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GOE 803 (HACKLINGER) AIRFOIL (goe803h-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 803 (HACKLINGER) AIRFOIL (goe803h-il)
Reynolds number: 100,000
Max Cl/Cd: 69.15 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe803h-il-100000.txt
Download as CSV file: xf-goe803h-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 803 (HACKLINGER) 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -6.750  -0.2559   0.10181   0.09734  -0.0196   1.0000   0.0497
  -6.500  -0.2680   0.10194   0.09759  -0.0176   1.0000   0.0500
  -6.250  -0.2787   0.10221   0.09796  -0.0167   1.0000   0.0502
  -6.000  -0.2849   0.10247   0.09830  -0.0177   1.0000   0.0504
  -5.750  -0.2835   0.10248   0.09836  -0.0213   1.0000   0.0506
  -5.500  -0.2671   0.09858   0.09448  -0.0249   0.9973   0.0509
  -5.250  -0.2551   0.09254   0.08846  -0.0220   0.9939   0.0517
  -5.000  -0.2302   0.08817   0.08407  -0.0253   0.9879   0.0530
  -4.750  -0.1973   0.08426   0.08013  -0.0318   0.9815   0.0548
  -4.500  -0.1597   0.08051   0.07634  -0.0400   0.9744   0.0571
  -4.250  -0.0710   0.07821   0.07381  -0.0669   0.9646   0.0610
  -4.000  -0.0620   0.07272   0.06840  -0.0635   0.9604   0.0620
  -3.750  -0.0398   0.06923   0.06490  -0.0653   0.9525   0.0638
  -3.500   0.0038   0.06552   0.06114  -0.0730   0.9473   0.0671
  -3.250   0.0991   0.06314   0.05840  -0.0966   0.9391   0.0728
  -3.000   0.1140   0.05821   0.05358  -0.0953   0.9342   0.0743
  -2.750   0.1449   0.05506   0.05044  -0.0984   0.9277   0.0775
  -2.500   0.2226   0.05195   0.04704  -0.1140   0.9217   0.0869
  -2.250   0.2544   0.04827   0.04343  -0.1163   0.9180   0.0917
  -2.000   0.3184   0.04559   0.04049  -0.1273   0.9112   0.1019
  -1.750   0.3565   0.04262   0.03753  -0.1309   0.9059   0.1091
  -1.500   0.4175   0.03948   0.03425  -0.1396   0.9029   0.1224
  -1.250   0.4782   0.03787   0.03230  -0.1478   0.8956   0.1465
  -1.000   0.5190   0.03452   0.02903  -0.1512   0.8884   0.1659
  -0.750   0.5634   0.03219   0.02661  -0.1547   0.8770   0.1979
  -0.500   0.6057   0.02989   0.02425  -0.1574   0.8657   0.2449
   0.250   0.6844   0.02503   0.01960  -0.1554   0.8316   0.4616
   0.500   0.7751   0.02415   0.01721  -0.1666   0.8222   0.2080
   0.750   0.8154   0.02251   0.01489  -0.1668   0.8106   0.1285
   1.000   0.8468   0.02154   0.01370  -0.1667   0.7993   0.1263
   1.250   0.8789   0.02062   0.01254  -0.1664   0.7892   0.1242
   1.500   0.9068   0.02008   0.01185  -0.1656   0.7762   0.1265
   1.750   0.9348   0.01958   0.01121  -0.1648   0.7633   0.1330
   2.000   0.9624   0.01912   0.01072  -0.1640   0.7501   0.1429
   2.250   0.9898   0.01865   0.01022  -0.1630   0.7366   0.1529
   2.500   1.0169   0.01831   0.00983  -0.1620   0.7222   0.1702
   2.750   1.0443   0.01807   0.00953  -0.1610   0.7067   0.1917
   3.000   1.0677   0.01671   0.00944  -0.1595   0.6911   1.0000
   3.250   1.0932   0.01684   0.00926  -0.1581   0.6729   1.0000
   3.500   1.1181   0.01695   0.00921  -0.1568   0.6525   1.0000
   3.750   1.1432   0.01702   0.00911  -0.1555   0.6308   1.0000
   4.000   1.1671   0.01713   0.00909  -0.1540   0.6046   1.0000
   4.250   1.1909   0.01728   0.00907  -0.1526   0.5755   1.0000
   4.500   1.2142   0.01756   0.00914  -0.1511   0.5434   1.0000
   4.750   1.2372   0.01801   0.00935  -0.1497   0.5121   1.0000
   5.000   1.2606   0.01858   0.00964  -0.1485   0.4854   1.0000
   5.250   1.2839   0.01920   0.01015  -0.1475   0.4611   1.0000
   5.500   1.3078   0.01986   0.01064  -0.1466   0.4423   1.0000
   5.750   1.3320   0.02053   0.01120  -0.1458   0.4265   1.0000
   6.000   1.3560   0.02120   0.01181  -0.1451   0.4119   1.0000
   6.250   1.3799   0.02188   0.01243  -0.1443   0.3986   1.0000
   6.500   1.4041   0.02259   0.01308  -0.1436   0.3872   1.0000
   6.750   1.4288   0.02332   0.01372  -0.1430   0.3768   1.0000
   7.000   1.4517   0.02402   0.01452  -0.1422   0.3655   1.0000
   7.250   1.4749   0.02476   0.01525  -0.1414   0.3547   1.0000
   7.750   1.5203   0.02620   0.01674  -0.1396   0.3336   1.0000
   8.000   1.5428   0.02700   0.01761  -0.1388   0.3241   1.0000
   8.250   1.5657   0.02774   0.01833  -0.1380   0.3144   1.0000
   8.500   1.5859   0.02854   0.01934  -0.1368   0.3047   1.0000
   8.750   1.6093   0.02940   0.02014  -0.1361   0.2961   1.0000
   9.000   1.6277   0.03010   0.02107  -0.1347   0.2855   1.0000
   9.250   1.6459   0.03086   0.02196  -0.1332   0.2746   1.0000
   9.500   1.6656   0.03158   0.02268  -0.1320   0.2641   1.0000
   9.750   1.6818   0.03223   0.02351  -0.1302   0.2530   1.0000
  10.000   1.6958   0.03297   0.02449  -0.1281   0.2414   1.0000
  10.250   1.7094   0.03368   0.02533  -0.1260   0.2296   1.0000
  10.500   1.7205   0.03436   0.02611  -0.1235   0.2168   1.0000
  10.750   1.7262   0.03509   0.02699  -0.1202   0.2020   1.0000
  11.000   1.7257   0.03596   0.02809  -0.1161   0.1844   1.0000
  11.250   1.7195   0.03706   0.02929  -0.1113   0.1660   1.0000
  11.500   1.7117   0.03863   0.03083  -0.1068   0.1499   1.0000
  11.750   1.7054   0.04075   0.03287  -0.1032   0.1364   1.0000
  12.000   1.7020   0.04316   0.03528  -0.1001   0.1260   1.0000
  12.250   1.7005   0.04568   0.03774  -0.0975   0.1185   1.0000
  12.500   1.7005   0.04812   0.04027  -0.0953   0.1118   1.0000
  12.750   1.7031   0.05064   0.04276  -0.0932   0.1063   1.0000
  13.000   1.7043   0.05322   0.04555  -0.0913   0.1016   1.0000
  13.250   1.7077   0.05561   0.04790  -0.0896   0.0967   1.0000
  13.500   1.7054   0.05859   0.05109  -0.0880   0.0924   1.0000
  13.750   1.6993   0.06170   0.05440  -0.0868   0.0882   1.0000
  14.000   1.7021   0.06421   0.05673  -0.0855   0.0829   1.0000
  14.250   1.6897   0.06818   0.06109  -0.0848   0.0803   1.0000
  14.500   1.6810   0.07196   0.06510  -0.0843   0.0769   1.0000
  14.750   1.6807   0.07483   0.06791  -0.0836   0.0731   1.0000
  15.000   1.6739   0.07885   0.07210  -0.0830   0.0702   1.0000
  15.250   1.6601   0.08371   0.07728  -0.0833   0.0680   1.0000
  15.500   1.6493   0.08827   0.08203  -0.0838   0.0654   1.0000
  15.750   1.6561   0.09068   0.08425  -0.0823   0.0608   1.0000
  16.000   1.6376   0.09660   0.09052  -0.0838   0.0598   1.0000
  16.250   1.6191   0.10292   0.09715  -0.0858   0.0587   1.0000
  16.500   1.6006   0.10956   0.10408  -0.0883   0.0576   1.0000
  16.750   1.5817   0.11663   0.11141  -0.0915   0.0568   1.0000
  17.000   1.5611   0.12444   0.11947  -0.0956   0.0563   1.0000
  17.250   1.5344   0.13412   0.12942  -0.1016   0.0566   1.0000
  17.500   1.5003   0.14642   0.14200  -0.1102   0.0579   1.0000
  17.750   1.4642   0.16035   0.15614  -0.1202   0.0595   1.0000
  18.000   1.4269   0.17616   0.17209  -0.1315   0.0613   1.0000
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