Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

GOE 677 (= M 6) AIRFOIL (goe677-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 677 (= M 6) AIRFOIL (goe677-il)
Reynolds number: 500,000
Max Cl/Cd: 73.28 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe677-il-500000-n5.txt
Download as CSV file: xf-goe677-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 677 (= M 6) 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
  ------ -------- --------- --------- -------- -------- --------
 -15.250  -1.1777   0.04837   0.04534  -0.0465   1.0000   0.0166
 -15.000  -1.2014   0.04323   0.03995  -0.0471   1.0000   0.0167
 -14.750  -1.2107   0.04020   0.03676  -0.0460   1.0000   0.0170
 -14.500  -1.2081   0.03850   0.03498  -0.0446   1.0000   0.0173
 -14.250  -1.2020   0.03718   0.03359  -0.0431   1.0000   0.0177
 -14.000  -1.1944   0.03602   0.03235  -0.0414   1.0000   0.0182
 -13.750  -1.1878   0.03479   0.03101  -0.0394   1.0000   0.0186
 -13.500  -1.1815   0.03354   0.02963  -0.0372   1.0000   0.0191
 -13.250  -1.1741   0.03224   0.02816  -0.0350   1.0000   0.0197
 -13.000  -1.1640   0.03086   0.02660  -0.0331   1.0000   0.0203
 -12.750  -1.1518   0.02955   0.02509  -0.0315   1.0000   0.0208
 -12.500  -1.1376   0.02842   0.02379  -0.0300   1.0000   0.0212
 -12.250  -1.1199   0.02776   0.02311  -0.0288   1.0000   0.0218
 -12.000  -1.0997   0.02732   0.02264  -0.0279   1.0000   0.0223
 -11.750  -1.0794   0.02685   0.02212  -0.0271   1.0000   0.0228
 -11.500  -1.0593   0.02628   0.02146  -0.0261   1.0000   0.0234
 -11.250  -1.0396   0.02559   0.02067  -0.0251   1.0000   0.0240
 -11.000  -1.0197   0.02484   0.01980  -0.0242   1.0000   0.0246
 -10.750  -0.9996   0.02407   0.01888  -0.0232   1.0000   0.0253
 -10.500  -0.9789   0.02333   0.01799  -0.0222   1.0000   0.0258
 -10.250  -0.9573   0.02272   0.01723  -0.0214   1.0000   0.0262
 -10.000  -0.9386   0.02167   0.01611  -0.0202   1.0000   0.0269
  -9.750  -0.9167   0.02116   0.01556  -0.0194   1.0000   0.0275
  -9.500  -0.8940   0.02076   0.01513  -0.0187   1.0000   0.0280
  -9.250  -0.8713   0.02035   0.01467  -0.0179   1.0000   0.0286
  -9.000  -0.8410   0.01979   0.01403  -0.0188   0.9846   0.0293
  -8.750  -0.8093   0.01919   0.01332  -0.0200   0.9609   0.0301
  -8.500  -0.7785   0.01856   0.01255  -0.0208   0.9324   0.0308
  -8.250  -0.7537   0.01800   0.01181  -0.0203   0.9040   0.0313
  -8.000  -0.7308   0.01750   0.01114  -0.0192   0.8779   0.0317
  -7.750  -0.7073   0.01712   0.01057  -0.0183   0.8517   0.0320
  -7.500  -0.6844   0.01650   0.00978  -0.0174   0.8249   0.0326
  -7.250  -0.6612   0.01592   0.00906  -0.0166   0.7993   0.0333
  -7.000  -0.6369   0.01549   0.00851  -0.0159   0.7773   0.0338
  -6.750  -0.6119   0.01514   0.00804  -0.0154   0.7592   0.0344
  -6.500  -0.5866   0.01482   0.00760  -0.0149   0.7431   0.0349
  -6.250  -0.5609   0.01450   0.00718  -0.0145   0.7290   0.0356
  -6.000  -0.5351   0.01418   0.00677  -0.0141   0.7173   0.0363
  -5.750  -0.5091   0.01388   0.00637  -0.0138   0.7077   0.0370
  -5.500  -0.4828   0.01360   0.00601  -0.0135   0.6990   0.0379
  -5.250  -0.4564   0.01335   0.00568  -0.0132   0.6914   0.0387
  -5.000  -0.4298   0.01309   0.00534  -0.0130   0.6845   0.0392
  -4.750  -0.4038   0.01274   0.00494  -0.0126   0.6784   0.0402
  -4.500  -0.3775   0.01243   0.00460  -0.0123   0.6729   0.0415
  -4.250  -0.3506   0.01219   0.00434  -0.0121   0.6676   0.0428
  -4.000  -0.3237   0.01200   0.00411  -0.0119   0.6628   0.0442
  -3.750  -0.2965   0.01181   0.00388  -0.0118   0.6577   0.0458
  -3.500  -0.2693   0.01163   0.00367  -0.0116   0.6520   0.0474
  -3.250  -0.2422   0.01145   0.00345  -0.0114   0.6470   0.0494
  -3.000  -0.2151   0.01126   0.00326  -0.0113   0.6427   0.0525
  -2.750  -0.1875   0.01111   0.00312  -0.0112   0.6387   0.0558
  -2.500  -0.1598   0.01099   0.00298  -0.0112   0.6345   0.0586
  -2.250  -0.1326   0.01083   0.00281  -0.0110   0.6304   0.0626
  -2.000  -0.1050   0.01069   0.00268  -0.0110   0.6263   0.0670
  -1.750  -0.0771   0.01059   0.00256  -0.0109   0.6221   0.0708
  -1.500  -0.0495   0.01045   0.00243  -0.0109   0.6180   0.0764
  -1.250  -0.0220   0.01034   0.00233  -0.0108   0.6141   0.0833
  -1.000   0.0056   0.01020   0.00224  -0.0108   0.6100   0.0961
  -0.750   0.0329   0.01001   0.00218  -0.0107   0.6051   0.1272
  -0.500   0.0601   0.00985   0.00210  -0.0106   0.6000   0.1556
  -0.250   0.0867   0.00961   0.00202  -0.0104   0.5954   0.2022
   0.000   0.1117   0.00915   0.00196  -0.0101   0.5904   0.3177
   0.250   0.1308   0.00819   0.00181  -0.0087   0.5851   0.5513
   0.500   0.1436   0.00719   0.00191  -0.0051   0.5800   0.8455
   0.750   0.1710   0.00722   0.00202  -0.0046   0.5730   0.8860
   1.000   0.1983   0.00731   0.00210  -0.0042   0.5643   0.9088
   1.250   0.2255   0.00740   0.00217  -0.0038   0.5523   0.9255
   1.500   0.2541   0.00752   0.00226  -0.0036   0.5385   0.9378
   1.750   0.2823   0.00764   0.00234  -0.0035   0.5246   0.9471
   2.000   0.3130   0.00778   0.00240  -0.0039   0.5072   0.9528
   2.250   0.3398   0.00794   0.00246  -0.0036   0.4855   0.9596
   2.500   0.3757   0.00819   0.00259  -0.0053   0.4618   0.9635
   2.750   0.4088   0.00843   0.00271  -0.0065   0.4430   0.9674
   3.000   0.4350   0.00862   0.00281  -0.0062   0.4276   0.9720
   3.250   0.4683   0.00881   0.00292  -0.0075   0.4121   0.9730
   3.500   0.5033   0.00897   0.00303  -0.0092   0.4000   0.9741
   3.750   0.5368   0.00910   0.00313  -0.0106   0.3916   0.9754
   4.000   0.5675   0.00923   0.00323  -0.0114   0.3814   0.9765
   4.250   0.5977   0.00933   0.00333  -0.0120   0.3724   0.9776
   4.500   0.6270   0.00946   0.00343  -0.0125   0.3637   0.9790
   4.750   0.6558   0.00958   0.00354  -0.0129   0.3528   0.9805
   5.000   0.6834   0.00973   0.00366  -0.0130   0.3400   0.9825
   5.250   0.7119   0.00990   0.00380  -0.0133   0.3234   0.9840
   5.500   0.7421   0.01015   0.00396  -0.0141   0.2999   0.9848
   5.750   0.7709   0.01052   0.00418  -0.0148   0.2645   0.9858
   6.000   0.7983   0.01102   0.00449  -0.0153   0.2243   0.9869
   6.250   0.8255   0.01152   0.00484  -0.0157   0.1907   0.9882
   6.500   0.8517   0.01209   0.00523  -0.0159   0.1574   0.9897
   6.750   0.8771   0.01269   0.00565  -0.0161   0.1211   0.9914
   7.000   0.9025   0.01326   0.00608  -0.0161   0.0981   0.9932
   7.250   0.9301   0.01369   0.00647  -0.0166   0.0892   0.9944
   7.500   0.9588   0.01400   0.00681  -0.0172   0.0850   0.9955
   7.750   0.9868   0.01436   0.00718  -0.0177   0.0810   0.9966
   8.000   1.0141   0.01476   0.00759  -0.0182   0.0772   0.9979
   8.250   1.0418   0.01511   0.00798  -0.0186   0.0739   0.9991
   8.500   1.0677   0.01540   0.00831  -0.0186   0.0703   1.0000
   8.750   1.0849   0.01574   0.00866  -0.0169   0.0657   1.0000
   9.000   1.1015   0.01610   0.00903  -0.0151   0.0613   1.0000
   9.250   1.1171   0.01649   0.00939  -0.0131   0.0513   1.0000
   9.500   1.1250   0.01732   0.01002  -0.0100   0.0284   1.0000
   9.750   1.1331   0.01810   0.01075  -0.0069   0.0201   1.0000
  10.000   1.1444   0.01869   0.01137  -0.0043   0.0175   1.0000
  10.250   1.1556   0.01928   0.01199  -0.0018   0.0160   1.0000
  10.500   1.1660   0.01995   0.01271   0.0008   0.0148   1.0000
  10.750   1.1760   0.02059   0.01342   0.0033   0.0141   1.0000
  11.000   1.1853   0.02125   0.01414   0.0059   0.0136   1.0000
  11.250   1.1951   0.02203   0.01499   0.0081   0.0130   1.0000
  11.500   1.2051   0.02294   0.01597   0.0099   0.0125   1.0000
  11.750   1.2144   0.02401   0.01711   0.0115   0.0120   1.0000
  12.000   1.2225   0.02528   0.01844   0.0129   0.0114   1.0000
  12.250   1.2280   0.02687   0.02012   0.0141   0.0109   1.0000
  12.500   1.2370   0.02830   0.02163   0.0149   0.0107   1.0000
  12.750   1.2458   0.02981   0.02323   0.0155   0.0104   1.0000
  13.000   1.2534   0.03152   0.02502   0.0160   0.0101   1.0000
  13.250   1.2599   0.03340   0.02700   0.0164   0.0098   1.0000
  13.500   1.2653   0.03545   0.02913   0.0166   0.0096   1.0000
  13.750   1.2698   0.03763   0.03141   0.0168   0.0094   1.0000
  14.000   1.2731   0.03996   0.03383   0.0168   0.0091   1.0000
  14.250   1.2752   0.04246   0.03642   0.0168   0.0090   1.0000
  14.500   1.2760   0.04513   0.03919   0.0167   0.0088   1.0000
  14.750   1.2750   0.04805   0.04219   0.0165   0.0086   1.0000
  15.000   1.2721   0.05124   0.04548   0.0162   0.0085   1.0000
  15.250   1.2674   0.05471   0.04904   0.0157   0.0084   1.0000
  15.500   1.2608   0.05856   0.05299   0.0149   0.0082   1.0000
  15.750   1.2522   0.06287   0.05740   0.0139   0.0081   1.0000
  16.000   1.2494   0.06655   0.06119   0.0129   0.0080   1.0000
  16.250   1.2460   0.07040   0.06516   0.0117   0.0079   1.0000
  16.500   1.2415   0.07453   0.06939   0.0104   0.0079   1.0000
  16.750   1.2367   0.07877   0.07375   0.0090   0.0077   1.0000
  17.000   1.2307   0.08321   0.07829   0.0074   0.0076   1.0000
  17.250   1.2239   0.08786   0.08305   0.0057   0.0076   1.0000
  17.500   1.2167   0.09263   0.08793   0.0039   0.0075   1.0000
  17.750   1.2087   0.09758   0.09298   0.0020   0.0074   1.0000
  18.000   1.2003   0.10265   0.09817   0.0000   0.0073   1.0000
  18.250   1.1918   0.10783   0.10345  -0.0022   0.0072   1.0000
  18.500   1.1831   0.11313   0.10886  -0.0044   0.0071   1.0000
  18.750   1.1744   0.11852   0.11435  -0.0068   0.0071   1.0000
<< Back to GOE 677 (= M 6) AIRFOIL (goe677-il)

Polar data table (+)

Polar graphs


<< Back to GOE 677 (= M 6) AIRFOIL (goe677-il)