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GOE 316 (HANSA-BRANDENBURG IV.5) AIRFOIL (goe316-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 316 (HANSA-BRANDENBURG IV.5) AIRFOIL (goe316-il)
Reynolds number: 1,000,000
Max Cl/Cd: 123.41 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe316-il-1000000.txt
Download as CSV file: xf-goe316-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 316 (HANSA-BRANDENBURG IV.5) 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4221   0.09555   0.09408  -0.0017   1.0000   0.0162
  -8.250  -0.4204   0.09127   0.08982  -0.0055   1.0000   0.0163
  -8.000  -0.4159   0.08685   0.08541  -0.0101   0.9780   0.0163
  -7.750  -0.4087   0.08235   0.08077  -0.0147   0.9038   0.0163
  -7.500  -0.4059   0.07768   0.07588  -0.0169   0.8475   0.0166
  -7.250  -0.3940   0.07537   0.07343  -0.0178   0.8168   0.0168
  -7.000  -0.3794   0.07264   0.07060  -0.0203   0.7965   0.0171
  -6.750  -0.3630   0.06942   0.06729  -0.0237   0.7814   0.0175
  -6.500  -0.3447   0.06575   0.06353  -0.0277   0.7695   0.0183
  -5.750  -0.2751   0.04773   0.04499  -0.0440   0.7411   0.0204
  -5.500  -0.2543   0.04599   0.04319  -0.0447   0.7306   0.0208
  -5.250  -0.2315   0.04387   0.04097  -0.0458   0.7211   0.0212
  -5.000  -0.2069   0.04138   0.03835  -0.0471   0.7118   0.0221
  -4.750  -0.1714   0.03697   0.03357  -0.0487   0.7046   0.0243
  -4.500  -0.1495   0.03100   0.02729  -0.0501   0.6972   0.0249
  -4.250  -0.1250   0.02950   0.02570  -0.0506   0.6884   0.0252
  -4.000  -0.0996   0.02816   0.02425  -0.0509   0.6787   0.0256
  -3.750  -0.0733   0.02676   0.02273  -0.0513   0.6686   0.0263
  -3.500  -0.0456   0.02515   0.02095  -0.0514   0.6581   0.0280
  -2.000   0.1221   0.00554   0.00018  -0.0497   0.5458   0.0361
  -1.000   0.2379   0.01181   0.00532  -0.0514   0.4903   0.0331
  -0.750   0.2663   0.01123   0.00458  -0.0514   0.4686   0.0333
  -0.500   0.2946   0.01074   0.00394  -0.0514   0.4417   0.0335
  -0.250   0.3227   0.01049   0.00351  -0.0514   0.4073   0.0339
   0.000   0.3507   0.01033   0.00320  -0.0514   0.3794   0.0345
   0.250   0.3789   0.01017   0.00295  -0.0515   0.3630   0.0349
   0.500   0.4072   0.01002   0.00274  -0.0515   0.3529   0.0353
   0.750   0.4355   0.00992   0.00258  -0.0516   0.3450   0.0358
   1.000   0.4641   0.00990   0.00255  -0.0517   0.3398   0.0363
   1.250   0.4925   0.00955   0.00216  -0.0519   0.3353   0.0383
   1.500   0.5210   0.00952   0.00211  -0.0520   0.3307   0.0397
   1.750   0.5495   0.00951   0.00209  -0.0521   0.3268   0.0412
   2.000   0.5781   0.00948   0.00207  -0.0522   0.3243   0.0429
   2.250   0.6066   0.00949   0.00208  -0.0523   0.3217   0.0445
   2.500   0.6352   0.00946   0.00204  -0.0524   0.3191   0.0493
   2.750   0.6636   0.00951   0.00208  -0.0525   0.3165   0.0546
   3.000   0.6871   0.00753   0.00229  -0.0522   0.3138   1.0000
   3.250   0.7154   0.00765   0.00237  -0.0523   0.3118   1.0000
   3.500   0.7438   0.00774   0.00245  -0.0524   0.3104   1.0000
   3.750   0.7722   0.00783   0.00253  -0.0525   0.3080   1.0000
   4.000   0.8005   0.00793   0.00259  -0.0526   0.3034   1.0000
   4.250   0.8283   0.00811   0.00272  -0.0527   0.2983   1.0000
   4.500   0.8564   0.00823   0.00284  -0.0528   0.2962   1.0000
   4.750   0.8847   0.00832   0.00294  -0.0529   0.2946   1.0000
   5.000   0.9129   0.00842   0.00305  -0.0530   0.2926   1.0000
   5.250   0.9410   0.00852   0.00316  -0.0531   0.2900   1.0000
   5.500   0.9689   0.00865   0.00328  -0.0532   0.2870   1.0000
   5.750   0.9965   0.00883   0.00345  -0.0533   0.2832   1.0000
   6.000   1.0245   0.00894   0.00358  -0.0534   0.2806   1.0000
   6.250   1.0526   0.00901   0.00370  -0.0535   0.2776   1.0000
   6.500   1.0805   0.00911   0.00379  -0.0536   0.2721   1.0000
   6.750   1.1080   0.00927   0.00394  -0.0537   0.2660   1.0000
   7.000   1.1360   0.00935   0.00406  -0.0538   0.2607   1.0000
   7.250   1.1633   0.00952   0.00421  -0.0539   0.2540   1.0000
   7.500   1.1909   0.00965   0.00435  -0.0540   0.2438   1.0000
   7.750   1.2174   0.00992   0.00454  -0.0540   0.2246   1.0000
   8.000   1.2396   0.01085   0.00512  -0.0536   0.1638   1.0000
   8.250   1.2620   0.01171   0.00577  -0.0532   0.1296   1.0000
   8.500   1.2835   0.01266   0.00648  -0.0527   0.0901   1.0000
   8.750   1.3044   0.01365   0.00726  -0.0521   0.0578   1.0000
   9.000   1.3284   0.01416   0.00777  -0.0518   0.0517   1.0000
   9.250   1.3527   0.01460   0.00823  -0.0515   0.0465   1.0000
   9.500   1.3758   0.01516   0.00877  -0.0511   0.0391   1.0000
   9.750   1.3975   0.01586   0.00939  -0.0506   0.0263   1.0000
  10.000   1.4180   0.01666   0.01014  -0.0499   0.0186   1.0000
  10.250   1.4387   0.01739   0.01087  -0.0492   0.0162   1.0000
  10.500   1.4593   0.01808   0.01162  -0.0485   0.0148   1.0000
  10.750   1.4797   0.01873   0.01233  -0.0477   0.0140   1.0000
  11.000   1.4985   0.01949   0.01315  -0.0468   0.0131   1.0000
  11.250   1.5140   0.02051   0.01424  -0.0455   0.0122   1.0000
  11.500   1.5287   0.02149   0.01531  -0.0442   0.0117   1.0000
  11.750   1.5450   0.02225   0.01614  -0.0430   0.0113   1.0000
  12.000   1.5583   0.02313   0.01709  -0.0415   0.0108   1.0000
  12.250   1.5661   0.02413   0.01816  -0.0392   0.0104   1.0000
  12.500   1.5719   0.02536   0.01948  -0.0372   0.0101   1.0000
  12.750   1.5757   0.02694   0.02115  -0.0355   0.0098   1.0000
  13.000   1.5761   0.02910   0.02340  -0.0343   0.0095   1.0000
  13.250   1.5711   0.03217   0.02660  -0.0338   0.0093   1.0000
  13.500   1.5594   0.03635   0.03094  -0.0339   0.0090   1.0000
  13.750   1.5617   0.03906   0.03374  -0.0342   0.0089   1.0000
  14.000   1.5612   0.04217   0.03696  -0.0346   0.0088   1.0000
  14.250   1.5585   0.04564   0.04054  -0.0352   0.0087   1.0000
  14.500   1.5535   0.04950   0.04451  -0.0360   0.0086   1.0000
  14.750   1.5461   0.05375   0.04888  -0.0369   0.0085   1.0000
  15.000   1.5372   0.05829   0.05354  -0.0380   0.0084   1.0000
  15.250   1.5269   0.06304   0.05839  -0.0392   0.0083   1.0000
  15.500   1.5153   0.06804   0.06350  -0.0405   0.0082   1.0000
  15.750   1.5038   0.07314   0.06870  -0.0419   0.0081   1.0000
  16.000   1.4926   0.07833   0.07400  -0.0434   0.0081   1.0000
  16.250   1.4819   0.08352   0.07928  -0.0450   0.0080   1.0000
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