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GOE 376 AIRFOIL (goe376-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 376 AIRFOIL (goe376-il)
Reynolds number: 100,000
Max Cl/Cd: 58.66 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe376-il-100000-n5.txt
Download as CSV file: xf-goe376-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 376 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3032   0.10019   0.09538  -0.0239   1.0000   0.0302
  -7.750  -0.3071   0.09878   0.09407  -0.0242   1.0000   0.0305
  -7.500  -0.3105   0.09719   0.09258  -0.0247   1.0000   0.0306
  -7.250  -0.3094   0.09527   0.09074  -0.0267   1.0000   0.0308
  -7.000  -0.3062   0.09319   0.08872  -0.0291   1.0000   0.0309
  -6.750  -0.3010   0.09101   0.08657  -0.0314   1.0000   0.0310
  -6.500  -0.3024   0.08553   0.08119  -0.0244   1.0000   0.0320
  -6.250  -0.3013   0.08293   0.07865  -0.0229   1.0000   0.0329
  -6.000  -0.3006   0.08067   0.07646  -0.0222   1.0000   0.0338
  -5.750  -0.2998   0.07847   0.07430  -0.0219   1.0000   0.0348
  -5.500  -0.2742   0.07462   0.07041  -0.0278   0.9949   0.0367
  -5.250  -0.1610   0.05175   0.04768  -0.0461   0.9596   0.0421
  -5.000  -0.1342   0.04734   0.04321  -0.0504   0.9508   0.0462
  -4.750  -0.0804   0.04431   0.03971  -0.0641   0.9396   0.0512
  -4.500  -0.0689   0.03848   0.03402  -0.0637   0.9310   0.0528
  -4.250  -0.0431   0.03454   0.03005  -0.0661   0.9242   0.0566
  -4.000  -0.0042   0.03134   0.02650  -0.0726   0.9144   0.0652
  -3.750   0.0196   0.02757   0.02275  -0.0740   0.9079   0.0697
  -3.500   0.0580   0.02520   0.01995  -0.0786   0.8969   0.0790
  -3.250   0.0793   0.02190   0.01670  -0.0793   0.8877   0.0829
  -3.000   0.1141   0.01946   0.01395  -0.0823   0.8786   0.0946
  -2.750   0.1415   0.01755   0.01181  -0.0836   0.8665   0.1085
  -2.500   0.1671   0.01570   0.00985  -0.0842   0.8547   0.1193
  -2.250   0.1927   0.01366   0.00769  -0.0849   0.8434   0.1282
  -2.000   0.2199   0.01210   0.00594  -0.0856   0.8316   0.1437
  -1.500   0.2870   0.02540   0.01787  -0.0884   0.8375   0.0732
  -1.250   0.3199   0.02396   0.01592  -0.0881   0.8246   0.0625
  -1.000   0.3487   0.02241   0.01417  -0.0881   0.8110   0.0591
  -0.750   0.3786   0.02118   0.01262  -0.0879   0.7972   0.0557
  -0.500   0.4091   0.02026   0.01128  -0.0874   0.7832   0.0526
  -0.250   0.4384   0.01980   0.01056  -0.0871   0.7685   0.0513
   0.000   0.4667   0.01892   0.00950  -0.0868   0.7535   0.0508
   0.250   0.4947   0.01832   0.00872  -0.0864   0.7380   0.0511
   0.500   0.5217   0.01753   0.00785  -0.0860   0.7221   0.0533
   0.750   0.5484   0.01706   0.00729  -0.0854   0.7053   0.0542
   1.000   0.5748   0.01665   0.00678  -0.0847   0.6870   0.0539
   1.250   0.6004   0.01632   0.00634  -0.0839   0.6670   0.0538
   1.500   0.6251   0.01606   0.00600  -0.0829   0.6456   0.0540
   1.750   0.6510   0.01591   0.00570  -0.0822   0.6250   0.0544
   2.000   0.6768   0.01584   0.00550  -0.0815   0.6054   0.0552
   2.250   0.7025   0.01583   0.00536  -0.0809   0.5866   0.0562
   2.500   0.7281   0.01587   0.00526  -0.0802   0.5682   0.0578
   2.750   0.7535   0.01596   0.00524  -0.0795   0.5509   0.0613
   3.000   0.7789   0.01606   0.00527  -0.0789   0.5343   0.0696
   3.250   0.8041   0.01618   0.00535  -0.0783   0.5181   0.0879
   3.500   0.8507   0.01490   0.00561  -0.0827   0.4993   1.0000
   3.750   0.8746   0.01520   0.00577  -0.0818   0.4845   1.0000
   4.000   0.8983   0.01551   0.00596  -0.0809   0.4701   1.0000
   4.250   0.9219   0.01585   0.00619  -0.0800   0.4561   1.0000
   4.500   0.9452   0.01619   0.00647  -0.0791   0.4419   1.0000
   4.750   0.9683   0.01656   0.00676  -0.0782   0.4275   1.0000
   5.000   0.9912   0.01692   0.00709  -0.0772   0.4131   1.0000
   5.250   1.0139   0.01729   0.00746  -0.0763   0.3982   1.0000
   5.500   1.0365   0.01767   0.00783  -0.0753   0.3835   1.0000
   5.750   1.0588   0.01805   0.00822  -0.0743   0.3686   1.0000
   6.000   1.0810   0.01844   0.00864  -0.0733   0.3541   1.0000
   6.250   1.1030   0.01885   0.00911  -0.0723   0.3398   1.0000
   6.500   1.1249   0.01927   0.00959  -0.0713   0.3263   1.0000
   6.750   1.1465   0.01973   0.01010  -0.0702   0.3134   1.0000
   7.000   1.1678   0.02021   0.01064  -0.0691   0.3009   1.0000
   7.250   1.1880   0.02072   0.01120  -0.0679   0.2866   1.0000
   7.500   1.2061   0.02126   0.01170  -0.0664   0.2669   1.0000
   7.750   1.2232   0.02186   0.01226  -0.0648   0.2445   1.0000
   8.000   1.2411   0.02250   0.01291  -0.0634   0.2275   1.0000
   8.250   1.2587   0.02315   0.01365  -0.0619   0.2116   1.0000
   8.500   1.2765   0.02381   0.01439  -0.0605   0.1978   1.0000
   8.750   1.2932   0.02452   0.01517  -0.0589   0.1804   1.0000
   9.000   1.3073   0.02539   0.01600  -0.0571   0.1517   1.0000
   9.250   1.3197   0.02643   0.01698  -0.0550   0.1228   1.0000
   9.500   1.3168   0.02875   0.01867  -0.0515   0.0539   1.0000
   9.750   1.3159   0.03079   0.02054  -0.0480   0.0312   1.0000
  10.000   1.3175   0.03247   0.02229  -0.0447   0.0261   1.0000
  10.250   1.3194   0.03414   0.02406  -0.0418   0.0238   1.0000
  10.500   1.3189   0.03604   0.02611  -0.0389   0.0223   1.0000
  10.750   1.3187   0.03797   0.02823  -0.0364   0.0215   1.0000
  11.000   1.3173   0.04008   0.03056  -0.0343   0.0209   1.0000
  11.250   1.3140   0.04251   0.03321  -0.0325   0.0205   1.0000
  11.500   1.3090   0.04528   0.03620  -0.0312   0.0201   1.0000
  11.750   1.3021   0.04847   0.03960  -0.0304   0.0197   1.0000
  12.000   1.2945   0.05201   0.04334  -0.0302   0.0194   1.0000
  12.250   1.2850   0.05605   0.04758  -0.0305   0.0189   1.0000
  12.500   1.2746   0.06049   0.05220  -0.0312   0.0185   1.0000
  12.750   1.2645   0.06515   0.05704  -0.0324   0.0184   1.0000
  13.000   1.2532   0.07021   0.06230  -0.0339   0.0180   1.0000
  13.250   1.2430   0.07529   0.06754  -0.0356   0.0179   1.0000
  13.500   1.2308   0.08085   0.07324  -0.0376   0.0173   1.0000
  13.750   1.2221   0.08589   0.07843  -0.0392   0.0172   1.0000
  14.000   1.2125   0.09114   0.08380  -0.0411   0.0168   1.0000
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