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GOE 655 AIRFOIL (goe655-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 655 AIRFOIL (goe655-il)
Reynolds number: 200,000
Max Cl/Cd: 64.55 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe655-il-200000.txt
Download as CSV file: xf-goe655-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 655 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3437   0.09738   0.09410  -0.0415   1.0000   0.0769
  -9.250  -0.3817   0.09431   0.09115  -0.0424   1.0000   0.0773
  -9.000  -0.3899   0.09078   0.08769  -0.0397   1.0000   0.0779
  -8.750  -0.3794   0.08960   0.08653  -0.0354   1.0000   0.0788
  -8.250  -0.3417   0.08518   0.08212  -0.0373   0.9949   0.0837
  -8.000  -0.3669   0.06855   0.06538  -0.0670   0.9748   0.0905
  -7.750  -0.3302   0.06983   0.06675  -0.0618   0.9737   0.0921
  -7.500  -0.3760   0.04174   0.03721  -0.0837   0.9528   0.0654
  -7.250  -0.3579   0.03693   0.03208  -0.0852   0.9443   0.0634
  -7.000  -0.3286   0.03256   0.02715  -0.0879   0.9404   0.0631
  -6.750  -0.3091   0.02979   0.02396  -0.0875   0.9303   0.0631
  -6.500  -0.2742   0.02705   0.02078  -0.0895   0.9265   0.0633
  -6.250  -0.2332   0.02508   0.01841  -0.0923   0.9241   0.0648
  -6.000  -0.2076   0.02395   0.01697  -0.0916   0.9136   0.0661
  -5.750  -0.1669   0.02188   0.01463  -0.0939   0.9093   0.0672
  -5.500  -0.1372   0.02036   0.01305  -0.0940   0.8993   0.0688
  -5.250  -0.0995   0.01926   0.01190  -0.0956   0.8929   0.0716
  -5.000  -0.0719   0.01848   0.01103  -0.0952   0.8826   0.0741
  -4.750  -0.0372   0.01761   0.01003  -0.0960   0.8759   0.0764
  -4.500  -0.0120   0.01671   0.00910  -0.0951   0.8649   0.0788
  -4.250   0.0192   0.01591   0.00833  -0.0955   0.8571   0.0832
  -4.000   0.0448   0.01541   0.00777  -0.0947   0.8453   0.0878
  -3.750   0.0701   0.01472   0.00711  -0.0939   0.8341   0.0935
  -3.500   0.0990   0.01422   0.00655  -0.0937   0.8243   0.1020
  -3.250   0.1230   0.01371   0.00609  -0.0926   0.8120   0.1173
  -3.000   0.1468   0.01306   0.00568  -0.0917   0.8002   0.1617
  -2.750   0.1715   0.01249   0.00545  -0.0910   0.7889   0.2528
  -2.500   0.1977   0.01225   0.00528  -0.0904   0.7770   0.3067
  -2.250   0.2223   0.01209   0.00518  -0.0894   0.7636   0.3487
  -2.000   0.2472   0.01192   0.00508  -0.0886   0.7505   0.3900
  -1.500   0.2972   0.01160   0.00489  -0.0868   0.7251   0.4831
  -1.250   0.3195   0.01137   0.00484  -0.0854   0.7113   0.5424
  -1.000   0.3390   0.01102   0.00485  -0.0833   0.6975   0.6372
  -0.750   0.3602   0.01061   0.00493  -0.0809   0.6838   0.7905
  -0.500   0.4300   0.01055   0.00494  -0.0884   0.6657   0.9301
  -0.250   0.4896   0.01066   0.00486  -0.0944   0.6462   0.9750
   0.000   0.5503   0.01076   0.00470  -0.1011   0.6254   1.0000
   0.250   0.5689   0.01085   0.00464  -0.0992   0.6073   1.0000
   0.500   0.5879   0.01097   0.00460  -0.0974   0.5887   1.0000
   0.750   0.6073   0.01112   0.00459  -0.0957   0.5700   1.0000
   1.000   0.6270   0.01132   0.00461  -0.0940   0.5519   1.0000
   1.250   0.6471   0.01154   0.00466  -0.0924   0.5347   1.0000
   1.500   0.6674   0.01177   0.00473  -0.0909   0.5182   1.0000
   1.750   0.6878   0.01202   0.00482  -0.0893   0.5026   1.0000
   2.000   0.7087   0.01228   0.00493  -0.0879   0.4887   1.0000
   2.500   0.7520   0.01279   0.00521  -0.0854   0.4657   1.0000
   2.750   0.7744   0.01307   0.00538  -0.0843   0.4565   1.0000
   3.000   0.7966   0.01333   0.00555  -0.0832   0.4473   1.0000
   3.250   0.8193   0.01360   0.00574  -0.0821   0.4391   1.0000
   3.500   0.8418   0.01385   0.00593  -0.0811   0.4310   1.0000
   3.750   0.8649   0.01414   0.00614  -0.0801   0.4239   1.0000
   4.000   0.8877   0.01439   0.00636  -0.0791   0.4167   1.0000
   4.250   0.9118   0.01473   0.00658  -0.0785   0.4106   1.0000
   4.500   0.9343   0.01496   0.00685  -0.0774   0.4042   1.0000
   4.750   0.9578   0.01524   0.00708  -0.0766   0.3985   1.0000
   5.000   0.9821   0.01559   0.00736  -0.0760   0.3931   1.0000
   5.250   1.0045   0.01584   0.00766  -0.0750   0.3872   1.0000
   5.500   1.0278   0.01613   0.00790  -0.0742   0.3815   1.0000
   5.750   1.0515   0.01648   0.00822  -0.0735   0.3761   1.0000
   6.000   1.0735   0.01674   0.00854  -0.0724   0.3703   1.0000
   6.250   1.0967   0.01705   0.00882  -0.0717   0.3650   1.0000
   6.500   1.1201   0.01743   0.00918  -0.0709   0.3597   1.0000
   6.750   1.1411   0.01770   0.00953  -0.0698   0.3538   1.0000
   7.000   1.1638   0.01803   0.00983  -0.0689   0.3481   1.0000
   7.250   1.1852   0.01839   0.01022  -0.0679   0.3422   1.0000
   7.500   1.2048   0.01867   0.01056  -0.0665   0.3355   1.0000
   7.750   1.2277   0.01909   0.01089  -0.0657   0.3291   1.0000
   8.000   1.2437   0.01934   0.01128  -0.0637   0.3217   1.0000
   8.250   1.2636   0.01970   0.01159  -0.0625   0.3148   1.0000
   8.500   1.2793   0.02004   0.01204  -0.0604   0.3070   1.0000
   8.750   1.2964   0.02039   0.01237  -0.0587   0.2994   1.0000
   9.000   1.3103   0.02079   0.01286  -0.0564   0.2910   1.0000
   9.250   1.3247   0.02118   0.01322  -0.0543   0.2834   1.0000
   9.500   1.3352   0.02162   0.01375  -0.0514   0.2751   1.0000
   9.750   1.3482   0.02208   0.01417  -0.0491   0.2680   1.0000
  10.000   1.3591   0.02261   0.01478  -0.0466   0.2603   1.0000
  10.250   1.3706   0.02309   0.01526  -0.0442   0.2536   1.0000
  10.500   1.3818   0.02368   0.01590  -0.0419   0.2469   1.0000
  10.750   1.3920   0.02424   0.01650  -0.0396   0.2404   1.0000
  11.000   1.4033   0.02491   0.01715  -0.0376   0.2345   1.0000
  11.250   1.4135   0.02559   0.01793  -0.0355   0.2285   1.0000
  11.500   1.4246   0.02632   0.01865  -0.0336   0.2236   1.0000
  11.750   1.4360   0.02714   0.01954  -0.0319   0.2188   1.0000
  12.000   1.4456   0.02798   0.02047  -0.0301   0.2139   1.0000
  12.250   1.4559   0.02886   0.02134  -0.0284   0.2095   1.0000
  12.500   1.4653   0.02986   0.02241  -0.0268   0.2050   1.0000
  12.750   1.4731   0.03091   0.02358  -0.0252   0.2005   1.0000
  13.000   1.4820   0.03198   0.02467  -0.0237   0.1965   1.0000
  13.250   1.4915   0.03314   0.02583  -0.0224   0.1924   1.0000
  13.500   1.4961   0.03450   0.02735  -0.0209   0.1881   1.0000
  13.750   1.5028   0.03583   0.02876  -0.0196   0.1845   1.0000
  14.000   1.5126   0.03707   0.02992  -0.0186   0.1799   1.0000
  14.250   1.5129   0.03888   0.03196  -0.0173   0.1762   1.0000
  14.500   1.5148   0.04069   0.03390  -0.0163   0.1720   1.0000
  14.750   1.5177   0.04247   0.03567  -0.0154   0.1674   1.0000
  15.000   1.5184   0.04456   0.03788  -0.0146   0.1634   1.0000
  15.250   1.5140   0.04718   0.04069  -0.0141   0.1584   1.0000
  15.500   1.5114   0.04972   0.04324  -0.0137   0.1534   1.0000
  15.750   1.5058   0.05280   0.04650  -0.0136   0.1484   1.0000
  16.000   1.4965   0.05650   0.05035  -0.0141   0.1419   1.0000
  16.250   1.4876   0.06034   0.05429  -0.0146   0.1357   1.0000
  16.500   1.4755   0.06491   0.05902  -0.0158   0.1275   1.0000
  16.750   1.4631   0.06978   0.06403  -0.0172   0.1178   1.0000
  17.000   1.4478   0.07517   0.06952  -0.0188   0.1063   1.0000
  17.250   1.4281   0.08130   0.07568  -0.0208   0.0932   1.0000
  17.500   1.4000   0.08884   0.08319  -0.0235   0.0776   1.0000
  17.750   1.3743   0.09620   0.09055  -0.0262   0.0671   1.0000
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