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GOE 464 AIRFOIL (goe464-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 464 AIRFOIL (goe464-il)
Reynolds number: 100,000
Max Cl/Cd: 79.66 at α=1.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe464-il-100000.txt
Download as CSV file: xf-goe464-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 464 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.1790   0.12182   0.11731  -0.0246   1.0000   0.0479
  -9.250  -0.1880   0.12173   0.11731  -0.0221   1.0000   0.0485
  -9.000  -0.1989   0.12220   0.11786  -0.0196   1.0000   0.0488
  -8.500  -0.2104   0.11940   0.11521  -0.0151   1.0000   0.0495
  -8.250  -0.2151   0.11796   0.11384  -0.0129   1.0000   0.0501
  -8.000  -0.2213   0.11697   0.11293  -0.0107   1.0000   0.0510
  -7.750  -0.2293   0.11626   0.11230  -0.0084   1.0000   0.0517
  -7.500  -0.2228   0.11443   0.11051  -0.0098   0.9970   0.0530
  -7.250  -0.1974   0.11164   0.10771  -0.0165   0.9883   0.0547
  -7.000  -0.1675   0.10946   0.10552  -0.0256   0.9776   0.0553
  -6.750  -0.1406   0.10372   0.09978  -0.0288   0.9716   0.0566
  -6.500  -0.1121   0.10001   0.09605  -0.0343   0.9618   0.0585
  -6.250  -0.0718   0.09630   0.09230  -0.0435   0.9543   0.0610
  -6.000  -0.0390   0.09395   0.08994  -0.0519   0.9414   0.0618
  -5.750  -0.0162   0.08911   0.08508  -0.0538   0.9333   0.0633
  -5.500   0.0198   0.08548   0.08142  -0.0604   0.9250   0.0662
  -5.250   0.0669   0.08425   0.08011  -0.0723   0.9128   0.0680
  -5.000   0.0980   0.07859   0.07445  -0.0758   0.9078   0.0688
  -4.750   0.1299   0.07483   0.07065  -0.0802   0.8996   0.0706
  -4.500   0.1716   0.07150   0.06726  -0.0872   0.8914   0.0732
  -4.250   0.2267   0.06989   0.06553  -0.0988   0.8811   0.0749
  -4.000   0.2501   0.06516   0.06079  -0.0999   0.8734   0.0760
  -3.750   0.2784   0.06240   0.05798  -0.1028   0.8623   0.0775
  -3.500   0.3212   0.05946   0.05494  -0.1088   0.8543   0.0799
  -3.250   0.3807   0.05939   0.05465  -0.1195   0.8409   0.0818
  -3.000   0.3962   0.05489   0.05015  -0.1185   0.8325   0.0825
  -2.750   0.4197   0.05230   0.04752  -0.1194   0.8207   0.0837
  -2.500   0.4473   0.05032   0.04547  -0.1213   0.8082   0.0855
  -2.250   0.5024   0.04911   0.04400  -0.1284   0.7995   0.0888
  -2.000   0.5352   0.04729   0.04205  -0.1311   0.7861   0.0895
  -1.750   0.5526   0.04454   0.03930  -0.1305   0.7739   0.0905
  -1.500   0.5843   0.04225   0.03688  -0.1322   0.7646   0.0925
  -1.250   0.6184   0.04094   0.03542  -0.1343   0.7514   0.0961
  -1.000   0.6221   0.02194   0.01654  -0.1259   0.7146   0.0986
  -0.750   0.6484   0.02036   0.01489  -0.1268   0.7024   0.1011
  -0.500   0.6957   0.02041   0.01457  -0.1305   0.6897   0.1061
  -0.250   0.7166   0.01766   0.01178  -0.1306   0.6813   0.1089
   0.000   0.7535   0.01705   0.01091  -0.1326   0.6689   0.1161
   0.250   0.8115   0.03178   0.02525  -0.1420   0.6788   0.1190
   0.500   0.8443   0.03053   0.02374  -0.1429   0.6671   0.1293
   0.750   0.8770   0.03003   0.02296  -0.1437   0.6535   0.1519
   1.000   0.8697   0.01324   0.00635  -0.1357   0.6232   0.1823
   1.250   0.8985   0.01267   0.00551  -0.1362   0.6131   0.2195
   1.500   0.9235   0.01244   0.00517  -0.1362   0.6010   0.2461
   1.750   0.9471   0.01189   0.00456  -0.1361   0.5906   0.2694
   2.000   1.0077   0.02607   0.01816  -0.1435   0.5955   0.2855
   2.250   1.0301   0.02559   0.01766  -0.1429   0.5838   0.3281
   2.500   1.0543   0.02523   0.01723  -0.1424   0.5737   0.3619
   2.750   1.0806   0.02510   0.01696  -0.1421   0.5639   0.3911
   3.000   1.1039   0.02475   0.01663  -0.1415   0.5536   0.4133
   3.250   1.1316   0.02457   0.01629  -0.1414   0.5454   0.4372
   3.500   1.1548   0.02461   0.01639  -0.1407   0.5354   0.4542
   3.750   1.1835   0.02447   0.01608  -0.1406   0.5277   0.4668
   4.000   1.2078   0.02478   0.01641  -0.1400   0.5174   0.4740
   4.250   1.2395   0.02467   0.01611  -0.1404   0.5092   0.4809
   4.500   1.2651   0.02488   0.01636  -0.1400   0.4986   0.4834
   4.750   1.2941   0.02505   0.01639  -0.1400   0.4901   0.4814
   5.000   1.3202   0.02539   0.01669  -0.1394   0.4809   0.4719
   5.250   1.3476   0.02579   0.01698  -0.1390   0.4729   0.4508
   5.500   1.3723   0.02634   0.01750  -0.1382   0.4642   0.4178
   5.750   1.3986   0.02691   0.01793  -0.1375   0.4566   0.3907
   6.000   1.4229   0.02731   0.01835  -0.1367   0.4477   0.3685
   6.250   1.4491   0.02786   0.01875  -0.1359   0.4403   0.3405
   6.500   1.4718   0.02832   0.01928  -0.1349   0.4312   0.3198
   6.750   1.4985   0.02872   0.01957  -0.1344   0.4237   0.2991
   7.000   1.5193   0.02928   0.02020  -0.1331   0.4146   0.2833
   7.250   1.5455   0.02970   0.02051  -0.1325   0.4068   0.2687
   7.500   1.5649   0.03028   0.02120  -0.1310   0.3974   0.2578
   7.750   1.5894   0.03066   0.02152  -0.1303   0.3891   0.2511
   8.000   1.6091   0.03113   0.02207  -0.1289   0.3797   0.2498
   8.250   1.6307   0.03172   0.02266  -0.1278   0.3712   0.2467
   8.500   1.6510   0.03218   0.02317  -0.1265   0.3620   0.2424
   8.750   1.6692   0.03285   0.02391  -0.1250   0.3527   0.2388
   9.000   1.6922   0.03320   0.02418  -0.1241   0.3436   0.2355
   9.250   1.7053   0.03409   0.02523  -0.1219   0.3338   0.2337
   9.500   1.7327   0.03442   0.02539  -0.1216   0.3255   0.2328
   9.750   1.7401   0.03554   0.02679  -0.1188   0.3160   0.2328
  10.000   1.7659   0.03598   0.02708  -0.1184   0.3079   0.2389
  10.250   1.7721   0.03710   0.02846  -0.1155   0.2989   0.2432
  10.500   1.7959   0.03765   0.02891  -0.1149   0.2911   0.2474
  10.750   1.8003   0.03884   0.03035  -0.1118   0.2829   0.2496
  11.000   1.8248   0.03934   0.03070  -0.1113   0.2754   0.2554
  11.250   1.8237   0.04072   0.03238  -0.1076   0.2680   0.2593
  11.500   1.8526   0.04102   0.03251  -0.1076   0.2606   0.2784
  11.750   1.8443   0.04254   0.03470  -0.1033   0.2547   0.6585
  12.000   1.8591   0.04322   0.03558  -0.1019   0.2481   1.0000
  12.250   1.8681   0.04441   0.03681  -0.0996   0.2423   1.0000
  12.500   1.8578   0.04613   0.03876  -0.0952   0.2372   1.0000
  12.750   1.8877   0.04609   0.03841  -0.0952   0.2293   1.0000
  13.000   1.8656   0.04851   0.04121  -0.0902   0.2255   1.0000
  13.250   1.8569   0.05047   0.04333  -0.0870   0.2205   1.0000
  13.500   1.8780   0.05069   0.04335  -0.0862   0.2133   1.0000
  13.750   1.8562   0.05389   0.04688  -0.0828   0.2098   1.0000
  14.000   1.8475   0.05634   0.04949  -0.0806   0.2050   1.0000
  14.250   1.8695   0.05654   0.04949  -0.0798   0.1983   1.0000
  14.500   1.8444   0.06071   0.05400  -0.0776   0.1953   1.0000
  14.750   1.8273   0.06450   0.05803  -0.0762   0.1916   1.0000
  15.000   1.8601   0.06344   0.05668  -0.0754   0.1840   1.0000
  15.250   1.8297   0.06878   0.06239  -0.0743   0.1818   1.0000
  15.500   1.8008   0.07459   0.06850  -0.0741   0.1792   1.0000
  15.750   1.7788   0.07995   0.07408  -0.0744   0.1760   1.0000
  16.000   1.8201   0.07724   0.07111  -0.0727   0.1688   1.0000
  16.250   1.7813   0.08498   0.07921  -0.0739   0.1671   1.0000
  16.500   1.7329   0.09510   0.08968  -0.0768   0.1659   1.0000
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