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GOE 323 (HANSA-BRANDENBURG V.1) AIRFOIL (goe323-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 323 (HANSA-BRANDENBURG V.1) AIRFOIL (goe323-il)
Reynolds number: 50,000
Max Cl/Cd: 29.31 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe323-il-50000-n5.txt
Download as CSV file: xf-goe323-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 323 (HANSA-BRANDENBURG V.1) AIRFOIL         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3005   0.11487   0.10895  -0.0131   1.0000   0.1044
  -9.000  -0.2946   0.11284   0.10685  -0.0179   0.9006   0.1091
  -8.750  -0.3009   0.11240   0.10636  -0.0245   0.8692   0.1108
  -8.500  -0.2858   0.10729   0.10120  -0.0236   0.8520   0.1124
  -8.250  -0.2694   0.10322   0.09704  -0.0221   0.8373   0.1154
  -8.000  -0.2603   0.10037   0.09412  -0.0227   0.8246   0.1189
  -7.750  -0.2555   0.09797   0.09168  -0.0248   0.8133   0.1232
  -7.500  -0.2612   0.09719   0.09087  -0.0344   0.8027   0.1269
  -7.250  -0.2498   0.09297   0.08663  -0.0340   0.7951   0.1286
  -7.000  -0.2334   0.08925   0.08289  -0.0311   0.7874   0.1325
  -6.750  -0.2231   0.08664   0.08022  -0.0334   0.7802   0.1393
  -6.500  -0.2153   0.08399   0.07751  -0.0412   0.7732   0.1453
  -6.250  -0.2001   0.08060   0.07413  -0.0383   0.7666   0.1502
  -5.750  -0.1728   0.07486   0.06827  -0.0449   0.7546   0.1642
  -5.500  -0.1567   0.07214   0.06552  -0.0456   0.7490   0.1711
  -5.250  -0.1409   0.06931   0.06256  -0.0493   0.7443   0.1805
  -5.000  -0.1229   0.06672   0.05995  -0.0504   0.7384   0.1890
  -4.750  -0.1054   0.06395   0.05712  -0.0524   0.7330   0.1993
  -4.500  -0.0872   0.06149   0.05456  -0.0542   0.7284   0.2142
  -4.250  -0.0693   0.05912   0.05217  -0.0549   0.7233   0.2317
  -3.750   0.0176   0.04955   0.04114  -0.0688   0.7141   0.0938
  -3.500   0.0414   0.04717   0.03858  -0.0693   0.7099   0.0901
  -3.250   0.0691   0.04470   0.03574  -0.0708   0.7044   0.0852
  -3.000   0.0982   0.04279   0.03331  -0.0716   0.6997   0.0815
  -2.750   0.1244   0.04112   0.03133  -0.0718   0.6957   0.0813
  -2.500   0.1515   0.03976   0.02963  -0.0723   0.6908   0.0819
  -2.250   0.1783   0.03853   0.02808  -0.0726   0.6855   0.0822
  -2.000   0.2049   0.03726   0.02655  -0.0725   0.6810   0.0819
  -1.750   0.2317   0.03615   0.02517  -0.0724   0.6767   0.0817
  -1.500   0.2583   0.03531   0.02414  -0.0726   0.6707   0.0816
  -1.250   0.2854   0.03448   0.02305  -0.0723   0.6656   0.0818
  -1.000   0.3126   0.03366   0.02200  -0.0718   0.6614   0.0832
  -0.750   0.3378   0.03323   0.02159  -0.0721   0.6540   0.0858
  -0.500   0.3647   0.03270   0.02092  -0.0716   0.6483   0.0884
  -0.250   0.3914   0.03227   0.02033  -0.0710   0.6424   0.0900
   0.000   0.4182   0.03202   0.01993  -0.0707   0.6349   0.0917
   0.250   0.4459   0.03159   0.01931  -0.0698   0.6297   0.0942
   0.500   0.4703   0.03155   0.01927  -0.0695   0.6219   0.0985
   0.750   0.4955   0.03135   0.01904  -0.0689   0.6156   0.1045
   1.000   0.5213   0.03118   0.01872  -0.0680   0.6101   0.1099
   1.250   0.5444   0.03132   0.01894  -0.0678   0.6016   0.1172
   1.500   0.5707   0.03106   0.01866  -0.0670   0.5962   0.1320
   1.750   0.5939   0.03126   0.01904  -0.0668   0.5877   0.1573
   2.000   0.6249   0.02914   0.01888  -0.0667   0.5812   1.0000
   2.250   0.6492   0.02956   0.01899  -0.0659   0.5740   1.0000
   2.500   0.6724   0.03004   0.01929  -0.0653   0.5655   1.0000
   2.750   0.6999   0.02998   0.01899  -0.0642   0.5606   1.0000
   3.000   0.7195   0.03088   0.01986  -0.0638   0.5494   1.0000
   3.250   0.7470   0.03076   0.01955  -0.0628   0.5441   1.0000
   3.500   0.7663   0.03165   0.02045  -0.0624   0.5327   1.0000
   3.750   0.7941   0.03146   0.02010  -0.0613   0.5273   1.0000
   4.000   0.8128   0.03237   0.02103  -0.0608   0.5155   1.0000
   4.500   0.8591   0.03303   0.02161  -0.0593   0.4980   1.0000
   4.750   0.8818   0.03339   0.02194  -0.0585   0.4890   1.0000
   5.000   0.9054   0.03361   0.02215  -0.0576   0.4803   1.0000
   5.250   0.9244   0.03437   0.02294  -0.0569   0.4695   1.0000
   5.500   0.9517   0.03411   0.02261  -0.0560   0.4627   1.0000
   5.750   0.9678   0.03517   0.02375  -0.0553   0.4509   1.0000
   6.000   0.9931   0.03514   0.02369  -0.0544   0.4436   1.0000
   6.250   1.0116   0.03587   0.02446  -0.0536   0.4332   1.0000
   6.500   1.0284   0.03679   0.02544  -0.0528   0.4229   1.0000
   6.750   1.0548   0.03661   0.02523  -0.0519   0.4161   1.0000
   7.000   1.0676   0.03796   0.02667  -0.0511   0.4053   1.0000
   7.250   1.0972   0.03744   0.02609  -0.0501   0.3996   1.0000
   7.500   1.1061   0.03919   0.02797  -0.0494   0.3889   1.0000
   7.750   1.1351   0.03878   0.02751  -0.0484   0.3832   1.0000
   8.000   1.1426   0.04064   0.02948  -0.0476   0.3731   1.0000
   8.250   1.1709   0.04034   0.02916  -0.0466   0.3674   1.0000
   8.500   1.1746   0.04257   0.03152  -0.0457   0.3580   1.0000
   8.750   1.2071   0.04196   0.03086  -0.0448   0.3531   1.0000
   9.000   1.1988   0.04525   0.03432  -0.0438   0.3438   1.0000
   9.250   1.2298   0.04483   0.03389  -0.0429   0.3383   1.0000
   9.500   1.2166   0.04860   0.03782  -0.0420   0.3300   1.0000
   9.750   1.2355   0.04931   0.03856  -0.0411   0.3241   1.0000
  10.000   1.2510   0.05047   0.03977  -0.0403   0.3186   1.0000
  10.250   1.2221   0.05669   0.04617  -0.0410   0.3098   1.0000
  10.500   1.2661   0.05439   0.04389  -0.0391   0.3058   1.0000
  10.750   1.1869   0.06766   0.05735  -0.0426   0.2941   1.0000
  11.000   1.2325   0.06442   0.05416  -0.0402   0.2906   1.0000
  11.250   1.1423   0.08097   0.07081  -0.0456   0.2771   1.0000
  11.500   1.1910   0.07650   0.06643  -0.0425   0.2744   1.0000
  12.000   1.1579   0.08806   0.07812  -0.0450   0.2581   1.0000
  12.500   1.1258   0.10033   0.09052  -0.0482   0.2423   1.0000
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