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GOE 481A AIRFOIL (goe481a-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 481A AIRFOIL (goe481a-il)
Reynolds number: 50,000
Max Cl/Cd: 27.88 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe481a-il-50000-n5.txt
Download as CSV file: xf-goe481a-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 481A AIRFOIL                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.2800   0.12096   0.11391  -0.0311   0.9838   0.1536
  -7.000  -0.2754   0.11797   0.11093  -0.0350   0.9758   0.1540
  -6.750  -0.2687   0.11476   0.10773  -0.0386   0.9681   0.1541
  -6.500  -0.2609   0.11147   0.10445  -0.0414   0.9596   0.1540
  -6.250  -0.2576   0.10348   0.09634  -0.0453   0.9508   0.1175
  -6.000  -0.2436   0.10013   0.09299  -0.0474   0.9430   0.1161
  -5.750  -0.2346   0.09658   0.08944  -0.0501   0.9334   0.1148
  -5.500  -0.2298   0.09287   0.08572  -0.0524   0.9222   0.1135
  -5.250  -0.2397   0.08543   0.07807  -0.0601   0.9083   0.1081
  -5.000  -0.2176   0.08169   0.07427  -0.0632   0.9013   0.1074
  -4.750  -0.2102   0.07846   0.07100  -0.0638   0.8888   0.1068
  -4.500  -0.1987   0.07473   0.06717  -0.0656   0.8779   0.1063
  -4.250  -0.1807   0.07033   0.06259  -0.0690   0.8688   0.1066
  -4.000  -0.1729   0.06638   0.05841  -0.0701   0.8560   0.1075
  -3.750  -0.1491   0.06167   0.05335  -0.0735   0.8493   0.1081
  -3.500  -0.1393   0.05913   0.05066  -0.0726   0.8360   0.1084
  -3.250  -0.1190   0.05650   0.04783  -0.0731   0.8267   0.1089
  -3.000  -0.0986   0.05419   0.04533  -0.0732   0.8167   0.1095
  -2.750  -0.0797   0.05248   0.04349  -0.0727   0.8063   0.1110
  -2.500  -0.0545   0.05043   0.04122  -0.0731   0.7978   0.1135
  -2.250  -0.0368   0.04846   0.03893  -0.0723   0.7869   0.1156
  -2.000  -0.0105   0.04586   0.03582  -0.0726   0.7794   0.1177
  -1.750   0.0090   0.04443   0.03415  -0.0715   0.7688   0.1191
  -1.500   0.0381   0.04314   0.03276  -0.0716   0.7611   0.1213
  -1.250   0.0603   0.04214   0.03156  -0.0707   0.7513   0.1246
  -1.000   0.0881   0.04053   0.02944  -0.0703   0.7433   0.1293
  -0.750   0.1256   0.03914   0.02804  -0.0714   0.7389   0.1329
  -0.500   0.1409   0.03870   0.02745  -0.0693   0.7258   0.1360
  -0.250   0.1790   0.03723   0.02565  -0.0702   0.7209   0.1428
   0.000   0.1969   0.03699   0.02540  -0.0686   0.7087   0.1477
   0.250   0.2357   0.03574   0.02385  -0.0697   0.7030   0.1557
   0.500   0.2599   0.03533   0.02344  -0.0689   0.6929   0.1630
   0.750   0.2948   0.03449   0.02247  -0.0696   0.6852   0.1731
   1.000   0.3444   0.03330   0.02114  -0.0725   0.6806   0.1880
   1.250   0.3633   0.03349   0.02129  -0.0711   0.6680   0.1987
   1.500   0.4121   0.03254   0.02028  -0.0741   0.6623   0.2169
   1.750   0.4359   0.03260   0.02035  -0.0735   0.6514   0.2295
   2.000   0.4778   0.03202   0.01972  -0.0754   0.6442   0.2466
   2.250   0.5122   0.03177   0.01941  -0.0762   0.6358   0.2621
   2.500   0.5406   0.03168   0.01938  -0.0762   0.6262   0.2758
   2.750   0.5905   0.03089   0.01859  -0.0794   0.6204   0.2979
   3.000   0.6010   0.03146   0.01928  -0.0768   0.6088   0.3124
   3.500   0.7313   0.02984   0.01925  -0.0907   0.5912   1.0000
   3.750   0.7631   0.03004   0.01919  -0.0910   0.5830   1.0000
   4.000   0.7868   0.03049   0.01947  -0.0901   0.5746   1.0000
   4.250   0.8042   0.03108   0.01995  -0.0883   0.5654   1.0000
   4.500   0.8501   0.03101   0.01964  -0.0909   0.5591   1.0000
   4.750   0.8451   0.03219   0.02085  -0.0857   0.5489   1.0000
   5.000   0.8776   0.03241   0.02092  -0.0862   0.5416   1.0000
   5.250   0.8931   0.03312   0.02158  -0.0842   0.5336   1.0000
   5.500   0.9048   0.03393   0.02237  -0.0817   0.5251   1.0000
   5.750   0.9461   0.03394   0.02221  -0.0835   0.5190   1.0000
   6.000   0.9369   0.03538   0.02373  -0.0780   0.5098   1.0000
   6.250   0.9614   0.03577   0.02405  -0.0773   0.5022   1.0000
   6.500   0.9802   0.03632   0.02454  -0.0758   0.4943   1.0000
   6.750   0.9808   0.03745   0.02569  -0.0718   0.4849   1.0000
   7.000   1.0211   0.03706   0.02513  -0.0730   0.4770   1.0000
   7.250   1.0028   0.03886   0.02705  -0.0667   0.4664   1.0000
   7.500   1.0451   0.03826   0.02629  -0.0679   0.4588   1.0000
   7.750   1.0223   0.04044   0.02861  -0.0615   0.4487   1.0000
   8.000   1.0504   0.04044   0.02852  -0.0611   0.4414   1.0000
   8.250   1.0465   0.04207   0.03022  -0.0573   0.4333   1.0000
   8.500   1.0506   0.04333   0.03152  -0.0545   0.4253   1.0000
   8.750   1.0930   0.04263   0.03070  -0.0555   0.4198   1.0000
   9.000   1.0526   0.04646   0.03475  -0.0488   0.4098   1.0000
   9.250   1.0802   0.04642   0.03466  -0.0483   0.4035   1.0000
   9.500   1.0671   0.04904   0.03737  -0.0447   0.3952   1.0000
   9.750   1.0660   0.05096   0.03936  -0.0422   0.3872   1.0000
  10.000   1.1122   0.04953   0.03783  -0.0428   0.3824   1.0000
  10.250   1.0518   0.05615   0.04469  -0.0375   0.3702   1.0000
  10.500   1.0909   0.05487   0.04334  -0.0372   0.3654   1.0000
  10.750   1.0364   0.06212   0.05079  -0.0339   0.3525   1.0000
  11.000   1.0700   0.06103   0.04966  -0.0331   0.3476   1.0000
  11.500   1.0446   0.06870   0.05749  -0.0305   0.3294   1.0000
  11.750   1.0901   0.06620   0.05493  -0.0295   0.3267   1.0000
  12.250   1.0333   0.07842   0.06735  -0.0284   0.3060   1.0000
  12.750   1.0040   0.08854   0.07759  -0.0286   0.2883   1.0000
  13.250   0.9611   0.10192   0.09110  -0.0308   0.2706   1.0000
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