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GOE 744 AIRFOIL (goe744-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 744 AIRFOIL (goe744-il)
Reynolds number: 1,000,000
Max Cl/Cd: 114.92 at α=8.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe744-il-1000000-n5.txt
Download as CSV file: xf-goe744-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 744 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.2122   0.08720   0.08375   0.0008   0.4636   0.0186
  -7.750  -0.2101   0.08418   0.08074  -0.0007   0.4619   0.0187
  -7.250  -0.2150   0.07830   0.07489  -0.0032   0.4585   0.0188
  -6.250  -0.3253   0.02148   0.01636  -0.0204   0.4593   0.0217
  -6.000  -0.3059   0.01910   0.01361  -0.0193   0.4579   0.0220
  -5.750  -0.2822   0.01778   0.01207  -0.0186   0.4563   0.0222
  -5.500  -0.2572   0.01678   0.01089  -0.0179   0.4543   0.0224
  -5.250  -0.2313   0.01596   0.00992  -0.0173   0.4524   0.0226
  -5.000  -0.2046   0.01530   0.00911  -0.0169   0.4502   0.0227
  -4.750  -0.1776   0.01471   0.00840  -0.0164   0.4478   0.0229
  -4.500  -0.1502   0.01422   0.00779  -0.0160   0.4452   0.0231
  -4.250  -0.1225   0.01378   0.00725  -0.0157   0.4425   0.0232
  -4.000  -0.0946   0.01340   0.00679  -0.0154   0.4405   0.0233
  -3.750  -0.0664   0.01306   0.00638  -0.0151   0.4389   0.0234
  -3.500  -0.0384   0.01267   0.00592  -0.0148   0.4368   0.0236
  -3.250  -0.0104   0.01227   0.00547  -0.0145   0.4343   0.0238
  -3.000   0.0180   0.01200   0.00517  -0.0143   0.4318   0.0241
  -2.750   0.0466   0.01180   0.00493  -0.0141   0.4294   0.0243
  -2.500   0.0753   0.01164   0.00475  -0.0139   0.4266   0.0246
  -2.250   0.1041   0.01149   0.00457  -0.0138   0.4237   0.0249
  -2.000   0.1328   0.01132   0.00438  -0.0136   0.4217   0.0252
  -1.750   0.1615   0.01113   0.00418  -0.0135   0.4195   0.0255
  -1.500   0.1902   0.01096   0.00398  -0.0133   0.4168   0.0258
  -1.250   0.2189   0.01080   0.00379  -0.0132   0.4137   0.0261
  -1.000   0.2476   0.01067   0.00362  -0.0131   0.4105   0.0264
  -0.750   0.2763   0.01056   0.00348  -0.0130   0.4073   0.0267
  -0.500   0.3050   0.01044   0.00335  -0.0129   0.4051   0.0269
  -0.250   0.3335   0.01027   0.00319  -0.0127   0.4021   0.0273
   0.000   0.3621   0.01017   0.00308  -0.0126   0.3986   0.0278
   0.250   0.3907   0.01011   0.00301  -0.0125   0.3951   0.0283
   0.500   0.4192   0.01007   0.00295  -0.0125   0.3913   0.0288
   0.750   0.4478   0.01001   0.00289  -0.0124   0.3882   0.0294
   1.000   0.4764   0.00996   0.00284  -0.0123   0.3846   0.0300
   1.250   0.5050   0.00994   0.00281  -0.0123   0.3806   0.0307
   1.500   0.5332   0.00991   0.00278  -0.0122   0.3767   0.0317
   1.750   0.5616   0.00990   0.00277  -0.0122   0.3735   0.0327
   2.000   0.5900   0.00989   0.00277  -0.0121   0.3701   0.0338
   2.250   0.6183   0.00989   0.00277  -0.0121   0.3659   0.0349
   2.500   0.6464   0.00992   0.00279  -0.0121   0.3618   0.0364
   2.750   0.6745   0.00996   0.00283  -0.0120   0.3583   0.0384
   3.000   0.7027   0.00997   0.00286  -0.0120   0.3554   0.0407
   3.250   0.7309   0.01000   0.00290  -0.0120   0.3519   0.0439
   3.500   0.7588   0.01005   0.00296  -0.0120   0.3478   0.0479
   3.750   0.7864   0.01014   0.00304  -0.0120   0.3433   0.0525
   4.000   0.8142   0.01017   0.00310  -0.0119   0.3400   0.0609
   4.250   0.8406   0.01011   0.00320  -0.0117   0.3360   0.1296
   4.500   0.8674   0.01015   0.00335  -0.0116   0.3320   0.1869
   4.750   0.8947   0.01026   0.00349  -0.0116   0.3279   0.2061
   5.000   0.9220   0.01033   0.00360  -0.0116   0.3250   0.2277
   5.250   0.9491   0.01038   0.00373  -0.0115   0.3216   0.2595
   5.500   0.9570   0.00941   0.00388  -0.0079   0.3185   0.7765
   6.500   1.1382   0.01010   0.00496  -0.0232   0.2998   0.9847
   6.750   1.1724   0.01037   0.00519  -0.0249   0.2957   0.9864
   7.000   1.2039   0.01054   0.00537  -0.0259   0.2928   0.9877
   7.250   1.2343   0.01075   0.00557  -0.0268   0.2893   0.9890
   7.500   1.2644   0.01102   0.00581  -0.0276   0.2854   0.9906
   7.750   1.2939   0.01134   0.00612  -0.0285   0.2813   0.9924
   8.000   1.3249   0.01157   0.00635  -0.0296   0.2785   0.9934
   8.250   1.3560   0.01180   0.00657  -0.0307   0.2754   0.9940
   8.500   1.3860   0.01208   0.00685  -0.0317   0.2715   0.9947
   8.750   1.4174   0.01244   0.00720  -0.0332   0.2672   0.9957
   9.000   1.4475   0.01277   0.00752  -0.0344   0.2638   0.9967
   9.250   1.4766   0.01305   0.00782  -0.0353   0.2610   0.9974
   9.500   1.5074   0.01338   0.00816  -0.0367   0.2579   0.9985
   9.750   1.5389   0.01378   0.00857  -0.0383   0.2546   0.9995
  10.000   1.5657   0.01428   0.00906  -0.0392   0.2512   1.0000
  10.250   1.5849   0.01474   0.00954  -0.0386   0.2488   1.0000
  10.500   1.6035   0.01519   0.01003  -0.0379   0.2468   1.0000
  10.750   1.6197   0.01577   0.01064  -0.0370   0.2443   1.0000
  11.000   1.6310   0.01683   0.01174  -0.0364   0.2414   1.0000
  11.250   1.6224   0.01840   0.01336  -0.0333   0.2394   1.0000
  11.500   1.6131   0.02015   0.01514  -0.0303   0.2364   1.0000
  11.750   1.6126   0.02170   0.01672  -0.0284   0.2340   1.0000
  12.000   1.6166   0.02309   0.01815  -0.0271   0.2313   1.0000
  12.250   1.6178   0.02477   0.01986  -0.0258   0.2279   1.0000
  12.500   1.6150   0.02685   0.02196  -0.0245   0.2243   1.0000
  12.750   1.6076   0.02939   0.02451  -0.0233   0.2200   1.0000
  13.000   1.6113   0.03108   0.02625  -0.0225   0.2178   1.0000
  13.250   1.6141   0.03288   0.02809  -0.0217   0.2158   1.0000
  13.500   1.6154   0.03483   0.03008  -0.0210   0.2132   1.0000
  13.750   1.6142   0.03706   0.03235  -0.0203   0.2110   1.0000
  14.000   1.6112   0.03957   0.03488  -0.0198   0.2082   1.0000
  14.250   1.6092   0.04203   0.03737  -0.0194   0.2049   1.0000
  14.500   1.6130   0.04401   0.03940  -0.0191   0.2028   1.0000
  14.750   1.6167   0.04600   0.04144  -0.0188   0.2005   1.0000
  15.000   1.6171   0.04835   0.04382  -0.0186   0.1976   1.0000
  15.250   1.6123   0.05129   0.04677  -0.0185   0.1939   1.0000
  15.500   1.6113   0.05387   0.04938  -0.0184   0.1909   1.0000
  15.750   1.6149   0.05600   0.05156  -0.0183   0.1886   1.0000
  16.000   1.6179   0.05818   0.05378  -0.0183   0.1856   1.0000
  16.250   1.6143   0.06115   0.05678  -0.0184   0.1821   1.0000
  16.500   1.6089   0.06433   0.05997  -0.0185   0.1776   1.0000
  16.750   1.6118   0.06662   0.06230  -0.0186   0.1749   1.0000
  17.000   1.6115   0.06932   0.06504  -0.0188   0.1719   1.0000
  17.250   1.6080   0.07237   0.06811  -0.0191   0.1679   1.0000
  17.500   1.6027   0.07569   0.07147  -0.0194   0.1646   1.0000
  17.750   1.6026   0.07843   0.07423  -0.0197   0.1601   1.0000
  18.000   1.5915   0.08254   0.07837  -0.0203   0.1548   1.0000
  18.250   1.5859   0.08599   0.08183  -0.0208   0.1493   1.0000
  18.500   1.5693   0.09091   0.08675  -0.0216   0.1422   1.0000
  18.750   1.5657   0.09421   0.09008  -0.0223   0.1377   1.0000
  19.000   1.5439   0.09991   0.09577  -0.0234   0.1291   1.0000
  19.250   1.5377   0.10365   0.09955  -0.0242   0.1241   1.0000
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