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GOE 322 (HANSA-BRANDENBURG IV.1) AIRFOIL (goe322-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 322 (HANSA-BRANDENBURG IV.1) AIRFOIL (goe322-il)
Reynolds number: 500,000
Max Cl/Cd: 104.81 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe322-il-500000.txt
Download as CSV file: xf-goe322-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 322 (HANSA-BRANDENBURG IV.1) AIRFOIL        
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.1874   0.08642   0.08321  -0.0398   0.7156   0.0287
  -7.750  -0.1817   0.08302   0.07980  -0.0425   0.7118   0.0297
  -7.500  -0.1815   0.07512   0.07183  -0.0592   0.7085   0.0309
  -7.250  -0.1740   0.07117   0.06791  -0.0599   0.7048   0.0312
  -7.000  -0.1606   0.06866   0.06539  -0.0606   0.7007   0.0315
  -6.750  -0.1455   0.06616   0.06286  -0.0620   0.6967   0.0318
  -6.500  -0.1292   0.06342   0.06006  -0.0642   0.6930   0.0323
  -6.250  -0.1112   0.06033   0.05692  -0.0672   0.6891   0.0329
  -6.000  -0.0912   0.05680   0.05333  -0.0709   0.6848   0.0340
  -5.750  -0.0643   0.04802   0.04423  -0.0803   0.6813   0.0369
  -5.500  -0.0449   0.04623   0.04239  -0.0807   0.6773   0.0373
  -5.250  -0.0235   0.04438   0.04048  -0.0815   0.6733   0.0379
  -5.000  -0.0002   0.04220   0.03822  -0.0827   0.6687   0.0388
  -4.750   0.0298   0.03561   0.03111  -0.0862   0.6650   0.0433
  -4.500   0.0527   0.03403   0.02948  -0.0866   0.6606   0.0439
  -4.250   0.0770   0.03272   0.02812  -0.0870   0.6555   0.0445
  -4.000   0.1026   0.03126   0.02659  -0.0875   0.6495   0.0457
  -3.750   0.1312   0.02767   0.02250  -0.0882   0.6445   0.0513
  -3.500   0.1569   0.02656   0.02137  -0.0885   0.6386   0.0522
  -3.250   0.1837   0.02548   0.02023  -0.0888   0.6326   0.0536
  -3.000   0.2130   0.02336   0.01760  -0.0889   0.6280   0.0601
  -2.750   0.2429   0.01791   0.01127  -0.0883   0.6240   0.0430
  -2.500   0.2709   0.01595   0.00918  -0.0884   0.6186   0.0415
  -2.250   0.2996   0.01479   0.00780  -0.0884   0.6136   0.0410
  -2.000   0.3284   0.01389   0.00672  -0.0884   0.6089   0.0405
  -1.750   0.3574   0.01321   0.00596  -0.0885   0.6031   0.0405
  -1.500   0.3861   0.01271   0.00537  -0.0885   0.5976   0.0408
  -1.250   0.4147   0.01232   0.00490  -0.0885   0.5927   0.0412
  -1.000   0.4436   0.01197   0.00453  -0.0886   0.5870   0.0416
  -0.750   0.4723   0.01170   0.00420  -0.0887   0.5816   0.0422
  -0.500   0.5010   0.01148   0.00394  -0.0888   0.5763   0.0431
  -0.250   0.5296   0.01114   0.00362  -0.0889   0.5702   0.0447
   0.000   0.5583   0.01099   0.00344  -0.0890   0.5647   0.0461
   0.250   0.5872   0.01088   0.00332  -0.0891   0.5592   0.0480
   0.500   0.6161   0.01079   0.00321  -0.0893   0.5524   0.0502
   0.750   0.6447   0.01072   0.00312  -0.0894   0.5456   0.0560
   1.000   0.6735   0.01060   0.00308  -0.0896   0.5379   0.0769
   1.250   0.7018   0.01050   0.00310  -0.0897   0.5311   0.1396
   1.500   0.7304   0.01031   0.00313  -0.0900   0.5243   0.2122
   1.750   0.7585   0.00854   0.00324  -0.0904   0.5175   1.0000
   2.000   0.7867   0.00864   0.00327  -0.0904   0.5104   1.0000
   2.250   0.8148   0.00875   0.00329  -0.0905   0.5027   1.0000
   2.500   0.8428   0.00887   0.00334  -0.0906   0.4949   1.0000
   2.750   0.8706   0.00900   0.00339  -0.0906   0.4858   1.0000
   3.000   0.8986   0.00911   0.00345  -0.0907   0.4765   1.0000
   3.250   0.9260   0.00928   0.00353  -0.0907   0.4670   1.0000
   3.500   0.9539   0.00940   0.00362  -0.0908   0.4571   1.0000
   3.750   0.9814   0.00957   0.00372  -0.0908   0.4474   1.0000
   4.000   1.0085   0.00976   0.00384  -0.0908   0.4365   1.0000
   4.250   1.0358   0.00993   0.00397  -0.0909   0.4249   1.0000
   4.500   1.0626   0.01014   0.00412  -0.0909   0.4131   1.0000
   4.750   1.0890   0.01039   0.00430  -0.0908   0.4011   1.0000
   5.000   1.1150   0.01067   0.00450  -0.0907   0.3892   1.0000
   5.250   1.1412   0.01092   0.00470  -0.0906   0.3778   1.0000
   5.500   1.1670   0.01120   0.00493  -0.0905   0.3677   1.0000
   5.750   1.1921   0.01153   0.00520  -0.0902   0.3580   1.0000
   6.000   1.2179   0.01179   0.00544  -0.0901   0.3493   1.0000
   6.250   1.2427   0.01213   0.00573  -0.0898   0.3413   1.0000
   6.500   1.2680   0.01240   0.00600  -0.0897   0.3336   1.0000
   6.750   1.2921   0.01276   0.00631  -0.0893   0.3255   1.0000
   7.000   1.3163   0.01309   0.00662  -0.0890   0.3158   1.0000
   7.250   1.3401   0.01344   0.00694  -0.0886   0.3068   1.0000
   7.500   1.3629   0.01383   0.00730  -0.0881   0.2978   1.0000
   7.750   1.3865   0.01416   0.00762  -0.0877   0.2883   1.0000
   8.000   1.4082   0.01460   0.00802  -0.0871   0.2789   1.0000
   8.250   1.4306   0.01497   0.00839  -0.0865   0.2696   1.0000
   8.500   1.4517   0.01539   0.00880  -0.0858   0.2600   1.0000
   8.750   1.4708   0.01592   0.00927  -0.0848   0.2491   1.0000
   9.000   1.4892   0.01644   0.00977  -0.0837   0.2375   1.0000
   9.250   1.5062   0.01701   0.01031  -0.0824   0.2258   1.0000
   9.500   1.5192   0.01767   0.01093  -0.0805   0.2149   1.0000
   9.750   1.5290   0.01847   0.01169  -0.0781   0.2050   1.0000
  10.000   1.5390   0.01936   0.01256  -0.0761   0.1950   1.0000
  10.250   1.5490   0.02035   0.01354  -0.0744   0.1859   1.0000
  10.500   1.5569   0.02159   0.01475  -0.0727   0.1771   1.0000
  10.750   1.5658   0.02289   0.01604  -0.0714   0.1686   1.0000
  11.000   1.5737   0.02439   0.01752  -0.0702   0.1590   1.0000
  11.250   1.5798   0.02614   0.01925  -0.0692   0.1494   1.0000
  11.500   1.5846   0.02804   0.02112  -0.0682   0.1372   1.0000
  11.750   1.5842   0.03046   0.02343  -0.0670   0.1161   1.0000
  12.000   1.5584   0.03521   0.02790  -0.0647   0.0742   1.0000
  12.250   1.5311   0.04026   0.03284  -0.0626   0.0439   1.0000
  12.500   1.5122   0.04466   0.03719  -0.0612   0.0227   1.0000
  12.750   1.5090   0.04761   0.04020  -0.0604   0.0204   1.0000
  13.000   1.5086   0.05038   0.04305  -0.0599   0.0191   1.0000
  13.250   1.5087   0.05317   0.04594  -0.0595   0.0184   1.0000
  13.500   1.5078   0.05617   0.04906  -0.0592   0.0178   1.0000
  13.750   1.5054   0.05944   0.05244  -0.0590   0.0173   1.0000
  14.000   1.5012   0.06302   0.05612  -0.0589   0.0169   1.0000
  14.250   1.4952   0.06688   0.06010  -0.0590   0.0165   1.0000
  14.500   1.4871   0.07113   0.06447  -0.0591   0.0162   1.0000
  14.750   1.4791   0.07547   0.06892  -0.0595   0.0159   1.0000
  15.000   1.4730   0.07957   0.07314  -0.0599   0.0158   1.0000
  15.250   1.4654   0.08397   0.07765  -0.0604   0.0156   1.0000
  15.500   1.4568   0.08861   0.08241  -0.0611   0.0154   1.0000
  15.750   1.4471   0.09347   0.08739  -0.0619   0.0152   1.0000
  16.000   1.4361   0.09858   0.09262  -0.0629   0.0150   1.0000
  16.250   1.4245   0.10389   0.09805  -0.0641   0.0148   1.0000
  16.500   1.4128   0.10931   0.10358  -0.0654   0.0146   1.0000
  16.750   1.4008   0.11484   0.10922  -0.0668   0.0145   1.0000
  17.000   1.3887   0.12043   0.11493  -0.0685   0.0143   1.0000
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