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GOE 277 (DAIMLER VIII) AIRFOIL (goe277-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 277 (DAIMLER VIII) AIRFOIL (goe277-il)
Reynolds number: 50,000
Max Cl/Cd: 33.99 at α=10°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe277-il-50000.txt
Download as CSV file: xf-goe277-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 277 (DAIMLER VIII) 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3785   0.10784   0.10131  -0.0230   1.0000   0.1535
  -7.750  -0.3508   0.10073   0.09415  -0.0194   1.0000   0.1634
  -7.500  -0.3642   0.10031   0.09389  -0.0220   1.0000   0.1679
  -7.250  -0.3499   0.09543   0.08902  -0.0192   1.0000   0.1769
  -7.000  -0.3610   0.09486   0.08859  -0.0233   1.0000   0.1833
  -6.750  -0.3481   0.09020   0.08397  -0.0195   1.0000   0.1936
  -6.500  -0.3535   0.08826   0.08216  -0.0221   1.0000   0.2006
  -6.250  -0.3499   0.08571   0.07966  -0.0215   1.0000   0.2127
  -6.000  -0.3433   0.08212   0.07615  -0.0190   1.0000   0.2221
  -5.750  -0.3426   0.07954   0.07365  -0.0193   1.0000   0.2334
  -5.500  -0.3409   0.07703   0.07122  -0.0194   1.0000   0.2472
  -5.250  -0.3377   0.07435   0.06860  -0.0183   1.0000   0.2625
  -5.000  -0.3339   0.07166   0.06599  -0.0160   1.0000   0.2804
  -4.750  -0.3323   0.06951   0.06387  -0.0161   1.0000   0.3057
  -4.500  -0.3304   0.06722   0.06166  -0.0138   1.0000   0.3351
  -4.250   0.0558   0.04054   0.03390  -0.0280   1.0000   1.0000
  -4.000   0.0659   0.03883   0.03226  -0.0286   1.0000   1.0000
  -3.750   0.0752   0.03723   0.03074  -0.0291   1.0000   1.0000
  -3.500   0.0751   0.03620   0.02982  -0.0273   1.0000   0.9966
  -3.250   0.0048   0.03878   0.03271  -0.0098   1.0000   0.9589
  -3.000  -0.0585   0.04054   0.03479   0.0046   1.0000   0.9231
  -2.750  -0.1155   0.04159   0.03612   0.0167   1.0000   0.8960
  -2.500  -0.1651   0.04200   0.03678   0.0266   1.0000   0.8714
  -2.250  -0.2375   0.04309   0.03818   0.0404   1.0000   0.8515
  -2.000  -0.2987   0.04331   0.03865   0.0508   1.0000   0.8271
  -1.750  -0.0383   0.03694   0.02881  -0.0521   1.0000   0.2161
  -1.500  -0.0071   0.03557   0.02693  -0.0538   1.0000   0.1970
  -1.250   0.0218   0.03460   0.02544  -0.0550   1.0000   0.1833
  -1.000   0.0688   0.03306   0.02353  -0.0594   0.9936   0.1720
  -0.750   0.1355   0.03178   0.02169  -0.0666   0.9769   0.1648
  -0.500   0.1987   0.03077   0.02030  -0.0731   0.9596   0.1664
  -0.250   0.2601   0.02981   0.01910  -0.0788   0.9423   0.1729
   0.000   0.3124   0.02906   0.01818  -0.0828   0.9219   0.1800
   0.250   0.3664   0.02819   0.01731  -0.0869   0.9020   0.1960
   0.500   0.4249   0.02687   0.01642  -0.0919   0.8842   0.2627
   0.750   0.4683   0.02463   0.01546  -0.0925   0.8647   1.0000
   1.000   0.5114   0.02452   0.01493  -0.0940   0.8421   1.0000
   1.250   0.5527   0.02432   0.01447  -0.0951   0.8207   1.0000
   1.500   0.5884   0.02420   0.01417  -0.0953   0.7982   1.0000
   1.750   0.6238   0.02404   0.01383  -0.0952   0.7776   1.0000
   2.000   0.6534   0.02418   0.01384  -0.0945   0.7553   1.0000
   2.250   0.6853   0.02421   0.01370  -0.0938   0.7362   1.0000
   2.500   0.7110   0.02470   0.01409  -0.0929   0.7154   1.0000
   2.750   0.7372   0.02523   0.01454  -0.0921   0.6968   1.0000
   3.000   0.7634   0.02580   0.01504  -0.0914   0.6799   1.0000
   3.250   0.7888   0.02647   0.01565  -0.0907   0.6643   1.0000
   3.500   0.8133   0.02727   0.01642  -0.0902   0.6499   1.0000
   3.750   0.8373   0.02818   0.01736  -0.0897   0.6369   1.0000
   4.000   0.8614   0.02909   0.01828  -0.0892   0.6250   1.0000
   4.250   0.8887   0.02972   0.01887  -0.0887   0.6151   1.0000
   4.500   0.9090   0.03109   0.02035  -0.0883   0.6038   1.0000
   4.750   0.9292   0.03251   0.02191  -0.0880   0.5937   1.0000
   5.000   0.9576   0.03312   0.02252  -0.0875   0.5859   1.0000
   5.250   0.9720   0.03519   0.02478  -0.0872   0.5757   1.0000
   5.500   0.9929   0.03665   0.02636  -0.0868   0.5677   1.0000
   5.750   1.0121   0.03827   0.02815  -0.0864   0.5591   1.0000
   6.000   1.0249   0.04064   0.03070  -0.0859   0.5507   1.0000
   6.250   1.0488   0.04179   0.03197  -0.0854   0.5430   1.0000
   6.500   1.0505   0.04533   0.03572  -0.0849   0.5337   1.0000
   6.750   1.0837   0.04547   0.03596  -0.0841   0.5262   1.0000
   7.000   1.0760   0.04990   0.04064  -0.0834   0.5156   1.0000
   7.250   1.0807   0.05277   0.04366  -0.0823   0.5042   1.0000
   7.500   1.1047   0.05297   0.04402  -0.0803   0.4895   1.0000
   7.750   1.1366   0.05200   0.04320  -0.0780   0.4729   1.0000
   8.000   1.1616   0.05204   0.04344  -0.0761   0.4578   1.0000
   8.250   1.1769   0.05339   0.04500  -0.0744   0.4441   1.0000
   8.500   1.1926   0.05471   0.04652  -0.0726   0.4300   1.0000
   8.750   1.2081   0.05600   0.04802  -0.0707   0.4153   1.0000
   9.000   1.2382   0.05543   0.04768  -0.0685   0.3976   1.0000
   9.250   1.2823   0.05292   0.04538  -0.0662   0.3755   1.0000
   9.500   1.3470   0.04455   0.03674  -0.0630   0.3329   1.0000
   9.750   1.3613   0.04228   0.03454  -0.0592   0.2981   1.0000
  10.000   1.3700   0.04031   0.03250  -0.0549   0.2609   1.0000
  10.250   1.3593   0.04078   0.03305  -0.0498   0.2210   1.0000
  10.500   1.3410   0.04246   0.03437  -0.0444   0.1817   1.0000
  10.750   1.3224   0.04544   0.03689  -0.0401   0.1546   1.0000
  11.000   1.3098   0.04899   0.04016  -0.0371   0.1349   1.0000
  11.250   1.3042   0.05246   0.04350  -0.0348   0.1200   1.0000
  11.500   1.3094   0.05562   0.04659  -0.0328   0.1083   1.0000
  11.750   1.3307   0.05860   0.04945  -0.0310   0.0981   1.0000
  12.000   1.3325   0.06211   0.05331  -0.0295   0.0934   1.0000
  12.250   1.3546   0.06551   0.05662  -0.0286   0.0864   1.0000
  12.500   1.3433   0.06946   0.06100  -0.0272   0.0851   1.0000
  12.750   1.3306   0.07389   0.06579  -0.0265   0.0841   1.0000
  13.000   1.3152   0.07884   0.07106  -0.0266   0.0835   1.0000
  13.250   1.2965   0.08440   0.07693  -0.0275   0.0834   1.0000
  13.500   1.2746   0.09070   0.08349  -0.0294   0.0837   1.0000
  13.750   1.2502   0.09781   0.09080  -0.0323   0.0844   1.0000
  14.000   1.2246   0.10571   0.09889  -0.0362   0.0852   1.0000
  14.250   1.1999   0.11424   0.10756  -0.0406   0.0861   1.0000
  14.500   1.1780   0.12301   0.11642  -0.0452   0.0870   1.0000
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