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GOE 380 AIRFOIL (goe380-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 380 AIRFOIL (goe380-il)
Reynolds number: 200,000
Max Cl/Cd: 75.58 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe380-il-200000.txt
Download as CSV file: xf-goe380-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 380 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -6.750  -0.3092   0.08868   0.08570  -0.0214   1.0000   0.0226
  -6.500  -0.3107   0.08609   0.08316  -0.0194   1.0000   0.0230
  -6.250  -0.3138   0.08399   0.08108  -0.0178   1.0000   0.0233
  -6.000  -0.3175   0.08204   0.07918  -0.0162   1.0000   0.0237
  -5.750  -0.3205   0.08017   0.07736  -0.0150   1.0000   0.0241
  -5.500  -0.2950   0.07627   0.07344  -0.0205   0.9961   0.0249
  -5.250  -0.2606   0.07186   0.06897  -0.0278   0.9904   0.0265
  -5.000  -0.2217   0.06744   0.06448  -0.0359   0.9848   0.0282
  -4.750  -0.1640   0.06422   0.06107  -0.0482   0.9774   0.0310
  -4.500  -0.1131   0.06091   0.05754  -0.0568   0.9717   0.0314
  -4.250  -0.0939   0.05416   0.05084  -0.0596   0.9657   0.0326
  -4.000  -0.0649   0.05034   0.04698  -0.0627   0.9593   0.0345
  -3.750  -0.0193   0.04654   0.04304  -0.0689   0.9555   0.0387
  -3.500   0.0348   0.04373   0.03982  -0.0751   0.9457   0.0435
  -3.250   0.0682   0.03901   0.03516  -0.0790   0.9417   0.0463
  -3.000   0.1021   0.03624   0.03224  -0.0811   0.9310   0.0501
  -2.750   0.1532   0.03610   0.03149  -0.0834   0.9209   0.0555
  -2.500   0.1786   0.03060   0.02604  -0.0855   0.9126   0.0577
  -2.250   0.2071   0.02824   0.02357  -0.0861   0.9005   0.0607
  -2.000   0.2458   0.02843   0.02316  -0.0858   0.8870   0.0686
  -1.750   0.2699   0.02434   0.01901  -0.0860   0.8728   0.0705
  -1.500   0.2961   0.02238   0.01693  -0.0857   0.8563   0.0745
  -1.250   0.3278   0.01945   0.01338  -0.0841   0.8397   0.0530
  -0.750   0.3847   0.01470   0.00753  -0.0815   0.8041   0.0434
  -0.500   0.4107   0.01382   0.00648  -0.0806   0.7832   0.0487
  -0.250   0.4369   0.01310   0.00551  -0.0796   0.7620   0.0575
   0.000   0.4625   0.01278   0.00507  -0.0786   0.7401   0.0745
   0.250   0.4877   0.01264   0.00475  -0.0778   0.7192   0.1018
   0.500   0.5123   0.01238   0.00438  -0.0771   0.6992   0.1221
   0.750   0.5370   0.01214   0.00404  -0.0762   0.6802   0.1328
   1.000   0.5610   0.01185   0.00371  -0.0753   0.6626   0.1411
   1.250   0.5853   0.01173   0.00351  -0.0744   0.6455   0.1500
   1.500   0.6098   0.01168   0.00339  -0.0736   0.6291   0.1636
   1.750   0.6342   0.01162   0.00336  -0.0728   0.6137   0.2019
   2.000   0.7045   0.01023   0.00336  -0.0821   0.5937   1.0000
   2.250   0.7284   0.01047   0.00343  -0.0812   0.5783   1.0000
   2.500   0.7521   0.01072   0.00350  -0.0803   0.5627   1.0000
   2.750   0.7756   0.01095   0.00361  -0.0793   0.5461   1.0000
   3.000   0.7988   0.01119   0.00374  -0.0783   0.5290   1.0000
   3.250   0.8220   0.01142   0.00387  -0.0773   0.5127   1.0000
   3.500   0.8454   0.01167   0.00406  -0.0764   0.4977   1.0000
   3.750   0.8690   0.01191   0.00424  -0.0756   0.4838   1.0000
   4.000   0.8925   0.01215   0.00442  -0.0747   0.4702   1.0000
   4.250   0.9159   0.01239   0.00462  -0.0738   0.4569   1.0000
   4.500   0.9394   0.01263   0.00482  -0.0730   0.4444   1.0000
   4.750   0.9628   0.01289   0.00508  -0.0721   0.4327   1.0000
   5.000   0.9862   0.01316   0.00531  -0.0713   0.4215   1.0000
   5.250   1.0095   0.01340   0.00557  -0.0705   0.4096   1.0000
   5.500   1.0326   0.01367   0.00586  -0.0696   0.3980   1.0000
   5.750   1.0558   0.01397   0.00617  -0.0688   0.3871   1.0000
   6.000   1.0787   0.01431   0.00654  -0.0679   0.3767   1.0000
   6.250   1.1014   0.01467   0.00688  -0.0670   0.3658   1.0000
   6.500   1.1239   0.01500   0.00728  -0.0661   0.3539   1.0000
   6.750   1.1457   0.01536   0.00768  -0.0651   0.3408   1.0000
   7.000   1.1654   0.01569   0.00802  -0.0637   0.3220   1.0000
   7.250   1.1854   0.01597   0.00838  -0.0624   0.3028   1.0000
   7.500   1.2042   0.01631   0.00870  -0.0610   0.2816   1.0000
   7.750   1.2238   0.01659   0.00905  -0.0597   0.2562   1.0000
   8.000   1.2411   0.01707   0.00943  -0.0581   0.2149   1.0000
   8.250   1.2479   0.01861   0.01037  -0.0551   0.1346   1.0000
   8.500   1.2434   0.02128   0.01229  -0.0508   0.0372   1.0000
   8.750   1.2525   0.02272   0.01386  -0.0478   0.0300   1.0000
   9.000   1.2638   0.02386   0.01522  -0.0452   0.0278   1.0000
   9.250   1.2716   0.02510   0.01666  -0.0423   0.0253   1.0000
   9.500   1.2727   0.02651   0.01822  -0.0385   0.0232   1.0000
   9.750   1.2712   0.02808   0.01994  -0.0347   0.0223   1.0000
  10.000   1.2669   0.02994   0.02191  -0.0310   0.0217   1.0000
  10.250   1.2581   0.03236   0.02444  -0.0273   0.0210   1.0000
  10.500   1.2539   0.03478   0.02694  -0.0246   0.0206   1.0000
  10.750   1.2538   0.03734   0.02956  -0.0222   0.0204   1.0000
  11.000   1.2619   0.03955   0.03183  -0.0204   0.0201   1.0000
  11.250   1.2761   0.04171   0.03410  -0.0189   0.0200   1.0000
  11.500   1.2878   0.04380   0.03635  -0.0175   0.0197   1.0000
  11.750   1.2928   0.04576   0.03849  -0.0161   0.0190   1.0000
  12.000   1.3010   0.04813   0.04105  -0.0149   0.0187   1.0000
  12.250   1.3083   0.05090   0.04403  -0.0136   0.0184   1.0000
  12.500   1.3145   0.05434   0.04772  -0.0123   0.0187   1.0000
  12.750   1.3174   0.05831   0.05195  -0.0113   0.0192   1.0000
  13.000   1.3420   0.06223   0.05604  -0.0104   0.0210   1.0000
  13.250   1.3311   0.06429   0.05837  -0.0092   0.0219   1.0000
  13.500   1.3100   0.06854   0.06310  -0.0090   0.0238   1.0000
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