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GOE 277 (DAIMLER VIII) AIRFOIL (goe277-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 277 (DAIMLER VIII) AIRFOIL (goe277-il)
Reynolds number: 500,000
Max Cl/Cd: 98.73 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe277-il-500000-n5.txt
Download as CSV file: xf-goe277-il-500000-n5.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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3531   0.09123   0.08904  -0.0248   1.0000   0.0092
  -8.250  -0.3531   0.08769   0.08553  -0.0260   1.0000   0.0094
  -8.000  -0.3590   0.08460   0.08249  -0.0260   1.0000   0.0096
  -7.750  -0.3534   0.07924   0.07715  -0.0315   0.9950   0.0099
  -7.500  -0.3351   0.07188   0.06978  -0.0420   0.9873   0.0104
  -7.250  -0.3115   0.06878   0.06665  -0.0474   0.9806   0.0108
  -7.000  -0.2862   0.06527   0.06310  -0.0532   0.9735   0.0113
  -6.750  -0.2604   0.05997   0.05774  -0.0610   0.9644   0.0121
  -6.500  -0.2325   0.04624   0.04374  -0.0765   0.9526   0.0137
  -6.250  -0.2073   0.04427   0.04168  -0.0786   0.9421   0.0141
  -6.000  -0.1823   0.04246   0.03978  -0.0803   0.9311   0.0147
  -5.750  -0.1534   0.02807   0.02461  -0.0879   0.9210   0.0182
  -5.500  -0.1288   0.02732   0.02375  -0.0881   0.9080   0.0186
  -5.250  -0.1039   0.02684   0.02317  -0.0880   0.8929   0.0191
  -5.000  -0.0790   0.02596   0.02215  -0.0880   0.8751   0.0199
  -4.750  -0.0535   0.02338   0.01922  -0.0882   0.8535   0.0211
  -4.500  -0.0273   0.01990   0.01518  -0.0881   0.8290   0.0233
  -4.250  -0.0012   0.01863   0.01351  -0.0877   0.7990   0.0241
  -4.000   0.0239   0.01628   0.01066  -0.0877   0.7720   0.0251
  -3.750   0.0501   0.01576   0.00994  -0.0875   0.7490   0.0259
  -3.250   0.1040   0.01461   0.00838  -0.0873   0.7149   0.0272
  -3.000   0.1314   0.01394   0.00751  -0.0872   0.6993   0.0277
  -2.750   0.1589   0.01333   0.00671  -0.0871   0.6835   0.0281
  -2.500   0.1865   0.01277   0.00597  -0.0869   0.6675   0.0285
  -2.250   0.2141   0.01238   0.00544  -0.0868   0.6513   0.0293
  -2.000   0.2417   0.01196   0.00489  -0.0867   0.6335   0.0299
  -1.750   0.2691   0.01155   0.00433  -0.0866   0.6137   0.0302
  -1.500   0.2964   0.01123   0.00387  -0.0864   0.5916   0.0307
  -1.250   0.3235   0.01100   0.00349  -0.0862   0.5681   0.0312
  -1.000   0.3508   0.01083   0.00319  -0.0861   0.5464   0.0318
  -0.750   0.3781   0.01070   0.00296  -0.0860   0.5271   0.0323
  -0.500   0.4055   0.01060   0.00276  -0.0859   0.5105   0.0327
  -0.250   0.4330   0.01051   0.00259  -0.0858   0.4949   0.0330
   0.000   0.4606   0.01045   0.00245  -0.0857   0.4794   0.0332
   0.250   0.4881   0.01035   0.00229  -0.0857   0.4639   0.0339
   0.750   0.5432   0.01025   0.00202  -0.0856   0.4305   0.0361
   1.000   0.5707   0.01028   0.00196  -0.0855   0.4134   0.0371
   1.250   0.5981   0.01033   0.00194  -0.0855   0.3981   0.0386
   1.500   0.6256   0.01040   0.00195  -0.0854   0.3853   0.0411
   2.000   0.6803   0.00974   0.00217  -0.0859   0.3649   0.4505
   2.500   0.7303   0.00877   0.00236  -0.0846   0.3500   1.0000
   2.750   0.7575   0.00895   0.00247  -0.0845   0.3429   1.0000
   3.000   0.7848   0.00910   0.00257  -0.0845   0.3352   1.0000
   3.250   0.8119   0.00930   0.00270  -0.0843   0.3278   1.0000
   3.500   0.8392   0.00944   0.00282  -0.0843   0.3219   1.0000
   3.750   0.8662   0.00962   0.00296  -0.0842   0.3163   1.0000
   4.000   0.8933   0.00979   0.00312  -0.0841   0.3119   1.0000
   4.250   0.9206   0.00994   0.00327  -0.0840   0.3076   1.0000
   4.500   0.9476   0.01010   0.00343  -0.0839   0.3035   1.0000
   5.000   1.0013   0.01045   0.00380  -0.0837   0.2945   1.0000
   5.250   1.0282   0.01062   0.00398  -0.0836   0.2902   1.0000
   5.500   1.0546   0.01084   0.00419  -0.0834   0.2847   1.0000
   5.750   1.0813   0.01101   0.00438  -0.0833   0.2758   1.0000
   6.000   1.1076   0.01123   0.00459  -0.0831   0.2658   1.0000
   6.250   1.1334   0.01148   0.00480  -0.0829   0.2488   1.0000
   6.500   1.1587   0.01179   0.00505  -0.0827   0.2290   1.0000
   6.750   1.1819   0.01235   0.00541  -0.0821   0.1888   1.0000
   7.000   1.1997   0.01357   0.00620  -0.0810   0.1202   1.0000
   7.250   1.2203   0.01443   0.00689  -0.0801   0.0890   1.0000
   7.500   1.2426   0.01505   0.00745  -0.0794   0.0717   1.0000
   7.750   1.2580   0.01645   0.00852  -0.0779   0.0206   1.0000
   8.000   1.2795   0.01710   0.00918  -0.0770   0.0153   1.0000
   8.250   1.3019   0.01761   0.00977  -0.0763   0.0135   1.0000
   8.500   1.3232   0.01820   0.01042  -0.0754   0.0119   1.0000
   8.750   1.3431   0.01891   0.01123  -0.0743   0.0107   1.0000
   9.000   1.3627   0.01961   0.01202  -0.0732   0.0099   1.0000
   9.250   1.3823   0.02026   0.01275  -0.0722   0.0093   1.0000
   9.500   1.4009   0.02096   0.01354  -0.0710   0.0087   1.0000
   9.750   1.4183   0.02171   0.01435  -0.0696   0.0081   1.0000
  10.000   1.4333   0.02260   0.01530  -0.0680   0.0075   1.0000
  10.250   1.4429   0.02382   0.01665  -0.0656   0.0071   1.0000
  10.500   1.4536   0.02470   0.01762  -0.0633   0.0069   1.0000
  10.750   1.4622   0.02571   0.01874  -0.0607   0.0067   1.0000
  11.000   1.4690   0.02689   0.02003  -0.0582   0.0064   1.0000
  11.250   1.4745   0.02823   0.02148  -0.0558   0.0062   1.0000
  11.500   1.4789   0.02974   0.02309  -0.0536   0.0060   1.0000
  11.750   1.4820   0.03146   0.02492  -0.0516   0.0059   1.0000
  12.000   1.4848   0.03334   0.02690  -0.0500   0.0057   1.0000
  12.250   1.4868   0.03544   0.02911  -0.0487   0.0055   1.0000
  12.500   1.4880   0.03779   0.03156  -0.0478   0.0054   1.0000
  12.750   1.4875   0.04053   0.03443  -0.0472   0.0052   1.0000
  13.000   1.4839   0.04383   0.03785  -0.0470   0.0051   1.0000
  13.250   1.4764   0.04782   0.04196  -0.0473   0.0050   1.0000
  13.500   1.4679   0.05209   0.04636  -0.0478   0.0049   1.0000
  13.750   1.4640   0.05591   0.05032  -0.0484   0.0048   1.0000
  14.000   1.4588   0.06003   0.05457  -0.0492   0.0047   1.0000
  14.250   1.4516   0.06446   0.05913  -0.0502   0.0047   1.0000
  14.500   1.4431   0.06917   0.06397  -0.0513   0.0046   1.0000
  14.750   1.4347   0.07394   0.06887  -0.0525   0.0045   1.0000
  15.000   1.4255   0.07885   0.07390  -0.0538   0.0045   1.0000
  15.250   1.4168   0.08380   0.07897  -0.0552   0.0044   1.0000
  15.500   1.4083   0.08878   0.08406  -0.0566   0.0044   1.0000
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