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GOE 398 AIRFOIL (goe398-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 398 AIRFOIL (goe398-il)
Reynolds number: 200,000
Max Cl/Cd: 68.18 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe398-il-200000-n5.txt
Download as CSV file: xf-goe398-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 398 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.3094   0.10964   0.10588  -0.0463   1.0000   0.0281
 -11.250  -0.3164   0.10600   0.10229  -0.0464   1.0000   0.0285
 -10.750  -0.5187   0.04558   0.04137  -0.0988   0.9661   0.0302
 -10.500  -0.5097   0.04216   0.03777  -0.1019   0.9563   0.0305
 -10.250  -0.4979   0.03934   0.03474  -0.1038   0.9470   0.0311
 -10.000  -0.4851   0.03667   0.03181  -0.1051   0.9375   0.0318
  -9.750  -0.4697   0.03333   0.02804  -0.1069   0.9302   0.0328
  -9.500  -0.4605   0.03007   0.02419  -0.1066   0.9196   0.0339
  -9.250  -0.4374   0.02788   0.02163  -0.1075   0.9137   0.0347
  -9.000  -0.4134   0.02691   0.02059  -0.1075   0.9059   0.0353
  -8.750  -0.3862   0.02595   0.01951  -0.1081   0.8992   0.0363
  -8.500  -0.3595   0.02473   0.01805  -0.1086   0.8928   0.0375
  -8.250  -0.3374   0.02348   0.01649  -0.1080   0.8840   0.0386
  -8.000  -0.3095   0.02221   0.01491  -0.1084   0.8779   0.0395
  -7.750  -0.2865   0.02152   0.01420  -0.1077   0.8693   0.0403
  -7.500  -0.2591   0.02085   0.01345  -0.1078   0.8626   0.0414
  -7.250  -0.2338   0.02019   0.01266  -0.1074   0.8554   0.0426
  -7.000  -0.2092   0.01947   0.01176  -0.1068   0.8475   0.0438
  -6.750  -0.1815   0.01874   0.01083  -0.1067   0.8412   0.0448
  -6.500  -0.1592   0.01817   0.01024  -0.1057   0.8323   0.0459
  -6.250  -0.1323   0.01770   0.00971  -0.1054   0.8250   0.0473
  -6.000  -0.1087   0.01727   0.00921  -0.1045   0.8160   0.0488
  -5.750  -0.0828   0.01678   0.00859  -0.1039   0.8075   0.0504
  -5.500  -0.0593   0.01632   0.00806  -0.1030   0.7985   0.0518
  -5.250  -0.0344   0.01593   0.00763  -0.1023   0.7902   0.0534
  -5.000  -0.0102   0.01561   0.00726  -0.1014   0.7814   0.0556
  -4.750   0.0148   0.01530   0.00683  -0.1006   0.7726   0.0583
  -4.500   0.0388   0.01496   0.00650  -0.0997   0.7644   0.0611
  -4.250   0.0633   0.01468   0.00618  -0.0989   0.7567   0.0645
  -4.000   0.0887   0.01440   0.00584  -0.0982   0.7503   0.0687
  -3.750   0.1126   0.01417   0.00560  -0.0973   0.7423   0.0744
  -3.500   0.1379   0.01392   0.00532  -0.0966   0.7354   0.0818
  -3.250   0.1622   0.01370   0.00510  -0.0957   0.7280   0.0902
  -3.000   0.1871   0.01350   0.00489  -0.0950   0.7209   0.1008
  -2.750   0.2123   0.01329   0.00471  -0.0943   0.7142   0.1158
  -2.500   0.2362   0.01310   0.00460  -0.0934   0.7062   0.1367
  -2.250   0.2618   0.01295   0.00449  -0.0927   0.6992   0.1641
  -2.000   0.2861   0.01284   0.00443  -0.0919   0.6913   0.1922
  -1.750   0.3109   0.01269   0.00433  -0.0912   0.6840   0.2183
  -1.500   0.3352   0.01256   0.00424  -0.0903   0.6763   0.2446
  -1.250   0.3590   0.01239   0.00416  -0.0894   0.6680   0.2762
  -1.000   0.3822   0.01218   0.00412  -0.0884   0.6601   0.3311
  -0.750   0.4041   0.01195   0.00412  -0.0871   0.6515   0.4073
  -0.500   0.4259   0.01173   0.00410  -0.0857   0.6434   0.4883
  -0.250   0.4461   0.01148   0.00413  -0.0839   0.6341   0.5752
   0.000   0.4666   0.01110   0.00416  -0.0820   0.6255   0.7045
   0.500   0.6340   0.01104   0.00437  -0.1049   0.5984   0.9872
   0.750   0.6741   0.01118   0.00439  -0.1075   0.5856   1.0000
   1.000   0.6949   0.01130   0.00439  -0.1060   0.5732   1.0000
   1.250   0.7154   0.01143   0.00442  -0.1044   0.5595   1.0000
   1.500   0.7357   0.01157   0.00446  -0.1028   0.5443   1.0000
   1.750   0.7556   0.01173   0.00451  -0.1011   0.5285   1.0000
   2.000   0.7754   0.01191   0.00457  -0.0994   0.5131   1.0000
   2.250   0.7950   0.01211   0.00466  -0.0976   0.4982   1.0000
   2.500   0.8144   0.01233   0.00476  -0.0959   0.4848   1.0000
   2.750   0.8335   0.01257   0.00488  -0.0941   0.4723   1.0000
   3.000   0.8532   0.01280   0.00503  -0.0925   0.4607   1.0000
   3.250   0.8730   0.01304   0.00520  -0.0908   0.4504   1.0000
   3.500   0.8924   0.01331   0.00537  -0.0892   0.4410   1.0000
   3.750   0.9127   0.01355   0.00556  -0.0877   0.4323   1.0000
   4.000   0.9323   0.01382   0.00577  -0.0861   0.4242   1.0000
   4.250   0.9527   0.01407   0.00598  -0.0846   0.4167   1.0000
   4.500   0.9728   0.01432   0.00620  -0.0831   0.4094   1.0000
   4.750   0.9923   0.01461   0.00644  -0.0815   0.4026   1.0000
   5.000   1.0124   0.01485   0.00668  -0.0801   0.3951   1.0000
   5.250   1.0310   0.01516   0.00693  -0.0784   0.3878   1.0000
   5.500   1.0506   0.01541   0.00720  -0.0768   0.3805   1.0000
   5.750   1.0688   0.01569   0.00747  -0.0751   0.3729   1.0000
   6.000   1.0872   0.01599   0.00776  -0.0733   0.3663   1.0000
   6.250   1.1052   0.01627   0.00806  -0.0715   0.3589   1.0000
   6.500   1.1206   0.01660   0.00835  -0.0693   0.3522   1.0000
   6.750   1.1374   0.01687   0.00866  -0.0673   0.3449   1.0000
   7.000   1.1522   0.01720   0.00899  -0.0650   0.3377   1.0000
   7.250   1.1678   0.01753   0.00934  -0.0629   0.3303   1.0000
   7.500   1.1825   0.01789   0.00971  -0.0607   0.3222   1.0000
   7.750   1.1974   0.01828   0.01010  -0.0585   0.3146   1.0000
   8.000   1.2110   0.01871   0.01054  -0.0563   0.3054   1.0000
   8.250   1.2247   0.01917   0.01100  -0.0541   0.2960   1.0000
   8.500   1.2364   0.01972   0.01151  -0.0518   0.2870   1.0000
   8.750   1.2502   0.02024   0.01205  -0.0498   0.2773   1.0000
   9.000   1.2618   0.02087   0.01266  -0.0476   0.2691   1.0000
   9.250   1.2752   0.02147   0.01328  -0.0458   0.2609   1.0000
   9.500   1.2868   0.02217   0.01397  -0.0438   0.2544   1.0000
   9.750   1.3009   0.02280   0.01466  -0.0422   0.2477   1.0000
  10.000   1.3119   0.02360   0.01545  -0.0403   0.2412   1.0000
  10.250   1.3246   0.02435   0.01624  -0.0387   0.2346   1.0000
  10.500   1.3359   0.02519   0.01711  -0.0370   0.2281   1.0000
  10.750   1.3462   0.02612   0.01805  -0.0353   0.2222   1.0000
  11.000   1.3589   0.02696   0.01897  -0.0339   0.2168   1.0000
  11.250   1.3688   0.02798   0.02001  -0.0324   0.2114   1.0000
  11.500   1.3791   0.02900   0.02109  -0.0310   0.2060   1.0000
  11.750   1.3904   0.03001   0.02217  -0.0297   0.2007   1.0000
  12.000   1.3987   0.03122   0.02342  -0.0283   0.1957   1.0000
  12.250   1.4082   0.03239   0.02467  -0.0270   0.1903   1.0000
  12.500   1.4157   0.03374   0.02608  -0.0258   0.1832   1.0000
  12.750   1.4216   0.03525   0.02762  -0.0246   0.1769   1.0000
  13.000   1.4285   0.03673   0.02918  -0.0235   0.1693   1.0000
  13.250   1.4326   0.03848   0.03098  -0.0224   0.1629   1.0000
  13.500   1.4379   0.04021   0.03279  -0.0214   0.1546   1.0000
  13.750   1.4408   0.04220   0.03484  -0.0205   0.1458   1.0000
  14.000   1.4407   0.04454   0.03721  -0.0197   0.1348   1.0000
  14.250   1.4373   0.04730   0.03997  -0.0190   0.1192   1.0000
  14.500   1.4269   0.05089   0.04350  -0.0184   0.1020   1.0000
  14.750   1.4145   0.05486   0.04743  -0.0180   0.0897   1.0000
  15.250   1.3935   0.06287   0.05549  -0.0179   0.0770   1.0000
  15.500   1.3841   0.06695   0.05964  -0.0182   0.0738   1.0000
  15.750   1.3747   0.07118   0.06395  -0.0186   0.0711   1.0000
  16.000   1.3669   0.07531   0.06819  -0.0192   0.0690   1.0000
  16.250   1.3578   0.07970   0.07267  -0.0200   0.0671   1.0000
  16.500   1.3470   0.08442   0.07749  -0.0209   0.0655   1.0000
  16.750   1.3363   0.08919   0.08235  -0.0221   0.0642   1.0000
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