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GOE 376 AIRFOIL (goe376-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 376 AIRFOIL (goe376-il)
Reynolds number: 1,000,000
Max Cl/Cd: 97.2 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe376-il-1000000-n5.txt
Download as CSV file: xf-goe376-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 376 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3375   0.10006   0.09847  -0.0193   1.0000   0.0048
  -8.750  -0.3378   0.09650   0.09493  -0.0198   1.0000   0.0049
  -8.500  -0.3396   0.09302   0.09147  -0.0202   1.0000   0.0052
  -8.250  -0.3246   0.08886   0.08732  -0.0249   0.9983   0.0052
  -8.000  -0.3074   0.08620   0.08466  -0.0284   0.9946   0.0054
  -7.750  -0.2930   0.08363   0.08210  -0.0313   0.9892   0.0057
  -7.250  -0.2648   0.07592   0.07439  -0.0400   0.9591   0.0061
  -7.000  -0.2248   0.06661   0.06499  -0.0562   0.9425   0.0071
  -6.750  -0.1597   0.06112   0.05938  -0.0723   0.9253   0.0074
  -6.500  -0.1161   0.05802   0.05611  -0.0810   0.8959   0.0082
  -6.250  -0.0985   0.05366   0.05159  -0.0853   0.8683   0.0090
  -6.000  -0.0832   0.04857   0.04634  -0.0891   0.8462   0.0096
  -5.750  -0.0640   0.04703   0.04469  -0.0900   0.8243   0.0099
  -5.500  -0.0450   0.04497   0.04249  -0.0910   0.8008   0.0101
  -5.250  -0.0252   0.04295   0.04032  -0.0918   0.7769   0.0107
  -5.000  -0.0033   0.03646   0.03354  -0.0949   0.7592   0.0124
  -4.750   0.0185   0.03510   0.03206  -0.0952   0.7429   0.0126
  -4.250   0.0643   0.03199   0.02872  -0.0957   0.7174   0.0132
  -4.000   0.0881   0.03014   0.02673  -0.0959   0.7062   0.0141
  -3.750   0.1132   0.02465   0.02082  -0.0957   0.6969   0.0158
  -3.500   0.1365   0.02372   0.01978  -0.0955   0.6851   0.0160
  -3.250   0.1604   0.02313   0.01911  -0.0952   0.6738   0.0164
  -3.000   0.1846   0.02208   0.01794  -0.0949   0.6636   0.0169
  -2.750   0.2089   0.02053   0.01620  -0.0943   0.6526   0.0174
  -2.500   0.2333   0.01893   0.01438  -0.0935   0.6399   0.0179
  -2.250   0.2574   0.01713   0.01231  -0.0924   0.6244   0.0184
  -2.000   0.2812   0.01466   0.00937  -0.0908   0.6078   0.0199
  -1.750   0.3051   0.01404   0.00858  -0.0901   0.5835   0.0201
  -1.500   0.3289   0.01361   0.00797  -0.0894   0.5541   0.0204
  -1.250   0.3528   0.01321   0.00737  -0.0886   0.5233   0.0207
  -1.000   0.3770   0.01276   0.00670  -0.0878   0.4940   0.0209
  -0.750   0.4017   0.01225   0.00600  -0.0871   0.4743   0.0211
  -0.250   0.4526   0.01143   0.00491  -0.0859   0.4470   0.0216
   0.000   0.4783   0.01097   0.00432  -0.0853   0.4369   0.0215
   0.250   0.5039   0.01056   0.00378  -0.0847   0.4266   0.0214
   0.500   0.5296   0.01022   0.00336  -0.0841   0.4172   0.0214
   0.750   0.5554   0.00996   0.00304  -0.0836   0.4099   0.0217
   1.000   0.5813   0.00976   0.00279  -0.0831   0.4027   0.0223
   1.250   0.6071   0.00961   0.00260  -0.0826   0.3963   0.0228
   1.500   0.6330   0.00950   0.00246  -0.0821   0.3884   0.0233
   1.750   0.6585   0.00946   0.00237  -0.0816   0.3771   0.0237
   2.000   0.6839   0.00941   0.00228  -0.0811   0.3666   0.0239
   2.250   0.7095   0.00940   0.00224  -0.0806   0.3554   0.0241
   2.750   0.7597   0.00935   0.00211  -0.0794   0.3291   0.0249
   3.000   0.7846   0.00934   0.00206  -0.0788   0.3157   0.0251
   3.250   0.8095   0.00940   0.00206  -0.0782   0.3010   0.0252
   3.500   0.8344   0.00947   0.00209  -0.0777   0.2867   0.0253
   3.750   0.8591   0.00956   0.00213  -0.0770   0.2722   0.0256
   4.000   0.8838   0.00968   0.00220  -0.0764   0.2594   0.0262
   4.250   0.9086   0.00981   0.00229  -0.0759   0.2478   0.0270
   4.500   0.9331   0.00998   0.00242  -0.0752   0.2344   0.0281
   4.750   0.9569   0.01022   0.00258  -0.0745   0.2156   0.0293
   5.000   0.9813   0.01043   0.00273  -0.0739   0.2034   0.0300
   5.250   1.0059   0.01060   0.00289  -0.0733   0.1936   0.0309
   5.500   1.0303   0.01080   0.00306  -0.0727   0.1821   0.0328
   5.750   1.0538   0.01106   0.00326  -0.0720   0.1662   0.0342
   6.000   1.0756   0.01149   0.00354  -0.0710   0.1390   0.0372
   6.500   1.1547   0.01188   0.00505  -0.0784   0.0493   1.0000
   6.750   1.1720   0.01270   0.00569  -0.0766   0.0161   1.0000
   7.000   1.1946   0.01301   0.00603  -0.0757   0.0131   1.0000
   7.250   1.2165   0.01338   0.00642  -0.0747   0.0110   1.0000
   7.500   1.2386   0.01372   0.00680  -0.0737   0.0097   1.0000
   7.750   1.2607   0.01405   0.00716  -0.0728   0.0088   1.0000
   8.000   1.2821   0.01443   0.00757  -0.0717   0.0079   1.0000
   8.250   1.3027   0.01486   0.00803  -0.0705   0.0072   1.0000
   8.500   1.3226   0.01535   0.00856  -0.0692   0.0066   1.0000
   8.750   1.3432   0.01575   0.00901  -0.0681   0.0062   1.0000
   9.000   1.3633   0.01618   0.00948  -0.0669   0.0058   1.0000
   9.250   1.3827   0.01664   0.00999  -0.0656   0.0054   1.0000
   9.500   1.4016   0.01713   0.01050  -0.0642   0.0050   1.0000
   9.750   1.4184   0.01776   0.01118  -0.0625   0.0046   1.0000
  10.000   1.4345   0.01841   0.01189  -0.0607   0.0044   1.0000
  10.250   1.4512   0.01896   0.01251  -0.0591   0.0043   1.0000
  10.500   1.4666   0.01958   0.01321  -0.0572   0.0041   1.0000
  10.750   1.4792   0.02025   0.01394  -0.0549   0.0039   1.0000
  11.000   1.4888   0.02098   0.01475  -0.0520   0.0038   1.0000
  11.250   1.5010   0.02158   0.01540  -0.0497   0.0036   1.0000
  11.500   1.5088   0.02247   0.01638  -0.0469   0.0035   1.0000
  11.750   1.5190   0.02325   0.01723  -0.0447   0.0034   1.0000
  12.000   1.5273   0.02419   0.01825  -0.0423   0.0033   1.0000
  12.250   1.5331   0.02533   0.01949  -0.0399   0.0032   1.0000
  12.500   1.5398   0.02650   0.02072  -0.0378   0.0031   1.0000
  12.750   1.5440   0.02791   0.02222  -0.0357   0.0030   1.0000
  13.000   1.5440   0.02978   0.02420  -0.0337   0.0029   1.0000
  13.250   1.5410   0.03207   0.02661  -0.0319   0.0028   1.0000
  13.500   1.5425   0.03414   0.02878  -0.0308   0.0027   1.0000
  13.750   1.5473   0.03601   0.03075  -0.0300   0.0027   1.0000
  14.000   1.5406   0.03925   0.03413  -0.0294   0.0027   1.0000
  14.250   1.5375   0.04232   0.03731  -0.0292   0.0026   1.0000
  14.500   1.5336   0.04561   0.04072  -0.0293   0.0026   1.0000
  14.750   1.5257   0.04959   0.04483  -0.0298   0.0026   1.0000
  15.000   1.5214   0.05324   0.04860  -0.0304   0.0025   1.0000
  15.250   1.5113   0.05785   0.05333  -0.0315   0.0025   1.0000
  15.500   1.4973   0.06322   0.05885  -0.0330   0.0025   1.0000
  15.750   1.4863   0.06832   0.06407  -0.0345   0.0024   1.0000
  16.000   1.4765   0.07336   0.06922  -0.0362   0.0024   1.0000
  16.250   1.4618   0.07928   0.07526  -0.0382   0.0024   1.0000
  16.500   1.4428   0.08591   0.08202  -0.0405   0.0024   1.0000
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