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GOE 596 AIRFOIL (goe596-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 596 AIRFOIL (goe596-il)
Reynolds number: 200,000
Max Cl/Cd: 75.62 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe596-il-200000-n5.txt
Download as CSV file: xf-goe596-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 596 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3566   0.09058   0.08702  -0.0405   1.0000   0.0365
  -8.500  -0.3673   0.08774   0.08426  -0.0409   1.0000   0.0366
  -8.250  -0.3796   0.08533   0.08193  -0.0399   1.0000   0.0366
  -8.000  -0.3745   0.08257   0.07921  -0.0366   0.9996   0.0373
  -7.750  -0.3546   0.07975   0.07638  -0.0382   0.9946   0.0383
  -7.500  -0.3353   0.07545   0.07207  -0.0439   0.9861   0.0390
  -7.250  -0.3160   0.06721   0.06372  -0.0566   0.9746   0.0356
  -7.000  -0.2950   0.06033   0.05671  -0.0657   0.9642   0.0359
  -6.750  -0.2735   0.05507   0.05132  -0.0712   0.9557   0.0356
  -6.500  -0.2501   0.05004   0.04613  -0.0762   0.9479   0.0350
  -6.250  -0.2290   0.04492   0.04078  -0.0800   0.9374   0.0346
  -6.000  -0.2051   0.03942   0.03493  -0.0837   0.9286   0.0348
  -5.750  -0.1827   0.03429   0.02928  -0.0857   0.9186   0.0356
  -5.500  -0.1601   0.03089   0.02550  -0.0864   0.9090   0.0355
  -5.250  -0.1347   0.02785   0.02203  -0.0871   0.9004   0.0357
  -5.000  -0.1114   0.02550   0.01928  -0.0869   0.8895   0.0359
  -4.750  -0.0855   0.02384   0.01716  -0.0867   0.8793   0.0367
  -4.500  -0.0603   0.02190   0.01498  -0.0867   0.8694   0.0374
  -4.250  -0.0353   0.02057   0.01341  -0.0863   0.8581   0.0378
  -4.000  -0.0093   0.01940   0.01201  -0.0860   0.8471   0.0380
  -3.750   0.0173   0.01840   0.01078  -0.0856   0.8355   0.0384
  -3.500   0.0436   0.01754   0.00974  -0.0851   0.8228   0.0388
  -3.250   0.0696   0.01680   0.00883  -0.0846   0.8095   0.0394
  -3.000   0.0958   0.01612   0.00801  -0.0841   0.7960   0.0399
  -2.750   0.1220   0.01561   0.00738  -0.0836   0.7814   0.0410
  -2.500   0.1482   0.01514   0.00678  -0.0830   0.7660   0.0424
  -2.250   0.1742   0.01464   0.00616  -0.0824   0.7498   0.0431
  -2.000   0.2000   0.01418   0.00559  -0.0818   0.7332   0.0437
  -1.750   0.2256   0.01379   0.00510  -0.0811   0.7159   0.0443
  -1.500   0.2510   0.01348   0.00467  -0.0804   0.6974   0.0450
  -1.250   0.2758   0.01314   0.00423  -0.0796   0.6788   0.0459
  -1.000   0.3004   0.01285   0.00387  -0.0789   0.6617   0.0473
  -0.750   0.3257   0.01269   0.00363  -0.0782   0.6477   0.0494
  -0.500   0.3514   0.01258   0.00345  -0.0777   0.6360   0.0524
  -0.250   0.3774   0.01249   0.00328  -0.0772   0.6256   0.0550
   0.000   0.4032   0.01238   0.00310  -0.0767   0.6163   0.0586
   0.250   0.4293   0.01229   0.00299  -0.0762   0.6072   0.0652
   0.500   0.4551   0.01216   0.00291  -0.0757   0.5992   0.0907
   0.750   0.4747   0.01111   0.00299  -0.0747   0.5912   0.4509
   1.250   0.5697   0.01011   0.00310  -0.0824   0.5744   1.0000
   1.500   0.5944   0.01025   0.00314  -0.0817   0.5673   1.0000
   1.750   0.6190   0.01038   0.00321  -0.0810   0.5594   1.0000
   2.000   0.6437   0.01054   0.00328  -0.0802   0.5524   1.0000
   2.250   0.6686   0.01067   0.00337  -0.0796   0.5451   1.0000
   2.500   0.6934   0.01084   0.00346  -0.0789   0.5384   1.0000
   2.750   0.7183   0.01097   0.00359  -0.0782   0.5305   1.0000
   3.000   0.7429   0.01114   0.00370  -0.0775   0.5226   1.0000
   3.250   0.7677   0.01128   0.00384  -0.0769   0.5137   1.0000
   3.500   0.7922   0.01145   0.00397  -0.0761   0.5050   1.0000
   3.750   0.8167   0.01160   0.00412  -0.0754   0.4946   1.0000
   4.000   0.8411   0.01176   0.00427  -0.0747   0.4845   1.0000
   4.250   0.8652   0.01195   0.00443  -0.0739   0.4742   1.0000
   4.500   0.8895   0.01211   0.00460  -0.0732   0.4625   1.0000
   4.750   0.9133   0.01229   0.00478  -0.0724   0.4491   1.0000
   5.000   0.9366   0.01249   0.00496  -0.0715   0.4336   1.0000
   5.250   0.9591   0.01272   0.00514  -0.0705   0.4150   1.0000
   5.500   0.9815   0.01298   0.00535  -0.0694   0.3953   1.0000
   5.750   1.0034   0.01328   0.00559  -0.0684   0.3752   1.0000
   6.000   1.0249   0.01362   0.00587  -0.0673   0.3566   1.0000
   6.250   1.0467   0.01396   0.00619  -0.0662   0.3409   1.0000
   6.500   1.0681   0.01434   0.00653  -0.0651   0.3248   1.0000
   6.750   1.0884   0.01477   0.00692  -0.0639   0.3051   1.0000
   7.000   1.1087   0.01520   0.00732  -0.0627   0.2838   1.0000
   7.250   1.1280   0.01570   0.00775  -0.0614   0.2601   1.0000
   7.500   1.1449   0.01634   0.00825  -0.0597   0.2236   1.0000
   7.750   1.1582   0.01723   0.00892  -0.0576   0.1820   1.0000
   8.000   1.1697   0.01826   0.00973  -0.0553   0.1447   1.0000
   8.250   1.1750   0.01969   0.01077  -0.0522   0.0832   1.0000
   8.500   1.1839   0.02080   0.01174  -0.0496   0.0649   1.0000
   8.750   1.1940   0.02167   0.01261  -0.0469   0.0583   1.0000
   9.000   1.2053   0.02242   0.01344  -0.0445   0.0547   1.0000
   9.250   1.2146   0.02331   0.01439  -0.0420   0.0516   1.0000
   9.500   1.2209   0.02439   0.01552  -0.0392   0.0488   1.0000
   9.750   1.2311   0.02527   0.01651  -0.0370   0.0470   1.0000
  10.000   1.2398   0.02628   0.01762  -0.0349   0.0452   1.0000
  10.250   1.2471   0.02742   0.01885  -0.0327   0.0433   1.0000
  10.500   1.2523   0.02876   0.02028  -0.0306   0.0416   1.0000
  10.750   1.2537   0.03045   0.02203  -0.0285   0.0401   1.0000
  11.000   1.2566   0.03214   0.02381  -0.0267   0.0390   1.0000
  11.250   1.2638   0.03359   0.02538  -0.0253   0.0375   1.0000
  11.500   1.2687   0.03530   0.02719  -0.0240   0.0362   1.0000
  11.750   1.2729   0.03714   0.02912  -0.0229   0.0349   1.0000
  12.000   1.2763   0.03914   0.03120  -0.0220   0.0337   1.0000
  12.250   1.2774   0.04145   0.03358  -0.0211   0.0326   1.0000
  12.500   1.2768   0.04401   0.03618  -0.0203   0.0316   1.0000
  12.750   1.2822   0.04606   0.03839  -0.0198   0.0305   1.0000
  13.000   1.2860   0.04833   0.04078  -0.0194   0.0294   1.0000
  13.250   1.2892   0.05072   0.04328  -0.0191   0.0284   1.0000
  13.500   1.2919   0.05321   0.04585  -0.0190   0.0273   1.0000
  13.750   1.2937   0.05584   0.04855  -0.0190   0.0266   1.0000
  14.000   1.2943   0.05867   0.05142  -0.0191   0.0257   1.0000
  14.250   1.2963   0.06138   0.05426  -0.0190   0.0250   1.0000
  14.500   1.2987   0.06416   0.05722  -0.0192   0.0240   1.0000
  14.750   1.3004   0.06705   0.06024  -0.0195   0.0232   1.0000
  15.000   1.3016   0.07007   0.06338  -0.0199   0.0224   1.0000
  15.250   1.3021   0.07324   0.06665  -0.0205   0.0218   1.0000
  15.500   1.3020   0.07655   0.07004  -0.0213   0.0212   1.0000
  15.750   1.3012   0.08003   0.07360  -0.0223   0.0207   1.0000
  16.000   1.3003   0.08356   0.07722  -0.0231   0.0202   1.0000
  16.250   1.2984   0.08739   0.08127  -0.0242   0.0196   1.0000
  16.500   1.2953   0.09154   0.08561  -0.0256   0.0188   1.0000
  16.750   1.2925   0.09566   0.08989  -0.0269   0.0184   1.0000
  17.000   1.2887   0.10006   0.09443  -0.0287   0.0180   1.0000
  17.250   1.2845   0.10459   0.09911  -0.0306   0.0176   1.0000
  17.500   1.2800   0.10926   0.10391  -0.0327   0.0173   1.0000
  17.750   1.2753   0.11406   0.10882  -0.0350   0.0170   1.0000
  18.000   1.2707   0.11890   0.11377  -0.0374   0.0167   1.0000
  18.250   1.2663   0.12376   0.11873  -0.0399   0.0165   1.0000
  18.500   1.2614   0.12874   0.12381  -0.0425   0.0163   1.0000
  18.750   1.2519   0.13487   0.13010  -0.0459   0.0160   1.0000
  19.000   1.2389   0.14203   0.13748  -0.0500   0.0159   1.0000
  19.250   1.2237   0.14994   0.14561  -0.0549   0.0157   1.0000
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