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

GOE 601 AIRFOIL (goe601-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 601 AIRFOIL (goe601-il)
Reynolds number: 500,000
Max Cl/Cd: 68.97 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe601-il-500000-n5.txt
Download as CSV file: xf-goe601-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 601 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
  ------ -------- --------- --------- -------- -------- --------
 -19.750  -0.8259   0.12018   0.11673  -0.0565   1.0000   0.0206
 -19.500  -0.8440   0.11333   0.10977  -0.0600   1.0000   0.0207
 -19.250  -0.8577   0.10725   0.10360  -0.0632   1.0000   0.0210
 -19.000  -0.8722   0.10123   0.09749  -0.0663   1.0000   0.0213
 -18.750  -0.8858   0.09556   0.09172  -0.0691   1.0000   0.0215
 -18.500  -0.8980   0.09020   0.08624  -0.0718   1.0000   0.0217
 -18.250  -0.9092   0.08513   0.08108  -0.0742   1.0000   0.0219
 -18.000  -0.9196   0.08026   0.07611  -0.0765   1.0000   0.0221
 -17.750  -0.9292   0.07564   0.07137  -0.0786   1.0000   0.0224
 -17.500  -0.9376   0.07129   0.06691  -0.0805   1.0000   0.0226
 -17.250  -0.9456   0.06721   0.06273  -0.0822   1.0000   0.0227
 -17.000  -0.9524   0.06335   0.05876  -0.0837   1.0000   0.0230
 -16.750  -0.9593   0.05971   0.05502  -0.0849   1.0000   0.0232
 -16.500  -0.9672   0.05616   0.05142  -0.0859   1.0000   0.0235
 -16.250  -0.9732   0.05299   0.04818  -0.0866   1.0000   0.0236
 -16.000  -0.9798   0.04989   0.04502  -0.0871   1.0000   0.0238
 -15.750  -0.9837   0.04715   0.04222  -0.0874   1.0000   0.0241
 -15.500  -0.9883   0.04449   0.03948  -0.0874   1.0000   0.0242
 -15.250  -0.9912   0.04211   0.03704  -0.0872   1.0000   0.0245
 -15.000  -0.9939   0.03990   0.03476  -0.0868   1.0000   0.0248
 -14.750  -0.9969   0.03783   0.03262  -0.0860   1.0000   0.0251
 -14.500  -1.0004   0.03589   0.03060  -0.0848   1.0000   0.0254
 -14.250  -0.9896   0.03395   0.02858  -0.0861   0.9990   0.0259
 -14.000  -0.9730   0.03210   0.02663  -0.0881   0.9969   0.0264
 -13.750  -0.9557   0.03047   0.02489  -0.0898   0.9942   0.0268
 -13.500  -0.9397   0.02901   0.02332  -0.0909   0.9913   0.0271
 -13.250  -0.9269   0.02730   0.02155  -0.0919   0.9879   0.0276
 -13.000  -0.9097   0.02584   0.02005  -0.0932   0.9849   0.0282
 -12.750  -0.8885   0.02463   0.01877  -0.0947   0.9826   0.0287
 -12.500  -0.8730   0.02361   0.01770  -0.0945   0.9778   0.0291
 -12.250  -0.8527   0.02266   0.01668  -0.0951   0.9743   0.0296
 -12.000  -0.8286   0.02179   0.01574  -0.0961   0.9716   0.0303
 -11.750  -0.8066   0.02101   0.01489  -0.0965   0.9678   0.0309
 -11.500  -0.7848   0.02031   0.01412  -0.0966   0.9627   0.0314
 -11.250  -0.7572   0.01959   0.01332  -0.0978   0.9595   0.0319
 -11.000  -0.7332   0.01865   0.01236  -0.0986   0.9557   0.0328
 -10.750  -0.7166   0.01802   0.01168  -0.0973   0.9474   0.0334
 -10.500  -0.6893   0.01736   0.01098  -0.0982   0.9426   0.0341
 -10.250  -0.6747   0.01690   0.01046  -0.0961   0.9318   0.0346
 -10.000  -0.6542   0.01642   0.00993  -0.0952   0.9230   0.0353
  -9.750  -0.6327   0.01598   0.00941  -0.0945   0.9123   0.0360
  -9.500  -0.6118   0.01558   0.00895  -0.0935   0.8990   0.0367
  -9.250  -0.5898   0.01511   0.00840  -0.0928   0.8855   0.0374
  -9.000  -0.5679   0.01466   0.00788  -0.0920   0.8727   0.0384
  -8.750  -0.5458   0.01429   0.00742  -0.0912   0.8609   0.0394
  -8.500  -0.5239   0.01397   0.00702  -0.0903   0.8502   0.0405
  -8.250  -0.5025   0.01370   0.00667  -0.0892   0.8412   0.0419
  -8.000  -0.4808   0.01343   0.00632  -0.0882   0.8335   0.0435
  -7.750  -0.4599   0.01313   0.00599  -0.0871   0.8267   0.0458
  -7.500  -0.4382   0.01287   0.00569  -0.0860   0.8203   0.0487
  -7.250  -0.4165   0.01258   0.00538  -0.0850   0.8149   0.0542
  -7.000  -0.3957   0.01226   0.00513  -0.0838   0.8097   0.0660
  -6.750  -0.3733   0.01202   0.00494  -0.0830   0.8046   0.0820
  -6.500  -0.3490   0.01187   0.00478  -0.0823   0.8000   0.0909
  -6.250  -0.3242   0.01174   0.00462  -0.0818   0.7960   0.0960
  -6.000  -0.3006   0.01156   0.00445  -0.0810   0.7915   0.1012
  -5.750  -0.2759   0.01144   0.00429  -0.0804   0.7871   0.1050
  -5.500  -0.2503   0.01136   0.00415  -0.0800   0.7831   0.1078
  -5.250  -0.2262   0.01118   0.00395  -0.0794   0.7793   0.1124
  -5.000  -0.2020   0.01101   0.00379  -0.0787   0.7753   0.1165
  -4.750  -0.1772   0.01088   0.00365  -0.0781   0.7712   0.1202
  -4.500  -0.1522   0.01075   0.00349  -0.0776   0.7671   0.1247
  -4.250  -0.1272   0.01060   0.00333  -0.0770   0.7634   0.1302
  -4.000  -0.1029   0.01043   0.00319  -0.0764   0.7592   0.1389
  -3.750  -0.0807   0.01013   0.00302  -0.0754   0.7536   0.1647
  -3.500  -0.0596   0.00976   0.00285  -0.0742   0.7479   0.2221
  -3.250  -0.0363   0.00954   0.00274  -0.0734   0.7427   0.2596
  -3.000  -0.0122   0.00936   0.00265  -0.0727   0.7373   0.2838
  -2.750   0.0125   0.00923   0.00256  -0.0720   0.7322   0.3034
  -2.500   0.0373   0.00911   0.00247  -0.0714   0.7271   0.3212
  -2.250   0.0617   0.00898   0.00240  -0.0707   0.7210   0.3384
  -2.000   0.0861   0.00884   0.00234  -0.0700   0.7158   0.3614
  -1.750   0.1100   0.00870   0.00229  -0.0692   0.7107   0.3945
  -1.500   0.1341   0.00859   0.00228  -0.0684   0.7042   0.4236
  -1.250   0.1589   0.00854   0.00226  -0.0677   0.6973   0.4449
  -1.000   0.1843   0.00851   0.00224  -0.0672   0.6913   0.4612
  -0.750   0.2098   0.00848   0.00223  -0.0666   0.6844   0.4736
  -0.500   0.2348   0.00848   0.00220  -0.0660   0.6768   0.4842
  -0.250   0.2598   0.00845   0.00219  -0.0653   0.6681   0.4938
   0.000   0.2848   0.00846   0.00218  -0.0646   0.6607   0.5042
   0.250   0.3093   0.00844   0.00218  -0.0639   0.6512   0.5143
   0.500   0.3333   0.00846   0.00217  -0.0630   0.6398   0.5223
   0.750   0.3565   0.00848   0.00217  -0.0620   0.6279   0.5298
   1.000   0.3803   0.00850   0.00219  -0.0611   0.6159   0.5387
   1.250   0.4034   0.00852   0.00221  -0.0601   0.6044   0.5479
   1.500   0.4258   0.00857   0.00224  -0.0589   0.5907   0.5583
   1.750   0.4468   0.00861   0.00228  -0.0575   0.5752   0.5706
   2.000   0.4671   0.00867   0.00234  -0.0559   0.5585   0.5860
   2.250   0.4862   0.00871   0.00241  -0.0540   0.5414   0.6112
   2.500   0.5034   0.00875   0.00251  -0.0518   0.5214   0.6434
   2.750   0.5189   0.00885   0.00262  -0.0492   0.4980   0.6741
   3.000   0.5322   0.00901   0.00275  -0.0462   0.4692   0.7010
   3.250   0.5399   0.00922   0.00290  -0.0421   0.4324   0.7289
   3.500   0.5469   0.00947   0.00310  -0.0378   0.3951   0.7602
   3.750   0.5559   0.00972   0.00335  -0.0340   0.3652   0.7977
   4.000   0.5691   0.00995   0.00363  -0.0311   0.3434   0.8436
   4.250   0.5953   0.01025   0.00397  -0.0310   0.3228   0.8933
   4.500   0.6424   0.01066   0.00436  -0.0355   0.3065   0.9268
   4.750   0.6915   0.01103   0.00469  -0.0405   0.2936   0.9459
   5.000   0.7357   0.01137   0.00499  -0.0443   0.2829   0.9595
   5.250   0.7720   0.01168   0.00526  -0.0465   0.2746   0.9713
   5.750   0.8348   0.01223   0.00577  -0.0487   0.2596   0.9901
   6.000   0.8637   0.01256   0.00607  -0.0493   0.2516   0.9989
   6.250   0.8828   0.01280   0.00628  -0.0478   0.2436   1.0000
   6.500   0.8944   0.01304   0.00650  -0.0449   0.2382   1.0000
   6.750   0.9092   0.01325   0.00671  -0.0425   0.2319   1.0000
   7.000   0.9229   0.01353   0.00696  -0.0400   0.2247   1.0000
   7.250   0.9377   0.01381   0.00723  -0.0377   0.2174   1.0000
   7.500   0.9512   0.01416   0.00754  -0.0353   0.2073   1.0000
   7.750   0.9667   0.01449   0.00785  -0.0333   0.1984   1.0000
   8.000   0.9807   0.01489   0.00821  -0.0311   0.1879   1.0000
   8.250   0.9937   0.01538   0.00863  -0.0288   0.1733   1.0000
   8.500   1.0024   0.01609   0.00919  -0.0260   0.1484   1.0000
   8.750   0.9961   0.01762   0.01032  -0.0214   0.0872   1.0000
   9.000   0.9938   0.01910   0.01154  -0.0174   0.0450   1.0000
   9.250   1.0053   0.01988   0.01228  -0.0154   0.0381   1.0000
   9.500   1.0198   0.02051   0.01292  -0.0139   0.0358   1.0000
   9.750   1.0340   0.02119   0.01361  -0.0123   0.0343   1.0000
  10.000   1.0478   0.02191   0.01435  -0.0108   0.0329   1.0000
  10.250   1.0612   0.02267   0.01514  -0.0093   0.0319   1.0000
  10.500   1.0755   0.02340   0.01592  -0.0080   0.0314   1.0000
  10.750   1.0893   0.02419   0.01674  -0.0067   0.0307   1.0000
  11.000   1.1025   0.02502   0.01762  -0.0053   0.0300   1.0000
  11.250   1.1151   0.02592   0.01856  -0.0040   0.0293   1.0000
  11.500   1.1267   0.02691   0.01959  -0.0027   0.0287   1.0000
  11.750   1.1371   0.02802   0.02073  -0.0014   0.0282   1.0000
  12.000   1.1464   0.02921   0.02197   0.0000   0.0277   1.0000
  12.250   1.1535   0.03061   0.02342   0.0014   0.0272   1.0000
  12.500   1.1637   0.03180   0.02467   0.0026   0.0270   1.0000
  12.750   1.1738   0.03304   0.02598   0.0036   0.0267   1.0000
  13.000   1.1821   0.03443   0.02744   0.0047   0.0264   1.0000
  13.250   1.1904   0.03587   0.02894   0.0057   0.0260   1.0000
  13.500   1.1971   0.03748   0.03062   0.0066   0.0257   1.0000
  13.750   1.2041   0.03912   0.03232   0.0075   0.0253   1.0000
  14.000   1.2094   0.04095   0.03421   0.0083   0.0250   1.0000
  14.250   1.2147   0.04283   0.03616   0.0090   0.0246   1.0000
  14.500   1.2182   0.04494   0.03834   0.0096   0.0243   1.0000
  14.750   1.2214   0.04715   0.04062   0.0101   0.0240   1.0000
  15.000   1.2219   0.04970   0.04323   0.0105   0.0237   1.0000
  15.250   1.2217   0.05240   0.04601   0.0108   0.0235   1.0000
  15.500   1.2177   0.05560   0.04927   0.0109   0.0231   1.0000
  15.750   1.2166   0.05859   0.05234   0.0109   0.0229   1.0000
  16.000   1.2177   0.06140   0.05525   0.0108   0.0227   1.0000
  16.250   1.2179   0.06436   0.05830   0.0105   0.0225   1.0000
  16.500   1.2172   0.06751   0.06154   0.0101   0.0224   1.0000
  16.750   1.2162   0.07077   0.06489   0.0096   0.0222   1.0000
  17.000   1.2141   0.07421   0.06843   0.0090   0.0220   1.0000
  17.250   1.2123   0.07769   0.07200   0.0082   0.0217   1.0000
  17.500   1.2101   0.08125   0.07565   0.0073   0.0214   1.0000
  17.750   1.2066   0.08505   0.07954   0.0064   0.0212   1.0000
  18.000   1.2040   0.08880   0.08338   0.0053   0.0209   1.0000
  18.250   1.2002   0.09274   0.08739   0.0041   0.0207   1.0000
  18.500   1.1968   0.09662   0.09135   0.0029   0.0205   1.0000
<< Back to GOE 601 AIRFOIL (goe601-il)

Polar data table (+)

Polar graphs


<< Back to GOE 601 AIRFOIL (goe601-il)