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GOE 394 AIRFOIL (goe394-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 394 AIRFOIL (goe394-il)
Reynolds number: 500,000
Max Cl/Cd: 107.95 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe394-il-500000-n5.txt
Download as CSV file: xf-goe394-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 394 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3194   0.09174   0.08879  -0.0200   0.7665   0.0107
  -7.750  -0.3125   0.08789   0.08493  -0.0227   0.7628   0.0110
  -7.500  -0.3056   0.08280   0.07983  -0.0272   0.7595   0.0117
  -7.250  -0.2918   0.07865   0.07566  -0.0319   0.7566   0.0123
  -7.000  -0.2738   0.07659   0.07355  -0.0346   0.7542   0.0127
  -6.750  -0.2549   0.07392   0.07087  -0.0381   0.7519   0.0133
  -6.500  -0.2345   0.06986   0.06679  -0.0435   0.7497   0.0141
  -6.250  -0.2065   0.06010   0.05695  -0.0571   0.7474   0.0162
  -6.000  -0.1820   0.05851   0.05532  -0.0598   0.7452   0.0166
  -5.750  -0.1567   0.05666   0.05343  -0.0628   0.7423   0.0173
  -5.250  -0.0757   0.04126   0.03770  -0.0858   0.7361   0.0218
  -5.000  -0.0456   0.03917   0.03552  -0.0891   0.7320   0.0225
  -4.500   0.0458   0.01750   0.01243  -0.1108   0.7267   0.0269
  -4.000   0.1035   0.01463   0.00893  -0.1122   0.7214   0.0283
  -3.750   0.1320   0.01378   0.00787  -0.1124   0.7186   0.0287
  -3.500   0.1605   0.01312   0.00702  -0.1126   0.7158   0.0290
  -3.250   0.1889   0.01259   0.00633  -0.1127   0.7130   0.0292
  -3.000   0.2172   0.01181   0.00533  -0.1128   0.7103   0.0296
  -2.750   0.2456   0.01118   0.00453  -0.1128   0.7075   0.0300
  -2.500   0.2740   0.01070   0.00396  -0.1129   0.7045   0.0305
  -2.250   0.3024   0.01033   0.00352  -0.1129   0.7012   0.0310
  -2.000   0.3307   0.01004   0.00316  -0.1128   0.6975   0.0320
  -1.750   0.3589   0.00982   0.00287  -0.1127   0.6942   0.0327
  -1.500   0.3874   0.00961   0.00264  -0.1127   0.6909   0.0332
  -1.250   0.4158   0.00943   0.00244  -0.1127   0.6872   0.0340
  -1.000   0.4441   0.00928   0.00225  -0.1126   0.6833   0.0351
  -0.750   0.4723   0.00917   0.00209  -0.1125   0.6798   0.0363
  -0.500   0.5007   0.00904   0.00196  -0.1124   0.6754   0.0378
  -0.250   0.5290   0.00894   0.00185  -0.1123   0.6703   0.0394
   0.000   0.5571   0.00883   0.00175  -0.1122   0.6654   0.0457
   0.250   0.5853   0.00874   0.00180  -0.1122   0.6595   0.0710
   0.500   0.6134   0.00875   0.00182  -0.1121   0.6521   0.0804
   0.750   0.6416   0.00875   0.00182  -0.1120   0.6441   0.0856
   1.000   0.6695   0.00878   0.00186  -0.1119   0.6332   0.0905
   1.250   0.6974   0.00879   0.00186  -0.1117   0.6168   0.0942
   1.500   0.7248   0.00885   0.00182  -0.1115   0.5875   0.0963
   1.750   0.7510   0.00900   0.00180  -0.1111   0.5461   0.0984
   2.000   0.7772   0.00924   0.00188  -0.1108   0.5127   0.1007
   2.250   0.8036   0.00950   0.00203  -0.1106   0.4872   0.1046
   2.500   0.8303   0.00970   0.00216  -0.1104   0.4667   0.1076
   2.750   0.8572   0.00985   0.00226  -0.1102   0.4517   0.1085
   3.000   0.8842   0.00998   0.00237  -0.1100   0.4399   0.1094
   3.250   0.9111   0.01010   0.00247  -0.1099   0.4277   0.1108
   3.500   0.9381   0.01021   0.00259  -0.1097   0.4155   0.1127
   3.750   0.9650   0.01035   0.00272  -0.1095   0.4040   0.1148
   4.000   0.9918   0.01049   0.00287  -0.1093   0.3944   0.1171
   4.250   1.0186   0.01062   0.00303  -0.1092   0.3846   0.1200
   4.750   1.0718   0.01095   0.00338  -0.1088   0.3625   0.1290
   5.000   1.0981   0.01114   0.00359  -0.1085   0.3489   0.1384
   5.250   1.1216   0.01039   0.00402  -0.1082   0.3357   0.8078
   6.250   1.2208   0.01188   0.00524  -0.1066   0.2185   1.0000
   6.500   1.2387   0.01317   0.00604  -0.1055   0.1379   1.0000
   6.750   1.2611   0.01384   0.00657  -0.1048   0.1146   1.0000
   7.000   1.2844   0.01435   0.00705  -0.1042   0.1014   1.0000
   7.250   1.3076   0.01485   0.00752  -0.1036   0.0893   1.0000
   7.500   1.3305   0.01537   0.00799  -0.1030   0.0754   1.0000
   7.750   1.3508   0.01617   0.00861  -0.1021   0.0490   1.0000
   8.000   1.3694   0.01713   0.00943  -0.1009   0.0273   1.0000
   8.250   1.3893   0.01790   0.01018  -0.0999   0.0186   1.0000
   8.500   1.4101   0.01853   0.01084  -0.0989   0.0158   1.0000
   8.750   1.4294   0.01929   0.01163  -0.0978   0.0133   1.0000
   9.000   1.4492   0.01993   0.01234  -0.0967   0.0121   1.0000
   9.250   1.4683   0.02062   0.01309  -0.0956   0.0110   1.0000
   9.500   1.4858   0.02140   0.01395  -0.0943   0.0101   1.0000
   9.750   1.5007   0.02237   0.01499  -0.0926   0.0094   1.0000
  10.000   1.5147   0.02333   0.01604  -0.0909   0.0089   1.0000
  10.250   1.5273   0.02420   0.01700  -0.0889   0.0085   1.0000
  10.500   1.5379   0.02517   0.01806  -0.0867   0.0081   1.0000
  10.750   1.5476   0.02623   0.01921  -0.0846   0.0077   1.0000
  11.000   1.5569   0.02738   0.02043  -0.0826   0.0073   1.0000
  11.250   1.5651   0.02867   0.02180  -0.0808   0.0070   1.0000
  11.500   1.5708   0.03025   0.02349  -0.0790   0.0066   1.0000
  11.750   1.5717   0.03237   0.02571  -0.0770   0.0064   1.0000
  12.000   1.5772   0.03416   0.02761  -0.0756   0.0062   1.0000
  12.250   1.5819   0.03610   0.02968  -0.0743   0.0061   1.0000
  12.500   1.5851   0.03825   0.03195  -0.0731   0.0059   1.0000
  12.750   1.5874   0.04058   0.03440  -0.0720   0.0058   1.0000
  13.000   1.5883   0.04309   0.03702  -0.0710   0.0056   1.0000
  13.250   1.5883   0.04574   0.03980  -0.0700   0.0055   1.0000
  13.500   1.5873   0.04856   0.04274  -0.0692   0.0053   1.0000
  13.750   1.5850   0.05157   0.04587  -0.0685   0.0052   1.0000
  14.000   1.5820   0.05476   0.04918  -0.0680   0.0051   1.0000
  14.250   1.5779   0.05815   0.05269  -0.0677   0.0050   1.0000
  14.500   1.5730   0.06177   0.05643  -0.0675   0.0050   1.0000
  14.750   1.5676   0.06566   0.06047  -0.0677   0.0049   1.0000
  15.000   1.5620   0.06975   0.06469  -0.0682   0.0048   1.0000
  15.250   1.5554   0.07416   0.06922  -0.0689   0.0047   1.0000
  15.500   1.5482   0.07884   0.07402  -0.0700   0.0047   1.0000
  15.750   1.5404   0.08375   0.07906  -0.0712   0.0046   1.0000
  16.000   1.5311   0.08898   0.08441  -0.0726   0.0045   1.0000
  16.250   1.5205   0.09450   0.09006  -0.0743   0.0045   1.0000
  16.500   1.5090   0.10026   0.09595  -0.0762   0.0044   1.0000
  16.750   1.4962   0.10631   0.10212  -0.0782   0.0044   1.0000
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