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GOE 412 AIRFOIL (goe412-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 412 AIRFOIL (goe412-il)
Reynolds number: 1,000,000
Max Cl/Cd: 137.73 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe412-il-1000000.txt
Download as CSV file: xf-goe412-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 412 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.5126   0.03738   0.03507  -0.1206   0.9429   0.0231
 -10.750  -0.5220   0.03227   0.02956  -0.1224   0.9312   0.0234
 -10.500  -0.5126   0.02995   0.02695  -0.1223   0.9220   0.0237
 -10.250  -0.4963   0.02872   0.02548  -0.1219   0.9123   0.0240
 -10.000  -0.4852   0.02633   0.02274  -0.1214   0.8994   0.0242
  -9.750  -0.4773   0.02273   0.01877  -0.1206   0.8851   0.0246
  -9.500  -0.4580   0.02131   0.01717  -0.1201   0.8715   0.0249
  -9.250  -0.4362   0.02032   0.01603  -0.1196   0.8589   0.0252
  -9.000  -0.4133   0.01949   0.01505  -0.1193   0.8476   0.0255
  -8.750  -0.3893   0.01881   0.01425  -0.1190   0.8374   0.0258
  -8.500  -0.3646   0.01820   0.01354  -0.1188   0.8288   0.0262
  -8.250  -0.3401   0.01749   0.01268  -0.1185   0.8209   0.0266
  -8.000  -0.3154   0.01669   0.01173  -0.1183   0.8140   0.0269
  -7.750  -0.2902   0.01596   0.01086  -0.1181   0.8073   0.0271
  -7.500  -0.2647   0.01532   0.01007  -0.1178   0.8012   0.0274
  -7.250  -0.2383   0.01471   0.00936  -0.1177   0.7956   0.0277
  -7.000  -0.2119   0.01421   0.00874  -0.1176   0.7899   0.0280
  -6.750  -0.1851   0.01379   0.00821  -0.1175   0.7846   0.0283
  -6.500  -0.1575   0.01349   0.00784  -0.1175   0.7796   0.0285
  -6.250  -0.1314   0.01277   0.00702  -0.1173   0.7744   0.0290
  -6.000  -0.1057   0.01203   0.00619  -0.1171   0.7693   0.0293
  -5.750  -0.0788   0.01149   0.00561  -0.1170   0.7649   0.0297
  -5.500  -0.0516   0.01107   0.00516  -0.1170   0.7600   0.0301
  -5.250  -0.0243   0.01074   0.00478  -0.1169   0.7551   0.0304
  -5.000   0.0033   0.01044   0.00444  -0.1169   0.7506   0.0308
  -4.750   0.0312   0.01015   0.00413  -0.1169   0.7461   0.0313
  -4.500   0.0591   0.00990   0.00384  -0.1169   0.7413   0.0318
  -4.250   0.0868   0.00971   0.00357  -0.1169   0.7366   0.0323
  -4.000   0.1152   0.00949   0.00334  -0.1170   0.7324   0.0329
  -3.750   0.1435   0.00931   0.00314  -0.1171   0.7277   0.0335
  -3.500   0.1717   0.00917   0.00295  -0.1171   0.7231   0.0339
  -3.250   0.1996   0.00894   0.00266  -0.1171   0.7186   0.0348
  -3.000   0.2280   0.00874   0.00246  -0.1172   0.7141   0.0359
  -2.750   0.2563   0.00859   0.00230  -0.1173   0.7094   0.0371
  -2.500   0.2844   0.00851   0.00216  -0.1173   0.7042   0.0385
  -2.250   0.3130   0.00839   0.00204  -0.1174   0.6989   0.0401
  -2.000   0.3412   0.00824   0.00192  -0.1175   0.6930   0.0479
  -1.750   0.3688   0.00808   0.00186  -0.1175   0.6873   0.0798
  -1.500   0.3972   0.00796   0.00180  -0.1176   0.6809   0.0956
  -1.250   0.4250   0.00790   0.00176  -0.1176   0.6732   0.1130
  -1.000   0.4533   0.00784   0.00174  -0.1177   0.6662   0.1295
  -0.750   0.4814   0.00779   0.00171  -0.1178   0.6594   0.1444
  -0.500   0.5095   0.00775   0.00168  -0.1179   0.6534   0.1595
  -0.250   0.5376   0.00766   0.00166  -0.1180   0.6471   0.1824
   0.000   0.5648   0.00749   0.00168  -0.1180   0.6410   0.2588
   0.250   0.5929   0.00741   0.00170  -0.1181   0.6353   0.3007
   0.500   0.6208   0.00734   0.00172  -0.1182   0.6292   0.3365
   0.750   0.6480   0.00725   0.00175  -0.1182   0.6232   0.3925
   1.000   0.6742   0.00687   0.00182  -0.1181   0.6170   0.5639
   1.250   0.6937   0.00617   0.00193  -0.1164   0.6104   0.8448
   1.500   0.7367   0.00608   0.00205  -0.1194   0.6034   0.9871
   1.750   0.7834   0.00619   0.00210  -0.1237   0.5954   0.9993
   2.000   0.8111   0.00627   0.00214  -0.1237   0.5876   1.0000
   2.250   0.8364   0.00636   0.00218  -0.1232   0.5792   1.0000
   2.500   0.8618   0.00646   0.00224  -0.1227   0.5712   1.0000
   2.750   0.8867   0.00657   0.00230  -0.1222   0.5620   1.0000
   3.000   0.9119   0.00667   0.00236  -0.1217   0.5523   1.0000
   3.250   0.9364   0.00681   0.00244  -0.1210   0.5406   1.0000
   3.500   0.9606   0.00698   0.00254  -0.1204   0.5269   1.0000
   3.750   0.9848   0.00715   0.00264  -0.1197   0.5122   1.0000
   4.000   1.0090   0.00734   0.00276  -0.1190   0.4971   1.0000
   4.250   1.0332   0.00753   0.00289  -0.1184   0.4819   1.0000
   4.500   1.0569   0.00775   0.00304  -0.1177   0.4654   1.0000
   4.750   1.0803   0.00800   0.00320  -0.1169   0.4474   1.0000
   5.000   1.1034   0.00826   0.00338  -0.1161   0.4287   1.0000
   5.250   1.1260   0.00855   0.00359  -0.1153   0.4093   1.0000
   5.500   1.1480   0.00887   0.00381  -0.1143   0.3894   1.0000
   5.750   1.1694   0.00921   0.00406  -0.1132   0.3703   1.0000
   6.000   1.1910   0.00954   0.00431  -0.1122   0.3521   1.0000
   6.250   1.2119   0.00990   0.00458  -0.1111   0.3334   1.0000
   6.500   1.2314   0.01031   0.00489  -0.1097   0.3123   1.0000
   6.750   1.2498   0.01076   0.00523  -0.1082   0.2914   1.0000
   7.000   1.2672   0.01122   0.00557  -0.1064   0.2675   1.0000
   7.250   1.2807   0.01176   0.00598  -0.1040   0.2421   1.0000
   7.500   1.2932   0.01238   0.00645  -0.1014   0.2158   1.0000
   7.750   1.3071   0.01297   0.00694  -0.0992   0.1960   1.0000
   8.000   1.3227   0.01351   0.00741  -0.0973   0.1836   1.0000
   8.250   1.3392   0.01401   0.00787  -0.0956   0.1754   1.0000
   8.500   1.3577   0.01443   0.00830  -0.0943   0.1700   1.0000
   8.750   1.3762   0.01485   0.00873  -0.0930   0.1660   1.0000
   9.000   1.3930   0.01537   0.00923  -0.0915   0.1606   1.0000
   9.250   1.4110   0.01584   0.00971  -0.0903   0.1558   1.0000
   9.500   1.4291   0.01630   0.01019  -0.0890   0.1509   1.0000
   9.750   1.4449   0.01691   0.01078  -0.0875   0.1453   1.0000
  10.000   1.4628   0.01740   0.01130  -0.0863   0.1406   1.0000
  10.250   1.4779   0.01807   0.01194  -0.0848   0.1311   1.0000
  10.500   1.4841   0.01929   0.01297  -0.0822   0.1005   1.0000
  10.750   1.4854   0.02087   0.01441  -0.0792   0.0798   1.0000
  11.000   1.4930   0.02211   0.01563  -0.0770   0.0717   1.0000
  11.250   1.5038   0.02319   0.01672  -0.0754   0.0646   1.0000
  11.500   1.5094   0.02467   0.01814  -0.0733   0.0519   1.0000
  11.750   1.5031   0.02707   0.02035  -0.0702   0.0268   1.0000
  12.000   1.5068   0.02883   0.02210  -0.0682   0.0205   1.0000
  12.250   1.5129   0.03043   0.02373  -0.0665   0.0182   1.0000
  12.500   1.5220   0.03182   0.02517  -0.0652   0.0172   1.0000
  12.750   1.5300   0.03334   0.02674  -0.0639   0.0163   1.0000
  13.000   1.5359   0.03508   0.02853  -0.0625   0.0155   1.0000
  13.250   1.5405   0.03697   0.03048  -0.0611   0.0147   1.0000
  13.500   1.5487   0.03857   0.03215  -0.0600   0.0143   1.0000
  13.750   1.5556   0.04033   0.03397  -0.0590   0.0139   1.0000
  14.000   1.5611   0.04227   0.03597  -0.0580   0.0134   1.0000
  14.250   1.5654   0.04435   0.03811  -0.0570   0.0131   1.0000
  14.500   1.5679   0.04664   0.04046  -0.0559   0.0127   1.0000
  14.750   1.5673   0.04933   0.04323  -0.0549   0.0123   1.0000
  15.000   1.5636   0.05243   0.04643  -0.0539   0.0120   1.0000
  15.250   1.5677   0.05475   0.04882  -0.0533   0.0118   1.0000
  15.500   1.5700   0.05728   0.05144  -0.0528   0.0116   1.0000
  15.750   1.5713   0.05999   0.05423  -0.0523   0.0114   1.0000
  16.000   1.5716   0.06288   0.05719  -0.0519   0.0112   1.0000
  16.250   1.5710   0.06593   0.06032  -0.0516   0.0110   1.0000
  16.500   1.5693   0.06914   0.06362  -0.0514   0.0108   1.0000
  16.750   1.5668   0.07251   0.06707  -0.0513   0.0106   1.0000
  17.000   1.5634   0.07604   0.07069  -0.0513   0.0104   1.0000
  17.250   1.5588   0.07982   0.07455  -0.0514   0.0103   1.0000
  17.500   1.5520   0.08396   0.07877  -0.0517   0.0101   1.0000
  17.750   1.5422   0.08855   0.08346  -0.0522   0.0099   1.0000
  18.000   1.5298   0.09359   0.08860  -0.0529   0.0098   1.0000
  18.250   1.5146   0.09915   0.09428  -0.0538   0.0096   1.0000
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