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GOE 535 AIRFOIL (goe535-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 535 AIRFOIL (goe535-il)
Reynolds number: 200,000
Max Cl/Cd: 68.52 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe535-il-200000-n5.txt
Download as CSV file: xf-goe535-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 535 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.2470   0.09931   0.09528  -0.0556   0.9907   0.0434
 -10.500  -0.4916   0.03610   0.03089  -0.1191   0.9509   0.0468
 -10.250  -0.4792   0.03103   0.02522  -0.1264   0.9381   0.0480
 -10.000  -0.4417   0.02997   0.02415  -0.1297   0.9338   0.0487
  -9.750  -0.4171   0.02894   0.02306  -0.1305   0.9216   0.0493
  -9.500  -0.3847   0.02767   0.02166  -0.1330   0.9127   0.0502
  -9.250  -0.3565   0.02622   0.02002  -0.1346   0.9013   0.0513
  -9.000  -0.3293   0.02460   0.01810  -0.1361   0.8902   0.0526
  -8.750  -0.2974   0.02356   0.01693  -0.1376   0.8800   0.0537
  -8.500  -0.2682   0.02295   0.01627  -0.1382   0.8673   0.0546
  -8.250  -0.2362   0.02224   0.01545  -0.1394   0.8553   0.0558
  -8.000  -0.2070   0.02140   0.01440  -0.1401   0.8410   0.0577
  -7.750  -0.1786   0.02070   0.01354  -0.1404   0.8258   0.0592
  -7.500  -0.1494   0.02028   0.01306  -0.1407   0.8109   0.0605
  -7.250  -0.1208   0.01979   0.01242  -0.1408   0.7961   0.0621
  -7.000  -0.0942   0.01920   0.01161  -0.1406   0.7802   0.0641
  -6.750  -0.0676   0.01878   0.01109  -0.1403   0.7649   0.0656
  -6.500  -0.0408   0.01848   0.01071  -0.1400   0.7505   0.0672
  -6.250  -0.0144   0.01814   0.01022  -0.1396   0.7366   0.0694
  -6.000   0.0117   0.01777   0.00968  -0.1392   0.7236   0.0716
  -5.750   0.0377   0.01748   0.00933  -0.1387   0.7108   0.0732
  -5.500   0.0635   0.01721   0.00899  -0.1381   0.6976   0.0754
  -5.250   0.0897   0.01696   0.00859  -0.1376   0.6855   0.0778
  -5.000   0.1154   0.01666   0.00822  -0.1370   0.6735   0.0799
  -4.750   0.1413   0.01642   0.00795  -0.1365   0.6625   0.0821
  -4.500   0.1673   0.01621   0.00765  -0.1359   0.6510   0.0847
  -4.250   0.1934   0.01602   0.00734  -0.1353   0.6396   0.0871
  -4.000   0.2188   0.01576   0.00706  -0.1347   0.6281   0.0894
  -3.750   0.2447   0.01556   0.00683  -0.1341   0.6170   0.0919
  -3.500   0.2707   0.01541   0.00658  -0.1335   0.6066   0.0946
  -3.250   0.2966   0.01521   0.00635  -0.1329   0.5960   0.0970
  -3.000   0.3221   0.01505   0.00614  -0.1323   0.5853   0.0997
  -2.750   0.3482   0.01491   0.00597  -0.1317   0.5744   0.1028
  -2.500   0.3740   0.01484   0.00579  -0.1310   0.5641   0.1059
  -2.250   0.4001   0.01468   0.00563  -0.1305   0.5542   0.1094
  -2.000   0.4259   0.01461   0.00550  -0.1299   0.5445   0.1136
  -1.750   0.4521   0.01453   0.00538  -0.1293   0.5349   0.1187
  -1.500   0.4779   0.01445   0.00528  -0.1287   0.5253   0.1259
  -1.250   0.5040   0.01437   0.00519  -0.1282   0.5168   0.1369
  -1.000   0.5299   0.01425   0.00513  -0.1276   0.5084   0.1621
  -0.750   0.5552   0.01406   0.00506  -0.1271   0.5008   0.2181
  -0.500   0.5806   0.01387   0.00519  -0.1266   0.4929   0.3096
  -0.250   0.6063   0.01397   0.00532  -0.1259   0.4853   0.3567
   0.000   0.6325   0.01411   0.00542  -0.1253   0.4789   0.3813
   0.250   0.6588   0.01424   0.00554  -0.1247   0.4721   0.3984
   0.500   0.6847   0.01439   0.00564  -0.1240   0.4656   0.4129
   0.750   0.7106   0.01458   0.00577  -0.1233   0.4599   0.4280
   1.000   0.7366   0.01472   0.00594  -0.1227   0.4539   0.4404
   1.250   0.7626   0.01490   0.00606  -0.1221   0.4482   0.4531
   1.500   0.7877   0.01509   0.00624  -0.1213   0.4428   0.4640
   1.750   0.8137   0.01529   0.00639  -0.1207   0.4377   0.4760
   2.000   0.8391   0.01544   0.00660  -0.1200   0.4323   0.4857
   2.250   0.8645   0.01563   0.00674  -0.1193   0.4271   0.4950
   2.500   0.8896   0.01583   0.00688  -0.1185   0.4222   0.5015
   2.750   0.9150   0.01597   0.00705  -0.1179   0.4172   0.5064
   3.000   0.9402   0.01612   0.00720  -0.1172   0.4119   0.5112
   3.250   0.9649   0.01630   0.00733  -0.1164   0.4063   0.5166
   3.500   0.9892   0.01653   0.00747  -0.1157   0.4012   0.5219
   3.750   1.0138   0.01664   0.00767  -0.1149   0.3956   0.5266
   4.000   1.0380   0.01681   0.00785  -0.1141   0.3900   0.5318
   4.250   1.0618   0.01702   0.00802  -0.1132   0.3850   0.5376
   4.500   1.0857   0.01724   0.00822  -0.1124   0.3805   0.5429
   4.750   1.1096   0.01740   0.00845  -0.1116   0.3754   0.5484
   5.000   1.1329   0.01759   0.00867  -0.1106   0.3703   0.5550
   5.250   1.1555   0.01783   0.00888  -0.1096   0.3657   0.5619
   5.500   1.1778   0.01806   0.00912  -0.1085   0.3616   0.5688
   5.750   1.2004   0.01825   0.00939  -0.1075   0.3567   0.5767
   6.000   1.2222   0.01847   0.00965  -0.1064   0.3516   0.5837
   6.250   1.2435   0.01872   0.00990  -0.1052   0.3466   0.5915
   6.500   1.2651   0.01899   0.01019  -0.1041   0.3420   0.6000
   6.750   1.2864   0.01921   0.01050  -0.1030   0.3366   0.6090
   7.000   1.3063   0.01947   0.01080  -0.1016   0.3316   0.6190
   7.250   1.3255   0.01978   0.01111  -0.1001   0.3271   0.6315
   7.500   1.3460   0.02005   0.01150  -0.0990   0.3223   0.6477
   7.750   1.3659   0.02032   0.01191  -0.0977   0.3170   0.6731
   8.000   1.3957   0.02037   0.01233  -0.0986   0.3112   1.0000
   8.250   1.4126   0.02080   0.01276  -0.0969   0.3062   1.0000
   8.500   1.4294   0.02123   0.01322  -0.0952   0.3006   1.0000
   8.750   1.4445   0.02173   0.01371  -0.0934   0.2953   1.0000
   9.000   1.4592   0.02227   0.01423  -0.0915   0.2905   1.0000
   9.250   1.4748   0.02280   0.01480  -0.0899   0.2847   1.0000
   9.500   1.4879   0.02342   0.01543  -0.0879   0.2791   1.0000
   9.750   1.5000   0.02411   0.01610  -0.0860   0.2739   1.0000
  10.000   1.5134   0.02479   0.01683  -0.0843   0.2677   1.0000
  10.250   1.5241   0.02560   0.01764  -0.0823   0.2620   1.0000
  10.500   1.5346   0.02648   0.01852  -0.0805   0.2569   1.0000
  10.750   1.5459   0.02735   0.01945  -0.0788   0.2509   1.0000
  11.000   1.5547   0.02840   0.02050  -0.0770   0.2458   1.0000
  11.250   1.5634   0.02950   0.02161  -0.0753   0.2411   1.0000
  11.500   1.5732   0.03060   0.02279  -0.0739   0.2358   1.0000
  11.750   1.5809   0.03187   0.02408  -0.0724   0.2313   1.0000
  12.000   1.5864   0.03333   0.02552  -0.0708   0.2272   1.0000
  12.250   1.5955   0.03463   0.02692  -0.0696   0.2228   1.0000
  12.500   1.6013   0.03620   0.02855  -0.0684   0.2179   1.0000
  12.750   1.6053   0.03796   0.03032  -0.0672   0.2139   1.0000
  13.000   1.6102   0.03973   0.03214  -0.0661   0.2097   1.0000
  13.250   1.6151   0.04156   0.03405  -0.0652   0.2053   1.0000
  13.500   1.6168   0.04372   0.03625  -0.0643   0.2008   1.0000
  13.750   1.6174   0.04603   0.03858  -0.0635   0.1970   1.0000
  14.000   1.6218   0.04811   0.04077  -0.0630   0.1934   1.0000
  14.250   1.6243   0.05041   0.04315  -0.0624   0.1898   1.0000
  14.500   1.6250   0.05293   0.04572  -0.0620   0.1864   1.0000
  14.750   1.6242   0.05565   0.04845  -0.0616   0.1833   1.0000
  15.000   1.6261   0.05820   0.05112  -0.0614   0.1802   1.0000
  15.250   1.6262   0.06099   0.05402  -0.0613   0.1767   1.0000
  15.500   1.6244   0.06406   0.05716  -0.0613   0.1733   1.0000
  15.750   1.6210   0.06732   0.06044  -0.0614   0.1700   1.0000
  16.000   1.6192   0.07053   0.06377  -0.0617   0.1667   1.0000
  16.250   1.6162   0.07397   0.06732  -0.0620   0.1630   1.0000
  16.500   1.6109   0.07773   0.07115  -0.0626   0.1592   1.0000
  16.750   1.6051   0.08156   0.07501  -0.0632   0.1557   1.0000
  17.000   1.5997   0.08555   0.07916  -0.0640   0.1517   1.0000
  17.250   1.5924   0.08980   0.08350  -0.0649   0.1475   1.0000
  17.500   1.5850   0.09404   0.08776  -0.0659   0.1437   1.0000
  17.750   1.5770   0.09859   0.09246  -0.0672   0.1393   1.0000
  18.000   1.5671   0.10340   0.09735  -0.0686   0.1346   1.0000
  18.250   1.5581   0.10812   0.10214  -0.0701   0.1301   1.0000
  18.500   1.5469   0.11329   0.10741  -0.0719   0.1246   1.0000
  18.750   1.5359   0.11843   0.11260  -0.0737   0.1196   1.0000
  19.000   1.5241   0.12377   0.11803  -0.0758   0.1138   1.0000
  19.250   1.5127   0.12908   0.12338  -0.0780   0.1086   1.0000
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