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GOE 281 (DAIMLER XII) AIRFOIL (goe281-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 281 (DAIMLER XII) AIRFOIL (goe281-il)
Reynolds number: 100,000
Max Cl/Cd: 59.56 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe281-il-100000-n5.txt
Download as CSV file: xf-goe281-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 281 (DAIMLER XII) 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3225   0.09663   0.09201  -0.0278   1.0000   0.0339
  -7.500  -0.3303   0.09521   0.09071  -0.0282   1.0000   0.0346
  -7.250  -0.3332   0.09349   0.08906  -0.0310   1.0000   0.0350
  -7.000  -0.3322   0.09132   0.08695  -0.0340   1.0000   0.0353
  -6.750  -0.3284   0.08874   0.08438  -0.0366   1.0000   0.0354
  -6.500  -0.3294   0.08452   0.08025  -0.0347   1.0000   0.0359
  -6.250  -0.3310   0.08125   0.07704  -0.0308   1.0000   0.0367
  -6.000  -0.3184   0.07768   0.07348  -0.0317   0.9972   0.0380
  -5.750  -0.2907   0.07323   0.06896  -0.0376   0.9914   0.0402
  -5.500  -0.2513   0.06825   0.06383  -0.0478   0.9851   0.0446
  -5.250  -0.2146   0.06267   0.05810  -0.0568   0.9783   0.0483
  -5.000  -0.1899   0.05926   0.05466  -0.0593   0.9727   0.0528
  -4.750  -0.1391   0.05398   0.04896  -0.0705   0.9663   0.0602
  -4.500  -0.1167   0.05057   0.04561  -0.0718   0.9604   0.0638
  -4.250  -0.0762   0.04662   0.04134  -0.0780   0.9541   0.0753
  -4.000  -0.0371   0.04331   0.03771  -0.0830   0.9477   0.0883
  -3.750  -0.0065   0.04035   0.03471  -0.0852   0.9402   0.0954
  -3.500   0.0282   0.03743   0.03156  -0.0884   0.9325   0.1083
  -3.000   0.1139   0.02982   0.02257  -0.0929   0.9162   0.0572
  -2.750   0.1491   0.02733   0.01976  -0.0946   0.9085   0.0542
  -2.500   0.1808   0.02571   0.01776  -0.0952   0.8975   0.0555
  -2.250   0.2135   0.02410   0.01581  -0.0959   0.8872   0.0549
  -2.000   0.2468   0.02260   0.01396  -0.0965   0.8772   0.0532
  -1.750   0.2784   0.02137   0.01244  -0.0968   0.8661   0.0520
  -1.500   0.3087   0.02037   0.01118  -0.0968   0.8546   0.0513
  -1.250   0.3389   0.01949   0.01010  -0.0969   0.8438   0.0510
  -1.000   0.3690   0.01872   0.00919  -0.0969   0.8331   0.0513
  -0.750   0.3987   0.01812   0.00849  -0.0969   0.8224   0.0542
  -0.500   0.4268   0.01759   0.00787  -0.0967   0.8101   0.0556
  -0.250   0.4547   0.01707   0.00731  -0.0964   0.7979   0.0556
   0.000   0.4824   0.01664   0.00684  -0.0961   0.7857   0.0557
   0.250   0.5102   0.01630   0.00644  -0.0958   0.7735   0.0560
   0.500   0.5378   0.01605   0.00609  -0.0955   0.7614   0.0564
   0.750   0.5653   0.01588   0.00582  -0.0951   0.7489   0.0572
   1.000   0.5927   0.01578   0.00560  -0.0947   0.7350   0.0582
   1.250   0.6201   0.01570   0.00541  -0.0943   0.7199   0.0599
   1.500   0.6472   0.01563   0.00524  -0.0939   0.7032   0.0635
   1.750   0.6737   0.01562   0.00513  -0.0933   0.6837   0.0717
   2.000   0.6982   0.01367   0.00516  -0.0925   0.6653   1.0000
   2.250   0.7246   0.01385   0.00514  -0.0919   0.6481   1.0000
   2.500   0.7510   0.01405   0.00518  -0.0915   0.6326   1.0000
   2.750   0.7773   0.01427   0.00529  -0.0910   0.6169   1.0000
   3.000   0.8034   0.01449   0.00541  -0.0906   0.6009   1.0000
   3.250   0.8292   0.01472   0.00557  -0.0901   0.5838   1.0000
   3.500   0.8549   0.01496   0.00578  -0.0897   0.5658   1.0000
   3.750   0.8805   0.01520   0.00598  -0.0892   0.5470   1.0000
   4.000   0.9056   0.01545   0.00617  -0.0886   0.5265   1.0000
   4.250   0.9303   0.01572   0.00638  -0.0880   0.5032   1.0000
   4.500   0.9544   0.01604   0.00660  -0.0873   0.4794   1.0000
   4.750   0.9780   0.01642   0.00686  -0.0865   0.4557   1.0000
   5.000   1.0015   0.01686   0.00719  -0.0857   0.4338   1.0000
   5.250   1.0252   0.01730   0.00762  -0.0851   0.4150   1.0000
   5.500   1.0489   0.01776   0.00807  -0.0844   0.3976   1.0000
   5.750   1.0725   0.01822   0.00854  -0.0838   0.3804   1.0000
   6.000   1.0955   0.01867   0.00904  -0.0831   0.3592   1.0000
   6.250   1.1166   0.01919   0.00952  -0.0821   0.3246   1.0000
   6.500   1.1366   0.01980   0.01000  -0.0810   0.2888   1.0000
   6.750   1.1559   0.02054   0.01059  -0.0799   0.2562   1.0000
   7.000   1.1754   0.02130   0.01127  -0.0788   0.2333   1.0000
   7.250   1.1932   0.02222   0.01204  -0.0775   0.1986   1.0000
   7.500   1.2116   0.02311   0.01286  -0.0764   0.1642   1.0000
   7.750   1.2288   0.02411   0.01371  -0.0750   0.1326   1.0000
   8.000   1.2416   0.02557   0.01486  -0.0732   0.0839   1.0000
   8.250   1.2452   0.02794   0.01675  -0.0703   0.0289   1.0000
   8.500   1.2588   0.02921   0.01817  -0.0683   0.0260   1.0000
   8.750   1.2709   0.03057   0.01972  -0.0662   0.0241   1.0000
   9.000   1.2794   0.03218   0.02158  -0.0637   0.0222   1.0000
   9.250   1.2866   0.03367   0.02328  -0.0611   0.0209   1.0000
   9.500   1.2924   0.03515   0.02499  -0.0584   0.0200   1.0000
   9.750   1.2961   0.03685   0.02691  -0.0557   0.0195   1.0000
  10.000   1.2977   0.03876   0.02904  -0.0531   0.0191   1.0000
  10.250   1.2976   0.04090   0.03139  -0.0508   0.0187   1.0000
  10.500   1.2959   0.04328   0.03398  -0.0487   0.0184   1.0000
  10.750   1.2931   0.04592   0.03681  -0.0470   0.0181   1.0000
  11.000   1.2894   0.04881   0.03988  -0.0457   0.0178   1.0000
  11.250   1.2856   0.05189   0.04314  -0.0447   0.0175   1.0000
  11.500   1.2815   0.05516   0.04660  -0.0440   0.0170   1.0000
  11.750   1.2777   0.05854   0.05012  -0.0436   0.0165   1.0000
  12.000   1.2740   0.06200   0.05371  -0.0433   0.0160   1.0000
  12.250   1.2709   0.06547   0.05730  -0.0430   0.0156   1.0000
  12.500   1.2691   0.06882   0.06076  -0.0426   0.0151   1.0000
  12.750   1.2698   0.07188   0.06391  -0.0419   0.0149   1.0000
  13.000   1.2726   0.07477   0.06690  -0.0411   0.0146   1.0000
  13.250   1.2763   0.07766   0.06991  -0.0402   0.0144   1.0000
  13.500   1.2796   0.08075   0.07314  -0.0395   0.0143   1.0000
  13.750   1.2805   0.08425   0.07680  -0.0392   0.0142   1.0000
  14.000   1.2792   0.08813   0.08087  -0.0393   0.0141   1.0000
  14.250   1.2747   0.09246   0.08540  -0.0400   0.0141   1.0000
  14.500   1.2683   0.09715   0.09031  -0.0412   0.0140   1.0000
  14.750   1.2604   0.10221   0.09558  -0.0429   0.0140   1.0000
  15.000   1.2512   0.10765   0.10126  -0.0452   0.0140   1.0000
  15.250   1.2411   0.11345   0.10728  -0.0481   0.0141   1.0000
  15.500   1.2303   0.11964   0.11368  -0.0515   0.0141   1.0000
  15.750   1.2189   0.12626   0.12051  -0.0554   0.0142   1.0000
  16.000   1.2072   0.13332   0.12777  -0.0599   0.0143   1.0000
  16.250   1.1951   0.14088   0.13552  -0.0649   0.0144   1.0000
  16.500   1.1825   0.14904   0.14387  -0.0705   0.0145   1.0000
  16.750   1.1694   0.15790   0.15288  -0.0767   0.0147   1.0000
  17.000   1.1555   0.16772   0.16287  -0.0835   0.0149   1.0000
  17.250   1.1409   0.17870   0.17399  -0.0909   0.0152   1.0000
  17.500   1.1233   0.19220   0.18760  -0.0995   0.0157   1.0000
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