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GOE 567 AIRFOIL (goe567-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 567 AIRFOIL (goe567-il)
Reynolds number: 100,000
Max Cl/Cd: 55.96 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe567-il-100000-n5.txt
Download as CSV file: xf-goe567-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 567 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.2969   0.09411   0.08898  -0.0656   0.9837   0.0711
 -10.000  -0.2993   0.08668   0.08153  -0.0726   0.9744   0.0728
  -9.750  -0.4365   0.05051   0.04498  -0.1128   0.9387   0.0746
  -9.500  -0.4325   0.04363   0.03757  -0.1226   0.9266   0.0763
  -9.250  -0.4133   0.04189   0.03576  -0.1238   0.9156   0.0778
  -9.000  -0.3904   0.03926   0.03288  -0.1270   0.9079   0.0794
  -8.750  -0.3695   0.03701   0.03036  -0.1290   0.8981   0.0815
  -8.500  -0.3465   0.03462   0.02757  -0.1313   0.8898   0.0840
  -8.250  -0.3228   0.03235   0.02482  -0.1332   0.8814   0.0862
  -8.000  -0.2968   0.03050   0.02248  -0.1347   0.8736   0.0879
  -7.750  -0.2700   0.02909   0.02105  -0.1355   0.8660   0.0899
  -7.500  -0.2394   0.02803   0.01988  -0.1367   0.8601   0.0923
  -7.250  -0.2144   0.02707   0.01876  -0.1369   0.8514   0.0946
  -7.000  -0.1832   0.02592   0.01736  -0.1381   0.8456   0.0970
  -6.750  -0.1582   0.02505   0.01626  -0.1380   0.8371   0.0993
  -6.500  -0.1283   0.02416   0.01512  -0.1388   0.8308   0.1020
  -6.250  -0.1016   0.02340   0.01437  -0.1389   0.8236   0.1045
  -6.000  -0.0740   0.02276   0.01367  -0.1391   0.8164   0.1072
  -5.750  -0.0436   0.02210   0.01289  -0.1397   0.8109   0.1102
  -5.500  -0.0186   0.02164   0.01231  -0.1393   0.8027   0.1136
  -5.250   0.0107   0.02107   0.01164  -0.1397   0.7967   0.1172
  -5.000   0.0369   0.02063   0.01120  -0.1395   0.7898   0.1208
  -4.750   0.0640   0.02023   0.01074  -0.1395   0.7829   0.1248
  -4.250   0.1184   0.01951   0.00993  -0.1394   0.7698   0.1357
  -4.000   0.1470   0.01918   0.00953  -0.1396   0.7637   0.1436
  -3.750   0.1745   0.01884   0.00920  -0.1397   0.7575   0.1526
  -3.500   0.2007   0.01856   0.00893  -0.1395   0.7504   0.1652
  -3.250   0.2299   0.01821   0.00862  -0.1399   0.7449   0.1877
  -3.000   0.2559   0.01797   0.00848  -0.1397   0.7381   0.2190
  -2.750   0.2830   0.01779   0.00839  -0.1397   0.7315   0.2548
  -2.500   0.3128   0.01766   0.00826  -0.1399   0.7265   0.2884
  -2.250   0.3375   0.01769   0.00834  -0.1394   0.7190   0.3158
  -2.000   0.3653   0.01769   0.00833  -0.1393   0.7129   0.3429
  -1.750   0.3940   0.01772   0.00832  -0.1393   0.7075   0.3663
  -1.500   0.4187   0.01782   0.00846  -0.1387   0.7002   0.3868
  -1.250   0.4469   0.01788   0.00848  -0.1385   0.6945   0.4098
  -1.000   0.4738   0.01800   0.00858  -0.1382   0.6886   0.4330
  -0.750   0.4990   0.01813   0.00875  -0.1376   0.6817   0.4524
  -0.500   0.5273   0.01819   0.00878  -0.1375   0.6765   0.4709
  -0.250   0.5527   0.01831   0.00890  -0.1370   0.6701   0.4864
   0.000   0.5786   0.01839   0.00898  -0.1365   0.6636   0.4995
   0.250   0.6072   0.01840   0.00895  -0.1365   0.6587   0.5119
   0.500   0.6313   0.01854   0.00911  -0.1358   0.6520   0.5241
   0.750   0.6577   0.01862   0.00918  -0.1355   0.6460   0.5374
   1.000   0.6865   0.01862   0.00914  -0.1354   0.6414   0.5503
   1.250   0.7092   0.01878   0.00938  -0.1345   0.6343   0.5624
   1.500   0.7357   0.01886   0.00946  -0.1342   0.6288   0.5756
   1.750   0.7649   0.01888   0.00944  -0.1342   0.6243   0.5897
   2.000   0.7874   0.01908   0.00973  -0.1334   0.6172   0.6036
   2.250   0.8142   0.01914   0.00981  -0.1331   0.6118   0.6180
   2.500   0.8423   0.01918   0.00985  -0.1330   0.6074   0.6338
   2.750   0.8645   0.01938   0.01018  -0.1320   0.6006   0.6502
   3.000   0.8910   0.01941   0.01026  -0.1317   0.5951   0.6700
   3.250   0.9170   0.01943   0.01036  -0.1312   0.5900   0.6935
   3.500   0.9380   0.01951   0.01063  -0.1299   0.5828   0.7260
   3.750   0.9608   0.01920   0.01060  -0.1284   0.5772   0.8116
   4.000   0.9871   0.01932   0.01080  -0.1282   0.5695   1.0000
   4.250   1.0135   0.01950   0.01091  -0.1280   0.5626   1.0000
   4.500   1.0389   0.01972   0.01109  -0.1276   0.5559   1.0000
   4.750   1.0622   0.02001   0.01139  -0.1268   0.5486   1.0000
   5.000   1.0906   0.02016   0.01146  -0.1268   0.5432   1.0000
   5.250   1.1108   0.02058   0.01195  -0.1257   0.5362   1.0000
   5.500   1.1357   0.02085   0.01222  -0.1252   0.5301   1.0000
   5.750   1.1605   0.02111   0.01247  -0.1247   0.5241   1.0000
   6.000   1.1806   0.02146   0.01287  -0.1234   0.5159   1.0000
   6.250   1.2049   0.02164   0.01302  -0.1227   0.5080   1.0000
   6.500   1.2230   0.02197   0.01341  -0.1211   0.4981   1.0000
   6.750   1.2430   0.02225   0.01369  -0.1197   0.4889   1.0000
   7.000   1.2625   0.02256   0.01402  -0.1183   0.4799   1.0000
   7.250   1.2806   0.02296   0.01449  -0.1168   0.4717   1.0000
   7.500   1.2992   0.02332   0.01490  -0.1153   0.4636   1.0000
   7.750   1.3165   0.02376   0.01540  -0.1136   0.4560   1.0000
   8.000   1.3320   0.02420   0.01592  -0.1117   0.4481   1.0000
   8.250   1.3459   0.02466   0.01644  -0.1095   0.4397   1.0000
   8.500   1.3582   0.02513   0.01695  -0.1071   0.4299   1.0000
   8.750   1.3667   0.02578   0.01769  -0.1043   0.4196   1.0000
   9.000   1.3780   0.02636   0.01829  -0.1020   0.4094   1.0000
   9.250   1.3857   0.02713   0.01914  -0.0993   0.3985   1.0000
   9.500   1.3917   0.02803   0.02013  -0.0966   0.3868   1.0000
   9.750   1.3983   0.02898   0.02112  -0.0941   0.3750   1.0000
  10.000   1.4042   0.03002   0.02220  -0.0917   0.3628   1.0000
  10.250   1.4078   0.03129   0.02352  -0.0893   0.3493   1.0000
  10.500   1.4105   0.03273   0.02502  -0.0870   0.3352   1.0000
  10.750   1.4126   0.03431   0.02665  -0.0849   0.3207   1.0000
  11.000   1.4138   0.03607   0.02844  -0.0828   0.3053   1.0000
  11.250   1.4128   0.03808   0.03045  -0.0809   0.2881   1.0000
  11.500   1.4092   0.04042   0.03275  -0.0790   0.2692   1.0000
  11.750   1.4045   0.04302   0.03531  -0.0773   0.2501   1.0000
  12.000   1.3992   0.04580   0.03806  -0.0759   0.2325   1.0000
  12.250   1.3932   0.04880   0.04103  -0.0746   0.2157   1.0000
  12.500   1.3864   0.05201   0.04423  -0.0736   0.1995   1.0000
  12.750   1.3793   0.05543   0.04761  -0.0727   0.1837   1.0000
  13.000   1.3728   0.05893   0.05112  -0.0721   0.1697   1.0000
  13.250   1.3670   0.06247   0.05465  -0.0717   0.1584   1.0000
  13.500   1.3611   0.06615   0.05831  -0.0714   0.1490   1.0000
  13.750   1.3571   0.06970   0.06187  -0.0713   0.1409   1.0000
  14.000   1.3539   0.07319   0.06537  -0.0712   0.1342   1.0000
  14.250   1.3520   0.07660   0.06881  -0.0712   0.1274   1.0000
  14.500   1.3499   0.08004   0.07222  -0.0713   0.1215   1.0000
  14.750   1.3519   0.08305   0.07535  -0.0714   0.1154   1.0000
  15.000   1.3513   0.08636   0.07865  -0.0715   0.1097   1.0000
  15.250   1.3538   0.08936   0.08175  -0.0717   0.1041   1.0000
  15.500   1.3552   0.09261   0.08510  -0.0722   0.0984   1.0000
  15.750   1.3557   0.09593   0.08842  -0.0727   0.0937   1.0000
  16.000   1.3589   0.09909   0.09179  -0.0732   0.0880   1.0000
  16.250   1.3586   0.10274   0.09552  -0.0741   0.0833   1.0000
  16.500   1.3606   0.10609   0.09901  -0.0750   0.0782   1.0000
  16.750   1.3595   0.10999   0.10298  -0.0762   0.0740   1.0000
  17.000   1.3593   0.11373   0.10679  -0.0773   0.0703   1.0000
  17.250   1.3579   0.11772   0.11084  -0.0787   0.0671   1.0000
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