -0.0139   0.0091   1.0000
  19.250   1.2869   0.11447   0.11110  -0.0163   0.0090   1.0000
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