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GOE 692 AIRFOIL (goe692-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 692 AIRFOIL (goe692-il)
Reynolds number: 200,000
Max Cl/Cd: 76.13 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe692-il-200000.txt
Download as CSV file: xf-goe692-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 692 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.1806   0.10254   0.09876  -0.0823   0.9714   0.0900
  -9.750  -0.3159   0.06424   0.06035  -0.1165   0.9571   0.0690
  -9.500  -0.3250   0.05920   0.05524  -0.1196   0.9474   0.0684
  -9.250  -0.3597   0.04789   0.04346  -0.1265   0.9385   0.0667
  -9.000  -0.3869   0.03975   0.03460  -0.1266   0.9279   0.0662
  -8.750  -0.3836   0.03541   0.02968  -0.1261   0.9213   0.0668
  -8.500  -0.3721   0.03248   0.02625  -0.1253   0.9144   0.0678
  -8.250  -0.3476   0.02991   0.02314  -0.1262   0.9111   0.0695
  -8.000  -0.3134   0.02849   0.02173  -0.1281   0.9091   0.0713
  -7.750  -0.2990   0.02784   0.02101  -0.1260   0.9000   0.0727
  -7.500  -0.2700   0.02649   0.01944  -0.1266   0.8962   0.0749
  -7.250  -0.2387   0.02513   0.01766  -0.1275   0.8933   0.0774
  -7.000  -0.2182   0.02405   0.01660  -0.1265   0.8861   0.0796
  -6.750  -0.1902   0.02341   0.01593  -0.1267   0.8807   0.0828
  -6.500  -0.1585   0.02261   0.01485  -0.1273   0.8771   0.0869
  -6.250  -0.1305   0.02167   0.01398  -0.1276   0.8726   0.0907
  -6.000  -0.1080   0.02127   0.01351  -0.1266   0.8649   0.0948
  -5.750  -0.0777   0.02046   0.01261  -0.1270   0.8605   0.1000
  -5.500  -0.0447   0.02002   0.01214  -0.1279   0.8572   0.1059
  -5.250  -0.0251   0.01969   0.01173  -0.1264   0.8482   0.1109
  -5.000   0.0045   0.01933   0.01140  -0.1266   0.8433   0.1167
  -4.750   0.0369   0.01885   0.01078  -0.1273   0.8397   0.1234
  -4.500   0.0578   0.01874   0.01075  -0.1261   0.8310   0.1288
  -4.250   0.0873   0.01853   0.01039  -0.1262   0.8258   0.1358
  -4.000   0.1188   0.01805   0.00996  -0.1268   0.8220   0.1431
  -3.750   0.1409   0.01805   0.00990  -0.1257   0.8136   0.1503
  -3.500   0.1691   0.01761   0.00953  -0.1257   0.8082   0.1582
  -3.250   0.2010   0.01733   0.00912  -0.1262   0.8042   0.1679
  -3.000   0.2229   0.01714   0.00905  -0.1252   0.7962   0.1771
  -2.750   0.2509   0.01681   0.00872  -0.1251   0.7906   0.1891
  -2.500   0.2823   0.01654   0.00838  -0.1256   0.7865   0.2033
  -2.250   0.3048   0.01643   0.00836  -0.1247   0.7790   0.2162
  -2.000   0.3322   0.01617   0.00814  -0.1245   0.7733   0.2305
  -1.750   0.3630   0.01589   0.00785  -0.1250   0.7692   0.2460
  -1.500   0.3868   0.01583   0.00785  -0.1243   0.7624   0.2608
  -1.250   0.4135   0.01566   0.00772  -0.1240   0.7566   0.2784
  -1.000   0.4434   0.01535   0.00749  -0.1243   0.7523   0.3007
  -0.750   0.4681   0.01520   0.00749  -0.1238   0.7463   0.3298
  -0.500   0.4924   0.01489   0.00746  -0.1233   0.7401   0.3846
  -0.250   0.5154   0.01406   0.00739  -0.1223   0.7356   0.5832
   0.000   0.5339   0.01349   0.00767  -0.1189   0.7308   0.8582
   0.250   0.5873   0.01359   0.00782  -0.1233   0.7246   0.9650
   0.500   0.6560   0.01356   0.00765  -0.1316   0.7198   0.9940
   0.750   0.6990   0.01353   0.00746  -0.1347   0.7154   1.0000
   1.000   0.7152   0.01370   0.00762  -0.1327   0.7081   1.0000
   1.250   0.7395   0.01372   0.00754  -0.1320   0.7025   1.0000
   1.500   0.7661   0.01375   0.00745  -0.1317   0.6977   1.0000
   1.750   0.7837   0.01394   0.00764  -0.1298   0.6904   1.0000
   2.000   0.8096   0.01397   0.00757  -0.1294   0.6848   1.0000
   2.250   0.8346   0.01407   0.00759  -0.1288   0.6792   1.0000
   2.500   0.8545   0.01423   0.00775  -0.1273   0.6720   1.0000
   2.750   0.8824   0.01426   0.00767  -0.1272   0.6663   1.0000
   3.000   0.9036   0.01443   0.00782  -0.1259   0.6589   1.0000
   3.250   0.9286   0.01447   0.00779  -0.1253   0.6510   1.0000
   3.500   0.9530   0.01456   0.00782  -0.1245   0.6431   1.0000
   3.750   0.9762   0.01466   0.00789  -0.1235   0.6347   1.0000
   4.000   1.0048   0.01478   0.00790  -0.1236   0.6285   1.0000
   4.250   1.0242   0.01498   0.00814  -0.1220   0.6200   1.0000
   4.500   1.0528   0.01507   0.00813  -0.1221   0.6131   1.0000
   4.750   1.0724   0.01527   0.00837  -0.1205   0.6041   1.0000
   5.000   1.0992   0.01535   0.00837  -0.1203   0.5962   1.0000
   5.250   1.1192   0.01555   0.00859  -0.1188   0.5870   1.0000
   5.500   1.1448   0.01563   0.00861  -0.1183   0.5786   1.0000
   5.750   1.1640   0.01583   0.00885  -0.1167   0.5690   1.0000
   6.000   1.1895   0.01593   0.00887  -0.1162   0.5604   1.0000
   6.250   1.2062   0.01612   0.00912  -0.1141   0.5498   1.0000
   6.500   1.2295   0.01626   0.00920  -0.1132   0.5406   1.0000
   6.750   1.2466   0.01647   0.00946  -0.1113   0.5303   1.0000
   7.000   1.2669   0.01668   0.00965  -0.1099   0.5207   1.0000
   7.250   1.2858   0.01689   0.00985  -0.1083   0.5106   1.0000
   7.500   1.3021   0.01716   0.01016  -0.1062   0.5001   1.0000
   7.750   1.3212   0.01742   0.01036  -0.1047   0.4901   1.0000
   8.000   1.3341   0.01773   0.01070  -0.1020   0.4786   1.0000
   8.250   1.3467   0.01808   0.01105  -0.0993   0.4675   1.0000
   8.500   1.3611   0.01847   0.01138  -0.0970   0.4564   1.0000
   8.750   1.3719   0.01893   0.01186  -0.0942   0.4440   1.0000
   9.000   1.3830   0.01946   0.01239  -0.0915   0.4315   1.0000
   9.250   1.3941   0.02005   0.01295  -0.0890   0.4189   1.0000
   9.500   1.4046   0.02070   0.01355  -0.0864   0.4060   1.0000
   9.750   1.4130   0.02145   0.01429  -0.0836   0.3922   1.0000
  10.000   1.4205   0.02229   0.01513  -0.0809   0.3779   1.0000
  10.250   1.4275   0.02322   0.01605  -0.0783   0.3635   1.0000
  10.500   1.4336   0.02425   0.01706  -0.0756   0.3491   1.0000
  10.750   1.4390   0.02540   0.01817  -0.0730   0.3347   1.0000
  11.000   1.4437   0.02665   0.01937  -0.0705   0.3209   1.0000
  11.250   1.4478   0.02800   0.02065  -0.0681   0.3076   1.0000
  11.500   1.4526   0.02940   0.02204  -0.0658   0.2944   1.0000
  11.750   1.4573   0.03085   0.02350  -0.0637   0.2821   1.0000
  12.000   1.4617   0.03238   0.02497  -0.0616   0.2711   1.0000
  12.250   1.4660   0.03396   0.02649  -0.0597   0.2606   1.0000
  12.500   1.4718   0.03550   0.02806  -0.0579   0.2506   1.0000
  12.750   1.4784   0.03699   0.02944  -0.0562   0.2422   1.0000
  13.000   1.4851   0.03855   0.03109  -0.0547   0.2340   1.0000
  13.250   1.4945   0.03990   0.03231  -0.0533   0.2269   1.0000
  13.500   1.5007   0.04155   0.03409  -0.0520   0.2201   1.0000
  13.750   1.5092   0.04300   0.03549  -0.0507   0.2140   1.0000
  14.000   1.5178   0.04449   0.03703  -0.0496   0.2083   1.0000
  14.250   1.5231   0.04627   0.03889  -0.0484   0.2025   1.0000
  14.500   1.5329   0.04763   0.04013  -0.0474   0.1965   1.0000
  14.750   1.5347   0.04982   0.04250  -0.0464   0.1914   1.0000
  15.000   1.5397   0.05172   0.04447  -0.0455   0.1866   1.0000
  15.250   1.5497   0.05309   0.04576  -0.0446   0.1819   1.0000
  15.500   1.5535   0.05522   0.04806  -0.0438   0.1780   1.0000
  15.750   1.5572   0.05738   0.05032  -0.0431   0.1736   1.0000
  16.000   1.5619   0.05940   0.05235  -0.0425   0.1694   1.0000
  16.250   1.5680   0.06130   0.05428  -0.0418   0.1653   1.0000
  16.500   1.5696   0.06381   0.05697  -0.0414   0.1615   1.0000
  16.750   1.5726   0.06616   0.05940  -0.0410   0.1579   1.0000
  17.000   1.5788   0.06806   0.06127  -0.0405   0.1541   1.0000
  17.250   1.5813   0.07052   0.06386  -0.0401   0.1508   1.0000
  17.500   1.5812   0.07338   0.06688  -0.0400   0.1472   1.0000
  17.750   1.5816   0.07616   0.06973  -0.0399   0.1435   1.0000
  18.000   1.5877   0.07803   0.07152  -0.0395   0.1395   1.0000
  18.250   1.5825   0.08172   0.07545  -0.0398   0.1362   1.0000
  18.500   1.5792   0.08515   0.07903  -0.0402   0.1322   1.0000
  18.750   1.5778   0.08823   0.08212  -0.0404   0.1282   1.0000
  19.000   1.5743   0.09173   0.08574  -0.0408   0.1243   1.0000
  19.250   1.5675   0.09585   0.09003  -0.0417   0.1200   1.0000
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