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GOE 280 (DAIMLER XI) AIRFOIL (goe280-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 280 (DAIMLER XI) AIRFOIL (goe280-il)
Reynolds number: 1,000,000
Max Cl/Cd: 98.74 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe280-il-1000000.txt
Download as CSV file: xf-goe280-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 280 (DAIMLER XI) 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.2548   0.08928   0.08785  -0.0254   1.0000   0.0091
  -8.500  -0.2521   0.08620   0.08479  -0.0259   1.0000   0.0093
  -8.250  -0.2523   0.08344   0.08205  -0.0257   1.0000   0.0095
  -8.000  -0.2464   0.07981   0.07843  -0.0274   0.9983   0.0098
  -7.750  -0.2370   0.07563   0.07426  -0.0304   0.9958   0.0103
  -7.500  -0.2279   0.07133   0.06996  -0.0338   0.9914   0.0113
  -7.250  -0.2202   0.06695   0.06558  -0.0387   0.9840   0.0115
  -7.000  -0.2129   0.06252   0.06115  -0.0436   0.9745   0.0116
  -6.750  -0.2020   0.05789   0.05649  -0.0486   0.9663   0.0116
  -6.500  -0.1908   0.05334   0.05191  -0.0528   0.9573   0.0116
  -6.250  -0.1779   0.04874   0.04726  -0.0566   0.9489   0.0116
  -6.000  -0.1633   0.04422   0.04266  -0.0598   0.9413   0.0116
  -5.750  -0.1464   0.03950   0.03788  -0.0631   0.9336   0.0117
  -4.250  -0.0189   0.03450   0.03198  -0.0779   0.9114   0.0156
  -4.000   0.0097   0.02804   0.02519  -0.0800   0.9036   0.0159
  -3.750   0.0322   0.02750   0.02462  -0.0804   0.8949   0.0166
  -3.500   0.0584   0.02636   0.02338  -0.0808   0.8851   0.0180
  -3.250   0.0924   0.02498   0.02174  -0.0802   0.8747   0.0205
  -3.000   0.1221   0.02241   0.01888  -0.0803   0.8614   0.0206
  -2.750   0.1507   0.01789   0.01394  -0.0814   0.8460   0.0218
  -2.500   0.1772   0.01729   0.01321  -0.0816   0.8210   0.0227
  -2.250   0.2047   0.01662   0.01234  -0.0815   0.7901   0.0247
  -2.000   0.2337   0.01734   0.01280  -0.0807   0.7586   0.0277
  -1.750  -0.90161118.054081118.05176   0.2231   0.7895   0.0206
  -0.250   0.4343   0.01099   0.00482  -0.0819   0.5738   0.0393
   0.000   0.4621   0.01058   0.00428  -0.0820   0.5402   0.0412
   0.500   0.5190   0.00989   0.00335  -0.0820   0.4993   0.0349
   0.750   0.5476   0.00953   0.00292  -0.0821   0.4845   0.0341
   1.000   0.5761   0.00937   0.00270  -0.0823   0.4698   0.0348
   1.250   0.6045   0.00928   0.00255  -0.0825   0.4550   0.0354
   1.500   0.6328   0.00925   0.00243  -0.0826   0.4361   0.0357
   1.750   0.6611   0.00925   0.00234  -0.0828   0.4140   0.0358
   2.000   0.6891   0.00931   0.00230  -0.0829   0.3921   0.0365
   2.250   0.7173   0.00936   0.00227  -0.0831   0.3718   0.0367
   2.500   0.7452   0.00946   0.00226  -0.0832   0.3501   0.0369
   2.750   0.7730   0.00959   0.00229  -0.0833   0.3264   0.0375
   3.000   0.8006   0.00974   0.00231  -0.0833   0.3019   0.0413
   3.250   0.8272   0.01008   0.00246  -0.0833   0.2613   0.0477
   3.500   0.8482   0.00859   0.00278  -0.0826   0.2283   1.0000
   3.750   0.8747   0.00900   0.00298  -0.0826   0.1954   1.0000
   4.000   0.9010   0.00942   0.00320  -0.0825   0.1618   1.0000
   4.250   0.9273   0.00983   0.00344  -0.0825   0.1364   1.0000
   4.500   0.9541   0.01013   0.00364  -0.0825   0.1222   1.0000
   4.750   0.9807   0.01045   0.00386  -0.0825   0.1087   1.0000
   5.000   1.0048   0.01117   0.00427  -0.0821   0.0617   1.0000
   5.250   1.0296   0.01179   0.00475  -0.0818   0.0341   1.0000
   5.500   1.0549   0.01230   0.00521  -0.0815   0.0147   1.0000
   5.750   1.0813   0.01259   0.00554  -0.0814   0.0130   1.0000
   6.000   1.1075   0.01291   0.00590  -0.0812   0.0118   1.0000
   6.250   1.1333   0.01326   0.00631  -0.0810   0.0111   1.0000
   6.500   1.1588   0.01366   0.00676  -0.0807   0.0104   1.0000
   6.750   1.1835   0.01415   0.00730  -0.0803   0.0097   1.0000
   7.000   1.2072   0.01478   0.00800  -0.0797   0.0091   1.0000
   7.250   1.2277   0.01587   0.00922  -0.0786   0.0084   1.0000
   7.500   1.2513   0.01642   0.00982  -0.0781   0.0080   1.0000
   7.750   1.2745   0.01698   0.01043  -0.0775   0.0076   1.0000
   8.000   1.2963   0.01770   0.01121  -0.0767   0.0074   1.0000
   8.250   1.3171   0.01849   0.01206  -0.0757   0.0071   1.0000
   8.500   1.3368   0.01934   0.01299  -0.0746   0.0068   1.0000
   8.750   1.3551   0.02027   0.01398  -0.0732   0.0065   1.0000
   9.000   1.3716   0.02131   0.01508  -0.0717   0.0062   1.0000
   9.250   1.3859   0.02247   0.01629  -0.0699   0.0060   1.0000
   9.500   1.3967   0.02386   0.01774  -0.0675   0.0058   1.0000
   9.750   1.4056   0.02533   0.01925  -0.0648   0.0058   1.0000
  10.000   1.4140   0.02676   0.02073  -0.0621   0.0058   1.0000
  10.250   1.4191   0.02842   0.02242  -0.0590   0.0057   1.0000
  10.500   1.4283   0.03074   0.02469  -0.0567   0.0055   1.0000
  10.750   1.4408   0.03211   0.02610  -0.0547   0.0056   1.0000
  12.750   1.5809   0.05590   0.05065  -0.0495   0.0054   1.0000
  13.000   1.5739   0.05834   0.05329  -0.0459   0.0054   1.0000
  13.250   1.5610   0.06053   0.05565  -0.0414   0.0053   1.0000
  13.500   1.5447   0.06290   0.05818  -0.0373   0.0053   1.0000
  13.750   1.5288   0.06559   0.06104  -0.0342   0.0053   1.0000
  14.000   1.5116   0.06863   0.06424  -0.0318   0.0053   1.0000
  14.250   1.4941   0.07201   0.06778  -0.0302   0.0053   1.0000
  14.500   1.4757   0.07579   0.07173  -0.0294   0.0053   1.0000
  14.750   1.4578   0.07995   0.07604  -0.0294   0.0053   1.0000
  15.000   1.4387   0.08453   0.08078  -0.0302   0.0053   1.0000
  15.250   1.4208   0.08943   0.08583  -0.0316   0.0053   1.0000
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