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GOE 280 (DAIMLER XI) AIRFOIL (goe280-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 280 (DAIMLER XI) AIRFOIL (goe280-il)
Reynolds number: 200,000
Max Cl/Cd: 72.93 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe280-il-200000.txt
Download as CSV file: xf-goe280-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.3327   0.09016   0.08698  -0.0212   1.0000   0.0253
  -7.000  -0.3332   0.08774   0.08462  -0.0219   1.0000   0.0258
  -6.750  -0.3338   0.08545   0.08238  -0.0226   1.0000   0.0264
  -6.500  -0.3324   0.08329   0.08024  -0.0243   1.0000   0.0269
  -6.250  -0.3258   0.08112   0.07808  -0.0279   1.0000   0.0274
  -6.000  -0.3147   0.07864   0.07555  -0.0314   1.0000   0.0276
  -5.750  -0.3026   0.07589   0.07273  -0.0337   1.0000   0.0277
  -5.500  -0.2896   0.07302   0.06978  -0.0354   1.0000   0.0278
  -5.250  -0.2824   0.06823   0.06499  -0.0361   1.0000   0.0282
  -5.000  -0.2698   0.06280   0.05966  -0.0367   0.9973   0.0292
  -4.750  -0.2365   0.05841   0.05519  -0.0418   0.9937   0.0305
  -4.500  -0.1974   0.05406   0.05071  -0.0480   0.9890   0.0322
  -4.250  -0.1510   0.04973   0.04618  -0.0551   0.9851   0.0349
  -4.000  -0.0861   0.04800   0.04380  -0.0624   0.9805   0.0376
  -3.750  -0.0591   0.04093   0.03680  -0.0668   0.9758   0.0394
  -3.500  -0.0216   0.03777   0.03355  -0.0710   0.9720   0.0433
  -3.250   0.0374   0.03772   0.03274  -0.0752   0.9686   0.0497
  -3.000   0.0656   0.03142   0.02659  -0.0789   0.9624   0.0531
  -2.750   0.1138   0.02970   0.02435  -0.0827   0.9586   0.0642
  -2.500   0.1547   0.02661   0.02130  -0.0870   0.9561   0.0726
  -2.250   0.1919   0.02456   0.01903  -0.0893   0.9485   0.0845
  -0.750   0.3924   0.01658   0.00985  -0.0936   0.8866   0.1509
  -0.500   0.4237   0.01569   0.00855  -0.0913   0.8714   0.0892
  -0.250   0.4511   0.01526   0.00787  -0.0898   0.8541   0.0771
   0.000   0.4768   0.01408   0.00668  -0.0887   0.8318   0.0732
   0.250   0.5028   0.01343   0.00592  -0.0875   0.8078   0.0708
   0.500   0.5286   0.01294   0.00531  -0.0864   0.7811   0.0697
   0.750   0.5546   0.01265   0.00489  -0.0855   0.7534   0.0722
   1.000   0.5808   0.01247   0.00456  -0.0847   0.7253   0.0738
   1.250   0.6073   0.01236   0.00430  -0.0842   0.6976   0.0739
   1.500   0.6340   0.01232   0.00412  -0.0837   0.6696   0.0748
   1.750   0.6610   0.01233   0.00398  -0.0834   0.6430   0.0768
   2.000   0.6882   0.01233   0.00387  -0.0831   0.6182   0.0835
   2.250   0.7105   0.01093   0.00400  -0.0823   0.5963   0.7541
   2.500   0.7344   0.01066   0.00386  -0.0808   0.5739   1.0000
   2.750   0.7609   0.01094   0.00390  -0.0804   0.5529   1.0000
   3.000   0.7876   0.01121   0.00402  -0.0802   0.5323   1.0000
   3.250   0.8140   0.01150   0.00418  -0.0799   0.5127   1.0000
   3.500   0.8404   0.01180   0.00436  -0.0797   0.4937   1.0000
   3.750   0.8669   0.01207   0.00455  -0.0795   0.4735   1.0000
   4.000   0.8929   0.01237   0.00474  -0.0792   0.4521   1.0000
   4.250   0.9188   0.01264   0.00497  -0.0789   0.4272   1.0000
   4.500   0.9444   0.01295   0.00518  -0.0786   0.4003   1.0000
   4.750   0.9692   0.01332   0.00541  -0.0782   0.3679   1.0000
   5.000   0.9926   0.01383   0.00565  -0.0777   0.3200   1.0000
   5.250   1.0162   0.01439   0.00601  -0.0772   0.2812   1.0000
   5.500   1.0399   0.01495   0.00640  -0.0768   0.2516   1.0000
   5.750   1.0634   0.01554   0.00681  -0.0764   0.2222   1.0000
   6.000   1.0877   0.01603   0.00722  -0.0761   0.2023   1.0000
   6.250   1.1112   0.01659   0.00763  -0.0757   0.1808   1.0000
   6.500   1.1349   0.01711   0.00804  -0.0753   0.1592   1.0000
   6.750   1.1579   0.01772   0.00848  -0.0748   0.1391   1.0000
   7.000   1.1813   0.01825   0.00895  -0.0743   0.1261   1.0000
   7.250   1.2050   0.01875   0.00944  -0.0738   0.1159   1.0000
   7.500   1.2287   0.01922   0.00998  -0.0733   0.1070   1.0000
   7.750   1.2492   0.02007   0.01062  -0.0725   0.0653   1.0000
   8.000   1.2666   0.02128   0.01165  -0.0711   0.0426   1.0000
   8.250   1.2847   0.02237   0.01265  -0.0698   0.0242   1.0000
   8.500   1.3058   0.02307   0.01344  -0.0688   0.0220   1.0000
   8.750   1.3258   0.02387   0.01439  -0.0677   0.0214   1.0000
   9.000   1.3450   0.02472   0.01541  -0.0664   0.0210   1.0000
   9.250   1.3627   0.02568   0.01657  -0.0649   0.0207   1.0000
   9.500   1.3775   0.02689   0.01801  -0.0631   0.0199   1.0000
   9.750   1.3891   0.02829   0.01964  -0.0610   0.0192   1.0000
  10.000   1.3996   0.02958   0.02114  -0.0586   0.0190   1.0000
  10.250   1.4065   0.03093   0.02268  -0.0559   0.0190   1.0000
  10.500   1.4095   0.03239   0.02434  -0.0526   0.0191   1.0000
  10.750   1.4112   0.03405   0.02617  -0.0496   0.0192   1.0000
  11.000   1.4117   0.03595   0.02822  -0.0469   0.0194   1.0000
  11.250   1.4115   0.03805   0.03048  -0.0446   0.0196   1.0000
  11.500   1.4107   0.04039   0.03297  -0.0426   0.0198   1.0000
  11.750   1.4096   0.04293   0.03565  -0.0410   0.0201   1.0000
  12.000   1.4086   0.04565   0.03852  -0.0396   0.0205   1.0000
  12.250   1.4076   0.04853   0.04153  -0.0385   0.0209   1.0000
  12.500   1.4070   0.05150   0.04463  -0.0374   0.0213   1.0000
  12.750   1.4076   0.05444   0.04765  -0.0362   0.0217   1.0000
  13.000   1.4129   0.05693   0.05021  -0.0347   0.0221   1.0000
  13.250   1.4197   0.05917   0.05262  -0.0343   0.0227   1.0000
  13.500   1.4259   0.06170   0.05539  -0.0335   0.0237   1.0000
  13.750   1.4306   0.06465   0.05859  -0.0322   0.0247   1.0000
  14.000   1.4298   0.06834   0.06252  -0.0314   0.0253   1.0000
  14.250   1.4254   0.07255   0.06698  -0.0311   0.0259   1.0000
  14.500   1.4188   0.07716   0.07182  -0.0311   0.0264   1.0000
  14.750   1.4105   0.08219   0.07707  -0.0313   0.0272   1.0000
  15.000   1.4115   0.08653   0.08158  -0.0304   0.0283   1.0000
  15.250   1.3985   0.09157   0.08688  -0.0330   0.0289   1.0000
  15.500   1.3780   0.09846   0.09406  -0.0366   0.0293   1.0000
  15.750   1.3562   0.10615   0.10202  -0.0409   0.0296   1.0000
  16.000   1.3343   0.11436   0.11046  -0.0458   0.0299   1.0000
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