Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

GOE 767 AIRFOIL (goe767-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 767 AIRFOIL (goe767-il)
Reynolds number: 1,000,000
Max Cl/Cd: 91.48 at α=9.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe767-il-1000000-n5.txt
Download as CSV file: xf-goe767-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 767 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
  ------ -------- --------- --------- -------- -------- --------
 -18.000  -1.2276   0.08666   0.08342  -0.0149   1.0000   0.0216
 -17.750  -1.3012   0.07092   0.06744  -0.0246   1.0000   0.0215
 -17.500  -1.3632   0.05657   0.05281  -0.0344   1.0000   0.0213
 -17.250  -1.3905   0.04793   0.04398  -0.0410   1.0000   0.0214
 -17.000  -1.4061   0.04199   0.03788  -0.0452   1.0000   0.0215
 -16.750  -1.4146   0.03781   0.03356  -0.0475   1.0000   0.0216
 -16.500  -1.4185   0.03474   0.03038  -0.0485   1.0000   0.0217
 -16.250  -1.4203   0.03232   0.02786  -0.0485   1.0000   0.0218
 -16.000  -1.4195   0.03045   0.02590  -0.0477   1.0000   0.0219
 -15.750  -1.4164   0.02896   0.02433  -0.0463   1.0000   0.0220
 -15.500  -1.4123   0.02770   0.02299  -0.0445   1.0000   0.0221
 -15.250  -1.4059   0.02668   0.02191  -0.0424   1.0000   0.0223
 -15.000  -1.3994   0.02576   0.02092  -0.0400   1.0000   0.0225
 -14.750  -1.3927   0.02493   0.02001  -0.0372   1.0000   0.0226
 -14.500  -1.3815   0.02422   0.01924  -0.0350   1.0000   0.0229
 -14.250  -1.3670   0.02350   0.01846  -0.0333   1.0000   0.0231
 -14.000  -1.3517   0.02278   0.01768  -0.0316   1.0000   0.0232
 -13.750  -1.3351   0.02211   0.01695  -0.0301   1.0000   0.0234
 -13.500  -1.3170   0.02150   0.01627  -0.0287   1.0000   0.0235
 -13.250  -1.2984   0.02089   0.01560  -0.0273   1.0000   0.0237
 -13.000  -1.2784   0.02037   0.01503  -0.0261   1.0000   0.0238
 -12.750  -1.2604   0.01965   0.01426  -0.0247   1.0000   0.0241
 -12.500  -1.2414   0.01896   0.01353  -0.0233   1.0000   0.0244
 -12.250  -1.2212   0.01837   0.01290  -0.0221   1.0000   0.0247
 -12.000  -1.2001   0.01783   0.01233  -0.0210   1.0000   0.0249
 -11.750  -1.1784   0.01733   0.01179  -0.0199   1.0000   0.0251
 -11.500  -1.1563   0.01686   0.01128  -0.0188   1.0000   0.0254
 -11.250  -1.1337   0.01641   0.01080  -0.0178   1.0000   0.0256
 -11.000  -1.1109   0.01598   0.01034  -0.0168   1.0000   0.0259
 -10.750  -1.0878   0.01557   0.00990  -0.0158   1.0000   0.0262
 -10.500  -1.0645   0.01518   0.00947  -0.0148   1.0000   0.0265
 -10.250  -1.0409   0.01481   0.00908  -0.0139   1.0000   0.0268
 -10.000  -1.0173   0.01445   0.00868  -0.0129   1.0000   0.0271
  -9.750  -0.9934   0.01411   0.00831  -0.0120   1.0000   0.0273
  -9.500  -0.9697   0.01376   0.00794  -0.0110   1.0000   0.0275
  -9.250  -0.9465   0.01334   0.00750  -0.0099   1.0000   0.0279
  -9.000  -0.9229   0.01297   0.00711  -0.0089   1.0000   0.0283
  -8.750  -0.8991   0.01262   0.00676  -0.0079   1.0000   0.0288
  -8.500  -0.8751   0.01231   0.00644  -0.0069   1.0000   0.0292
  -8.250  -0.8510   0.01201   0.00613  -0.0059   1.0000   0.0296
  -8.000  -0.8268   0.01173   0.00584  -0.0049   1.0000   0.0301
  -7.750  -0.8007   0.01146   0.00556  -0.0043   0.9994   0.0306
  -7.500  -0.7680   0.01118   0.00528  -0.0050   0.9912   0.0312
  -7.250  -0.7305   0.01085   0.00495  -0.0069   0.9781   0.0322
  -7.000  -0.6727   0.01049   0.00455  -0.0130   0.9210   0.0337
  -6.750  -0.6485   0.01054   0.00429  -0.0117   0.8190   0.0347
  -6.500  -0.6294   0.01087   0.00406  -0.0096   0.6420   0.0358
  -6.250  -0.6042   0.01078   0.00382  -0.0088   0.5920   0.0380
  -6.000  -0.5784   0.01064   0.00359  -0.0082   0.5561   0.0412
  -5.750  -0.5526   0.01045   0.00335  -0.0075   0.5276   0.0479
  -5.500  -0.5266   0.01024   0.00313  -0.0069   0.5034   0.0590
  -5.250  -0.4999   0.01009   0.00298  -0.0064   0.4845   0.0675
  -5.000  -0.4729   0.00999   0.00284  -0.0059   0.4686   0.0732
  -4.750  -0.4456   0.00989   0.00272  -0.0055   0.4544   0.0783
  -4.500  -0.4182   0.00980   0.00261  -0.0051   0.4416   0.0820
  -4.250  -0.3908   0.00972   0.00250  -0.0046   0.4283   0.0855
  -4.000  -0.3631   0.00966   0.00240  -0.0042   0.4149   0.0883
  -3.750  -0.3356   0.00959   0.00230  -0.0038   0.4030   0.0913
  -3.500  -0.3081   0.00952   0.00221  -0.0034   0.3915   0.0949
  -3.250  -0.2803   0.00946   0.00212  -0.0030   0.3818   0.0976
  -3.000  -0.2525   0.00943   0.00204  -0.0027   0.3720   0.0998
  -2.750  -0.2247   0.00935   0.00196  -0.0023   0.3627   0.1031
  -2.500  -0.1971   0.00929   0.00189  -0.0019   0.3534   0.1070
  -2.250  -0.1692   0.00925   0.00182  -0.0015   0.3445   0.1103
  -2.000  -0.1413   0.00922   0.00176  -0.0012   0.3354   0.1128
  -1.750  -0.1136   0.00916   0.00170  -0.0008   0.3269   0.1180
  -1.500  -0.0858   0.00913   0.00165  -0.0004   0.3178   0.1236
  -1.250  -0.0580   0.00907   0.00161  -0.0001   0.3090   0.1307
  -1.000  -0.0303   0.00905   0.00158   0.0003   0.2992   0.1385
  -0.750  -0.0026   0.00900   0.00155   0.0006   0.2898   0.1497
  -0.500   0.0251   0.00897   0.00152   0.0010   0.2811   0.1620
  -0.250   0.0529   0.00893   0.00151   0.0013   0.2727   0.1749
   0.000   0.0806   0.00893   0.00150   0.0017   0.2633   0.1881
   0.250   0.1082   0.00890   0.00149   0.0021   0.2540   0.2039
   0.500   0.1355   0.00884   0.00148   0.0024   0.2462   0.2290
   0.750   0.1621   0.00869   0.00149   0.0029   0.2384   0.2847
   1.000   0.1892   0.00862   0.00150   0.0033   0.2316   0.3253
   1.250   0.2164   0.00853   0.00153   0.0037   0.2271   0.3632
   1.500   0.2434   0.00844   0.00156   0.0041   0.2224   0.4089
   1.750   0.2695   0.00829   0.00159   0.0047   0.2168   0.4792
   2.000   0.2959   0.00812   0.00164   0.0052   0.2137   0.5450
   2.250   0.3223   0.00801   0.00169   0.0058   0.2104   0.6020
   2.500   0.3489   0.00794   0.00175   0.0063   0.2074   0.6513
   2.750   0.3746   0.00785   0.00183   0.0071   0.2041   0.7104
   3.000   0.3992   0.00773   0.00192   0.0081   0.2005   0.7755
   3.250   0.4241   0.00761   0.00200   0.0092   0.1984   0.8327
   3.500   0.4493   0.00754   0.00211   0.0102   0.1953   0.8902
   3.750   0.4789   0.00757   0.00222   0.0103   0.1915   0.9281
   4.000   0.5138   0.00769   0.00234   0.0092   0.1871   0.9529
   4.250   0.5517   0.00782   0.00246   0.0073   0.1833   0.9671
   4.500   0.5925   0.00795   0.00258   0.0049   0.1783   0.9781
   4.750   0.6314   0.00813   0.00270   0.0028   0.1704   0.9861
   5.000   0.6666   0.00827   0.00282   0.0015   0.1639   0.9909
   5.250   0.6992   0.00846   0.00294   0.0006   0.1549   0.9939
   5.500   0.7323   0.00867   0.00309  -0.0003   0.1438   0.9961
   5.750   0.7648   0.00891   0.00326  -0.0012   0.1335   0.9981
   6.000   0.7969   0.00916   0.00345  -0.0020   0.1246   0.9997
   6.250   0.8228   0.00940   0.00365  -0.0015   0.1182   1.0000
   6.500   0.8467   0.00960   0.00384  -0.0006   0.1140   1.0000
   6.750   0.8704   0.00985   0.00405   0.0004   0.1094   1.0000
   7.000   0.8946   0.01005   0.00425   0.0013   0.1062   1.0000
   7.250   0.9188   0.01027   0.00446   0.0022   0.1031   1.0000
   7.500   0.9428   0.01052   0.00469   0.0031   0.0997   1.0000
   7.750   0.9670   0.01075   0.00492   0.0039   0.0969   1.0000
   8.000   0.9916   0.01095   0.00513   0.0047   0.0952   1.0000
   8.250   1.0161   0.01117   0.00535   0.0055   0.0928   1.0000
   8.500   1.0403   0.01143   0.00560   0.0063   0.0902   1.0000
   8.750   1.0643   0.01171   0.00587   0.0071   0.0876   1.0000
   9.000   1.0889   0.01193   0.00611   0.0079   0.0861   1.0000
   9.250   1.1133   0.01217   0.00636   0.0086   0.0840   1.0000
   9.500   1.1373   0.01244   0.00664   0.0094   0.0816   1.0000
   9.750   1.1610   0.01276   0.00695   0.0102   0.0790   1.0000
  10.000   1.1851   0.01303   0.00723   0.0109   0.0770   1.0000
  10.250   1.2091   0.01331   0.00754   0.0116   0.0744   1.0000
  10.500   1.2323   0.01368   0.00789   0.0124   0.0710   1.0000
  10.750   1.2557   0.01401   0.00822   0.0132   0.0681   1.0000
  11.000   1.2786   0.01439   0.00860   0.0140   0.0644   1.0000
  11.250   1.3011   0.01479   0.00901   0.0148   0.0611   1.0000
  11.500   1.3232   0.01524   0.00944   0.0156   0.0571   1.0000
  11.750   1.3448   0.01570   0.00991   0.0165   0.0536   1.0000
  12.000   1.3653   0.01625   0.01045   0.0175   0.0497   1.0000
  12.250   1.3860   0.01675   0.01096   0.0185   0.0468   1.0000
  12.500   1.4055   0.01735   0.01156   0.0196   0.0440   1.0000
  12.750   1.4252   0.01788   0.01212   0.0206   0.0420   1.0000
  13.000   1.4435   0.01850   0.01276   0.0218   0.0400   1.0000
  13.250   1.4613   0.01912   0.01341   0.0230   0.0385   1.0000
  13.500   1.4787   0.01972   0.01405   0.0243   0.0374   1.0000
  13.750   1.4948   0.02037   0.01474   0.0257   0.0364   1.0000
  14.000   1.5088   0.02110   0.01551   0.0273   0.0355   1.0000
  14.250   1.5199   0.02191   0.01635   0.0292   0.0347   1.0000
  14.500   1.5278   0.02263   0.01714   0.0317   0.0342   1.0000
  14.750   1.5342   0.02346   0.01804   0.0341   0.0338   1.0000
  15.000   1.5391   0.02449   0.01913   0.0363   0.0333   1.0000
  15.250   1.5420   0.02581   0.02053   0.0379   0.0328   1.0000
  15.500   1.5428   0.02756   0.02236   0.0388   0.0324   1.0000
  15.750   1.5415   0.02997   0.02487   0.0386   0.0320   1.0000
  16.000   1.5371   0.03354   0.02856   0.0367   0.0317   1.0000
  16.250   1.5286   0.03836   0.03352   0.0333   0.0314   1.0000
  16.500   1.5140   0.04401   0.03931   0.0298   0.0312   1.0000
  16.750   1.4915   0.05048   0.04593   0.0262   0.0311   1.0000
  17.000   1.4616   0.05773   0.05332   0.0225   0.0309   1.0000
  17.250   1.4302   0.06510   0.06083   0.0190   0.0310   1.0000
  17.500   1.3956   0.07296   0.06883   0.0152   0.0309   1.0000
  17.750   1.3647   0.08050   0.07649   0.0116   0.0308   1.0000
<< Back to GOE 767 AIRFOIL (goe767-il)

Polar data table (+)

Polar graphs


<< Back to GOE 767 AIRFOIL (goe767-il)