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GOE 417 AIRFOIL (goe417-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 417 AIRFOIL (goe417-il)
Reynolds number: 500,000
Max Cl/Cd: 102.9 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe417-il-500000-n5.txt
Download as CSV file: xf-goe417-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 417 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.2871   0.11995   0.11766  -0.0275   1.0000   0.0083
 -10.000  -0.2851   0.11761   0.11535  -0.0270   1.0000   0.0083
  -9.750  -0.2845   0.11540   0.11317  -0.0262   1.0000   0.0083
  -9.500  -0.2737   0.11215   0.10993  -0.0292   0.9988   0.0084
  -9.250  -0.2616   0.10858   0.10636  -0.0306   0.9973   0.0088
  -9.000  -0.2470   0.10522   0.10301  -0.0337   0.9948   0.0089
  -8.750  -0.2326   0.10194   0.09973  -0.0367   0.9918   0.0092
  -8.500  -0.2170   0.09854   0.09633  -0.0401   0.9888   0.0094
  -8.250  -0.2005   0.09505   0.09285  -0.0438   0.9862   0.0096
  -8.000  -0.1862   0.09185   0.08965  -0.0468   0.9816   0.0100
  -7.750  -0.1691   0.08834   0.08614  -0.0508   0.9781   0.0105
  -7.250  -0.1353   0.08020   0.07799  -0.0599   0.9677   0.0079
  -7.000  -0.1129   0.07637   0.07414  -0.0655   0.9629   0.0078
  -6.750  -0.0914   0.07240   0.07017  -0.0711   0.9560   0.0080
  -6.500  -0.0659   0.06834   0.06608  -0.0775   0.9509   0.0080
  -6.250  -0.0455   0.06519   0.06291  -0.0817   0.9419   0.0088
  -6.000  -0.0222   0.06288   0.06057  -0.0853   0.9342   0.0099
  -5.750   0.0002   0.05927   0.05692  -0.0900   0.9241   0.0096
  -5.500   0.0214   0.05580   0.05340  -0.0939   0.9126   0.0095
  -5.250   0.0447   0.05245   0.04997  -0.0978   0.9015   0.0096
  -5.000   0.0701   0.04902   0.04646  -0.1019   0.8916   0.0100
  -4.750   0.0972   0.04538   0.04272  -0.1060   0.8806   0.0104
  -4.500   0.1287   0.04072   0.03792  -0.1112   0.8695   0.0116
  -4.250   0.1538   0.03897   0.03607  -0.1128   0.8569   0.0121
  -4.000   0.1821   0.03635   0.03331  -0.1152   0.8443   0.0127
  -3.750   0.2125   0.03323   0.03001  -0.1179   0.8321   0.0136
  -3.500   0.2482   0.02851   0.02500  -0.1215   0.8225   0.0156
  -3.250   0.2740   0.02737   0.02376  -0.1221   0.8123   0.0162
  -3.000   0.3027   0.02525   0.02146  -0.1232   0.8014   0.0172
  -2.750   0.3390   0.01954   0.01517  -0.1248   0.7918   0.0202
  -2.500   0.3642   0.01867   0.01416  -0.1249   0.7782   0.0208
  -2.250   0.3901   0.01786   0.01319  -0.1248   0.7641   0.0215
  -2.000   0.4165   0.01691   0.01205  -0.1247   0.7485   0.0229
  -1.750   0.4437   0.01533   0.01012  -0.1243   0.7302   0.0241
  -1.500   0.4699   0.01414   0.00857  -0.1238   0.7072   0.0248
  -1.250   0.4955   0.01342   0.00752  -0.1231   0.6808   0.0254
  -1.000   0.5210   0.01368   0.00752  -0.1223   0.6557   0.0265
  -0.750   0.5464   0.01261   0.00613  -0.1218   0.6351   0.0267
  -0.250   0.5973   0.01124   0.00433  -0.1208   0.5994   0.0277
   0.000   0.6228   0.01094   0.00390  -0.1203   0.5799   0.0281
   0.250   0.6477   0.01078   0.00358  -0.1197   0.5556   0.0286
   0.500   0.6726   0.01066   0.00331  -0.1191   0.5300   0.0290
   0.750   0.6975   0.01061   0.00314  -0.1185   0.5041   0.0298
   1.000   0.7223   0.01059   0.00300  -0.1179   0.4798   0.0306
   1.250   0.7470   0.01056   0.00284  -0.1172   0.4548   0.0305
   1.500   0.7714   0.01060   0.00273  -0.1165   0.4272   0.0304
   1.750   0.7960   0.01065   0.00267  -0.1159   0.4036   0.0304
   2.000   0.8209   0.01071   0.00263  -0.1154   0.3842   0.0305
   2.250   0.8456   0.01082   0.00264  -0.1148   0.3651   0.0310
   2.750   0.8958   0.01102   0.00271  -0.1138   0.3371   0.0325
   3.000   0.9214   0.01112   0.00277  -0.1133   0.3289   0.0336
   3.250   0.9469   0.01124   0.00285  -0.1129   0.3208   0.0346
   3.500   0.9725   0.01135   0.00295  -0.1125   0.3134   0.0354
   3.750   0.9978   0.01149   0.00305  -0.1120   0.3059   0.0383
   4.000   1.0233   0.01162   0.00319  -0.1116   0.2992   0.0418
   4.250   1.0485   0.01177   0.00334  -0.1111   0.2918   0.0451
   4.500   1.0723   0.01130   0.00372  -0.1108   0.2859   0.5623
   5.000   1.1267   0.01096   0.00411  -0.1108   0.2718   1.0000
   5.250   1.1514   0.01119   0.00430  -0.1103   0.2618   1.0000
   5.500   1.1757   0.01143   0.00453  -0.1097   0.2496   1.0000
   5.750   1.1998   0.01170   0.00476  -0.1091   0.2375   1.0000
   6.000   1.2233   0.01202   0.00501  -0.1084   0.2214   1.0000
   6.250   1.2442   0.01257   0.00537  -0.1074   0.1887   1.0000
   6.500   1.2651   0.01312   0.00579  -0.1064   0.1641   1.0000
   7.000   1.3079   0.01411   0.00662  -0.1045   0.1332   1.0000
   7.250   1.3291   0.01460   0.00706  -0.1035   0.1195   1.0000
   7.500   1.3498   0.01512   0.00753  -0.1025   0.1051   1.0000
   7.750   1.3632   0.01632   0.00840  -0.1004   0.0514   1.0000
   8.000   1.3763   0.01753   0.00944  -0.0982   0.0174   1.0000
   8.250   1.3951   0.01816   0.01010  -0.0968   0.0128   1.0000
   8.500   1.4145   0.01869   0.01072  -0.0955   0.0113   1.0000
   8.750   1.4327   0.01929   0.01141  -0.0941   0.0099   1.0000
   9.000   1.4485   0.02006   0.01227  -0.0923   0.0085   1.0000
   9.250   1.4628   0.02080   0.01311  -0.0902   0.0079   1.0000
   9.500   1.4767   0.02149   0.01389  -0.0880   0.0074   1.0000
   9.750   1.4891   0.02224   0.01473  -0.0857   0.0068   1.0000
  10.000   1.5003   0.02308   0.01566  -0.0833   0.0064   1.0000
  10.250   1.5104   0.02399   0.01665  -0.0809   0.0060   1.0000
  10.500   1.5167   0.02517   0.01793  -0.0781   0.0056   1.0000
  10.750   1.5227   0.02639   0.01926  -0.0753   0.0053   1.0000
  11.000   1.5310   0.02747   0.02045  -0.0731   0.0050   1.0000
  11.250   1.5355   0.02887   0.02197  -0.0705   0.0048   1.0000
  11.500   1.5395   0.03036   0.02358  -0.0681   0.0046   1.0000
  11.750   1.5424   0.03200   0.02533  -0.0659   0.0044   1.0000
  12.000   1.5431   0.03391   0.02737  -0.0637   0.0043   1.0000
  12.250   1.5434   0.03597   0.02954  -0.0618   0.0042   1.0000
  12.500   1.5422   0.03831   0.03200  -0.0601   0.0041   1.0000
  12.750   1.5406   0.04082   0.03463  -0.0588   0.0040   1.0000
  13.000   1.5369   0.04373   0.03768  -0.0578   0.0039   1.0000
  13.250   1.5314   0.04704   0.04111  -0.0571   0.0038   1.0000
  13.500   1.5231   0.05094   0.04514  -0.0568   0.0037   1.0000
  13.750   1.5127   0.05541   0.04976  -0.0571   0.0036   1.0000
  14.000   1.5014   0.06026   0.05476  -0.0578   0.0036   1.0000
  14.250   1.4919   0.06515   0.05979  -0.0589   0.0035   1.0000
  14.500   1.4832   0.07009   0.06488  -0.0601   0.0035   1.0000
  14.750   1.4757   0.07504   0.06997  -0.0616   0.0035   1.0000
  15.000   1.4669   0.08032   0.07539  -0.0632   0.0034   1.0000
  15.250   1.4582   0.08575   0.08096  -0.0651   0.0034   1.0000
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