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GOE 630 AIRFOIL (goe630-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 630 AIRFOIL (goe630-il)
Reynolds number: 1,000,000
Max Cl/Cd: 128.97 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe630-il-1000000.txt
Download as CSV file: xf-goe630-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 630 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250   0.0993   0.09089   0.08841  -0.1073   0.8041   0.0212
 -11.000   0.0759   0.09665   0.09434  -0.1172   0.8669   0.0211
 -10.750   0.0748   0.09314   0.09069  -0.1200   0.8430   0.0213
 -10.500   0.0855   0.09038   0.08786  -0.1198   0.8273   0.0215
 -10.250   0.0943   0.08821   0.08562  -0.1203   0.8136   0.0216
 -10.000   0.1054   0.08661   0.08396  -0.1204   0.8016   0.0218
  -9.750   0.1139   0.08467   0.08196  -0.1208   0.7908   0.0221
  -9.500   0.1223   0.08266   0.07992  -0.1213   0.7809   0.0223
  -9.250   0.1304   0.08072   0.07793  -0.1218   0.7720   0.0230
  -9.000   0.1251   0.07734   0.07454  -0.1243   0.7640   0.0248
  -8.750   0.1403   0.06196   0.05924  -0.1143   0.7359   0.0250
  -8.500   0.1499   0.05957   0.05683  -0.1142   0.7300   0.0252
  -8.250   0.1365   0.06936   0.06649  -0.1258   0.7433   0.0252
  -8.000   0.1465   0.06767   0.06479  -0.1256   0.7371   0.0254
  -7.750   0.1544   0.06598   0.06309  -0.1255   0.7309   0.0255
  -7.500   0.1601   0.06435   0.06144  -0.1251   0.7247   0.0258
  -7.250   0.1617   0.06253   0.05963  -0.1247   0.7190   0.0259
  -7.000   0.1661   0.06087   0.05796  -0.1248   0.7131   0.0264
  -6.750   0.1735   0.05881   0.05588  -0.1258   0.7076   0.0271
  -6.250   0.1830   0.04839   0.04539  -0.1374   0.6975   0.0292
  -6.000   0.1979   0.04663   0.04359  -0.1379   0.6924   0.0294
  -5.750   0.2154   0.04512   0.04206  -0.1386   0.6875   0.0297
  -5.500   0.2338   0.04318   0.04009  -0.1399   0.6819   0.0300
  -5.250   0.2529   0.04127   0.03811  -0.1412   0.6765   0.0305
  -5.000   0.2804   0.03380   0.03037  -0.1482   0.6721   0.0335
  -4.750   0.2943   0.02907   0.02548  -0.1498   0.6673   0.0341
  -4.500   0.3161   0.02786   0.02420  -0.1499   0.6615   0.0344
  -4.250   0.3385   0.02662   0.02287  -0.1500   0.6557   0.0348
  -4.000   0.3442   0.01534   0.01045  -0.1494   0.6521   0.0319
  -3.750   0.3661   0.01349   0.00823  -0.1485   0.6460   0.0321
  -3.500   0.3900   0.01247   0.00696  -0.1477   0.6397   0.0324
  -3.250   0.4158   0.01182   0.00616  -0.1473   0.6333   0.0328
  -3.000   0.4413   0.01139   0.00558  -0.1467   0.6261   0.0332
  -2.750   0.4679   0.01112   0.00521  -0.1463   0.6188   0.0335
  -2.500   0.4922   0.01037   0.00434  -0.1456   0.6103   0.0344
  -2.250   0.5183   0.01015   0.00408  -0.1452   0.6015   0.0350
  -1.750   0.5700   0.00982   0.00364  -0.1442   0.5827   0.0362
  -1.500   0.5954   0.00967   0.00341  -0.1436   0.5731   0.0368
  -1.250   0.6209   0.00955   0.00323  -0.1430   0.5625   0.0376
  -1.000   0.6465   0.00946   0.00307  -0.1425   0.5520   0.0383
  -0.750   0.6716   0.00946   0.00300  -0.1418   0.5407   0.0388
  -0.500   0.6957   0.00921   0.00270  -0.1410   0.5293   0.0402
  -0.250   0.7210   0.00921   0.00267  -0.1405   0.5184   0.0416
   0.000   0.7458   0.00924   0.00264  -0.1398   0.5080   0.0430
   0.250   0.7707   0.00925   0.00261  -0.1392   0.4975   0.0443
   0.500   0.7955   0.00922   0.00252  -0.1385   0.4881   0.0459
   1.000   0.8448   0.00927   0.00250  -0.1372   0.4692   0.0506
   1.250   0.8689   0.00933   0.00252  -0.1364   0.4602   0.0533
   1.500   0.8934   0.00935   0.00252  -0.1357   0.4514   0.0581
   1.750   0.9175   0.00943   0.00256  -0.1349   0.4433   0.0627
   2.000   0.9419   0.00946   0.00260  -0.1343   0.4359   0.0713
   2.250   0.9648   0.00949   0.00270  -0.1333   0.4286   0.1164
   2.500   0.9884   0.00939   0.00283  -0.1326   0.4226   0.2224
   2.750   1.0093   0.00925   0.00302  -0.1314   0.4161   0.4012
   3.000   1.0779   0.00846   0.00340  -0.1410   0.4083   1.0000
   3.250   1.1014   0.00862   0.00350  -0.1401   0.4024   1.0000
   3.500   1.1238   0.00882   0.00363  -0.1391   0.3964   1.0000
   3.750   1.1482   0.00894   0.00373  -0.1385   0.3916   1.0000
   4.000   1.1711   0.00911   0.00386  -0.1375   0.3863   1.0000
   4.250   1.1925   0.00933   0.00402  -0.1364   0.3806   1.0000
   4.500   1.2166   0.00945   0.00414  -0.1357   0.3770   1.0000
   4.750   1.2394   0.00961   0.00428  -0.1348   0.3727   1.0000
   5.000   1.2608   0.00981   0.00444  -0.1336   0.3683   1.0000
   5.250   1.2817   0.01002   0.00463  -0.1324   0.3640   1.0000
   5.500   1.3037   0.01016   0.00477  -0.1313   0.3610   1.0000
   5.750   1.3240   0.01032   0.00493  -0.1299   0.3574   1.0000
   6.000   1.3432   0.01053   0.00512  -0.1284   0.3537   1.0000
   6.250   1.3606   0.01080   0.00536  -0.1265   0.3494   1.0000
   6.500   1.3821   0.01096   0.00554  -0.1254   0.3468   1.0000
   6.750   1.4035   0.01113   0.00573  -0.1244   0.3440   1.0000
   7.000   1.4236   0.01135   0.00595  -0.1231   0.3409   1.0000
   7.250   1.4430   0.01160   0.00620  -0.1218   0.3379   1.0000
   7.500   1.4609   0.01193   0.00651  -0.1202   0.3345   1.0000
   7.750   1.4814   0.01216   0.00676  -0.1191   0.3315   1.0000
   8.000   1.5031   0.01236   0.00698  -0.1183   0.3284   1.0000
   8.250   1.5228   0.01263   0.00726  -0.1171   0.3246   1.0000
   8.500   1.5404   0.01299   0.00761  -0.1157   0.3204   1.0000
   8.750   1.5589   0.01333   0.00796  -0.1144   0.3162   1.0000
   9.000   1.5801   0.01357   0.00824  -0.1136   0.3123   1.0000
   9.250   1.5988   0.01392   0.00859  -0.1125   0.3083   1.0000
   9.500   1.6143   0.01442   0.00907  -0.1109   0.3032   1.0000
   9.750   1.6346   0.01472   0.00942  -0.1100   0.2993   1.0000
  10.000   1.6535   0.01509   0.00982  -0.1090   0.2953   1.0000
  10.250   1.6704   0.01557   0.01031  -0.1078   0.2911   1.0000
  10.500   1.6856   0.01615   0.01088  -0.1064   0.2861   1.0000
  10.750   1.7050   0.01653   0.01131  -0.1055   0.2818   1.0000
  11.000   1.7206   0.01711   0.01190  -0.1043   0.2763   1.0000
  11.250   1.7352   0.01777   0.01257  -0.1029   0.2700   1.0000
  11.500   1.7497   0.01845   0.01325  -0.1017   0.2615   1.0000
  11.750   1.7619   0.01930   0.01408  -0.1002   0.2512   1.0000
  12.000   1.7710   0.02035   0.01510  -0.0984   0.2390   1.0000
  12.250   1.7758   0.02173   0.01641  -0.0963   0.2213   1.0000
  12.500   1.7692   0.02395   0.01846  -0.0932   0.1940   1.0000
  12.750   1.7530   0.02700   0.02131  -0.0896   0.1631   1.0000
  13.000   1.7349   0.03037   0.02452  -0.0862   0.1352   1.0000
  13.250   1.7124   0.03436   0.02835  -0.0830   0.1046   1.0000
  13.500   1.6896   0.03865   0.03252  -0.0803   0.0805   1.0000
  13.750   1.6729   0.04261   0.03642  -0.0782   0.0629   1.0000
  14.000   1.6471   0.04772   0.04144  -0.0763   0.0409   1.0000
  14.250   1.6275   0.05245   0.04615  -0.0749   0.0280   1.0000
  14.500   1.6177   0.05628   0.05002  -0.0741   0.0234   1.0000
  14.750   1.6107   0.05992   0.05373  -0.0735   0.0210   1.0000
  15.000   1.6067   0.06327   0.05716  -0.0730   0.0198   1.0000
  15.250   1.5995   0.06705   0.06101  -0.0727   0.0186   1.0000
  15.500   1.5912   0.07107   0.06510  -0.0724   0.0176   1.0000
  15.750   1.5877   0.07451   0.06863  -0.0723   0.0172   1.0000
  16.000   1.5816   0.07835   0.07255  -0.0722   0.0165   1.0000
  16.250   1.5751   0.08223   0.07652  -0.0722   0.0161   1.0000
  16.500   1.5667   0.08645   0.08081  -0.0723   0.0157   1.0000
  16.750   1.5569   0.09090   0.08535  -0.0726   0.0152   1.0000
  17.000   1.5464   0.09547   0.09001  -0.0729   0.0148   1.0000
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