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GOE 277 (DAIMLER VIII) AIRFOIL (goe277-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 277 (DAIMLER VIII) AIRFOIL (goe277-il)
Reynolds number: 1,000,000
Max Cl/Cd: 122.61 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe277-il-1000000.txt
Download as CSV file: xf-goe277-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3559   0.08950   0.08796  -0.0257   1.0000   0.0148
  -8.000  -0.3587   0.08657   0.08505  -0.0262   1.0000   0.0148
  -7.750  -0.3668   0.08415   0.08268  -0.0253   0.9999   0.0148
  -7.500  -0.3448   0.07816   0.07667  -0.0341   0.9965   0.0149
  -7.250  -0.3272   0.07249   0.07100  -0.0404   0.9941   0.0152
  -7.000  -0.3042   0.06945   0.06794  -0.0447   0.9904   0.0156
  -6.750  -0.2776   0.06580   0.06427  -0.0507   0.9861   0.0161
  -6.500  -0.2502   0.06155   0.05997  -0.0574   0.9798   0.0171
  -6.250  -0.2098   0.05307   0.05133  -0.0704   0.9709   0.0187
  -6.000  -0.1843   0.04711   0.04523  -0.0755   0.9599   0.0188
  -5.750  -0.1662   0.04032   0.03826  -0.0798   0.9487   0.0194
  -5.500  -0.1455   0.03933   0.03722  -0.0800   0.9381   0.0198
  -5.000  -0.0897   0.03382   0.03135  -0.0822   0.9155   0.0236
  -4.750  -0.0637   0.02923   0.02642  -0.0833   0.9035   0.0237
  -4.500  -0.0433   0.02288   0.01963  -0.0848   0.8907   0.0247
  -4.250  -0.0185   0.02234   0.01902  -0.0848   0.8752   0.0254
  -4.000   0.0068   0.02157   0.01812  -0.0847   0.8565   0.0264
  -3.750   0.0362   0.02210   0.01844  -0.0838   0.8326   0.0300
  -2.500  -0.0132   0.02492   0.02093  -0.0603   0.7235   0.0282
  -2.250   0.1968   0.01169   0.00606  -0.0832   0.6993   0.0310
  -2.000   0.2248   0.01116   0.00540  -0.0831   0.6843   0.0308
  -1.750   0.2524   0.01015   0.00426  -0.0831   0.6689   0.0315
  -1.500   0.2801   0.00963   0.00364  -0.0830   0.6511   0.0320
  -1.250   0.3077   0.00930   0.00321  -0.0829   0.6304   0.0324
  -1.000   0.3354   0.00904   0.00286  -0.0828   0.6065   0.0328
  -0.750   0.3629   0.00886   0.00256  -0.0827   0.5820   0.0332
  -0.500   0.3905   0.00872   0.00231  -0.0826   0.5586   0.0336
  -0.250   0.4182   0.00861   0.00211  -0.0825   0.5380   0.0341
   0.000   0.4460   0.00855   0.00197  -0.0825   0.5190   0.0351
   0.250   0.4739   0.00850   0.00184  -0.0824   0.5012   0.0361
   0.500   0.5017   0.00847   0.00173  -0.0824   0.4832   0.0372
   0.750   0.5295   0.00848   0.00166  -0.0824   0.4646   0.0382
   1.000   0.5573   0.00852   0.00162  -0.0824   0.4445   0.0389
   1.250   0.5850   0.00854   0.00153  -0.0823   0.4244   0.0408
   1.500   0.6128   0.00859   0.00150  -0.0823   0.4056   0.0447
   1.750   0.6404   0.00866   0.00151  -0.0823   0.3887   0.0531
   2.000   0.6630   0.00672   0.00174  -0.0818   0.3747   1.0000
   2.250   0.6905   0.00689   0.00181  -0.0817   0.3614   1.0000
   2.500   0.7182   0.00704   0.00188  -0.0817   0.3513   1.0000
   2.750   0.7459   0.00717   0.00197  -0.0817   0.3440   1.0000
   3.000   0.7735   0.00733   0.00206  -0.0817   0.3368   1.0000
   3.250   0.8012   0.00745   0.00215  -0.0816   0.3308   1.0000
   3.500   0.8289   0.00759   0.00226  -0.0816   0.3252   1.0000
   3.750   0.8562   0.00776   0.00238  -0.0816   0.3190   1.0000
   4.000   0.8841   0.00786   0.00248  -0.0816   0.3151   1.0000
   4.250   0.9116   0.00799   0.00260  -0.0816   0.3108   1.0000
   4.500   0.9389   0.00816   0.00275  -0.0815   0.3060   1.0000
   4.750   0.9665   0.00828   0.00288  -0.0815   0.3021   1.0000
   5.000   0.9938   0.00842   0.00299  -0.0815   0.2944   1.0000
   5.250   1.0210   0.00858   0.00315  -0.0814   0.2881   1.0000
   5.500   1.0483   0.00871   0.00327  -0.0814   0.2809   1.0000
   5.750   1.0753   0.00888   0.00342  -0.0813   0.2732   1.0000
   6.000   1.1023   0.00904   0.00357  -0.0812   0.2643   1.0000
   6.250   1.1292   0.00921   0.00373  -0.0812   0.2544   1.0000
   6.500   1.1555   0.00945   0.00392  -0.0810   0.2381   1.0000
   6.750   1.1807   0.00981   0.00416  -0.0807   0.2120   1.0000
   7.000   1.2008   0.01082   0.00477  -0.0798   0.1453   1.0000
   7.250   1.2198   0.01195   0.00556  -0.0787   0.0901   1.0000
   7.500   1.2418   0.01270   0.00613  -0.0780   0.0610   1.0000
   7.750   1.2595   0.01394   0.00710  -0.0766   0.0183   1.0000
   8.000   1.2824   0.01452   0.00771  -0.0759   0.0152   1.0000
   8.250   1.3061   0.01495   0.00819  -0.0754   0.0144   1.0000
   8.500   1.3291   0.01545   0.00875  -0.0747   0.0134   1.0000
   8.750   1.3509   0.01606   0.00940  -0.0739   0.0124   1.0000
   9.000   1.3693   0.01700   0.01045  -0.0725   0.0113   1.0000
   9.250   1.3916   0.01747   0.01096  -0.0718   0.0109   1.0000
   9.500   1.4124   0.01806   0.01161  -0.0709   0.0104   1.0000
   9.750   1.4321   0.01872   0.01233  -0.0698   0.0099   1.0000
  10.000   1.4507   0.01943   0.01310  -0.0686   0.0095   1.0000
  10.250   1.4677   0.02023   0.01396  -0.0672   0.0091   1.0000
  10.500   1.4802   0.02132   0.01514  -0.0652   0.0087   1.0000
  10.750   1.4804   0.02314   0.01711  -0.0614   0.0083   1.0000
  11.000   1.4880   0.02411   0.01816  -0.0585   0.0082   1.0000
  11.250   1.4987   0.02496   0.01907  -0.0563   0.0080   1.0000
  11.500   1.5073   0.02598   0.02018  -0.0540   0.0078   1.0000
  11.750   1.5152   0.02712   0.02140  -0.0519   0.0076   1.0000
  12.000   1.5217   0.02843   0.02280  -0.0499   0.0073   1.0000
  12.250   1.5265   0.02998   0.02443  -0.0480   0.0071   1.0000
  12.500   1.5300   0.03175   0.02630  -0.0464   0.0070   1.0000
  12.750   1.5328   0.03375   0.02838  -0.0450   0.0068   1.0000
  13.000   1.5338   0.03608   0.03080  -0.0440   0.0067   1.0000
  13.250   1.5343   0.03866   0.03348  -0.0434   0.0065   1.0000
  13.500   1.5330   0.04165   0.03657  -0.0432   0.0064   1.0000
  13.750   1.5295   0.04504   0.04005  -0.0433   0.0063   1.0000
  14.000   1.5233   0.04891   0.04403  -0.0436   0.0062   1.0000
  14.250   1.5131   0.05336   0.04858  -0.0441   0.0061   1.0000
  14.500   1.5014   0.05808   0.05342  -0.0447   0.0060   1.0000
  14.750   1.4880   0.06300   0.05845  -0.0452   0.0059   1.0000
  15.000   1.4700   0.06830   0.06388  -0.0453   0.0058   1.0000
  15.250   1.4658   0.07245   0.06814  -0.0464   0.0058   1.0000
  15.500   1.4604   0.07675   0.07255  -0.0476   0.0058   1.0000
  15.750   1.4549   0.08120   0.07711  -0.0490   0.0057   1.0000
  16.000   1.4486   0.08582   0.08184  -0.0504   0.0057   1.0000
  16.250   1.4418   0.09056   0.08668  -0.0519   0.0057   1.0000
  16.500   1.4344   0.09541   0.09164  -0.0535   0.0056   1.0000
  16.750   1.4271   0.10037   0.09671  -0.0552   0.0056   1.0000
  17.000   1.4195   0.10544   0.10189  -0.0571   0.0055   1.0000
  17.250   1.4115   0.11062   0.10718  -0.0590   0.0055   1.0000
  17.500   1.4032   0.11592   0.11259  -0.0612   0.0055   1.0000
  17.750   1.3947   0.12136   0.11815  -0.0635   0.0054   1.0000
  18.000   1.3861   0.12694   0.12384  -0.0660   0.0054   1.0000
  18.250   1.3770   0.13267   0.12969  -0.0687   0.0053   1.0000
  18.500   1.3679   0.13851   0.13564  -0.0716   0.0053   1.0000
  18.750   1.3584   0.14456   0.14181  -0.0747   0.0053   1.0000
  19.000   1.3482   0.15092   0.14829  -0.0782   0.0053   1.0000
  19.250   1.3384   0.15745   0.15493  -0.0819   0.0052   1.0000
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