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

GOE 770 AIRFOIL (goe770-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 770 AIRFOIL (goe770-il)
Reynolds number: 500,000
Max Cl/Cd: 86.08 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe770-il-500000-n5.txt
Download as CSV file: xf-goe770-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 770 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  -1.0162   0.09697   0.09260  -0.0413   1.0000   0.0276
 -19.500  -1.0233   0.09226   0.08783  -0.0437   1.0000   0.0278
 -19.250  -1.0300   0.08765   0.08315  -0.0461   1.0000   0.0280
 -19.000  -1.0362   0.08311   0.07854  -0.0484   1.0000   0.0282
 -18.750  -1.0416   0.07871   0.07406  -0.0507   1.0000   0.0284
 -18.500  -1.0460   0.07453   0.06980  -0.0527   1.0000   0.0286
 -18.250  -1.0495   0.07057   0.06576  -0.0546   1.0000   0.0288
 -18.000  -1.0520   0.06682   0.06193  -0.0564   1.0000   0.0291
 -17.750  -1.0535   0.06330   0.05833  -0.0579   1.0000   0.0294
 -17.500  -1.0542   0.06001   0.05496  -0.0593   1.0000   0.0296
 -17.250  -1.0538   0.05691   0.05177  -0.0605   1.0000   0.0299
 -17.000  -1.0528   0.05397   0.04875  -0.0616   1.0000   0.0302
 -16.750  -1.0511   0.05119   0.04589  -0.0625   1.0000   0.0305
 -16.500  -1.0483   0.04862   0.04323  -0.0632   1.0000   0.0307
 -16.250  -1.0443   0.04620   0.04073  -0.0639   1.0000   0.0310
 -16.000  -1.0414   0.04373   0.03821  -0.0644   1.0000   0.0312
 -15.750  -1.0380   0.04133   0.03577  -0.0650   1.0000   0.0315
 -15.500  -1.0327   0.03913   0.03353  -0.0655   1.0000   0.0318
 -15.250  -1.0252   0.03723   0.03147  -0.0660   0.8919   0.0321
 -15.000  -1.0215   0.03571   0.02963  -0.0649   0.8166   0.0324
 -14.750  -1.0130   0.03415   0.02785  -0.0648   0.7780   0.0328
 -14.500  -1.0032   0.03265   0.02617  -0.0647   0.7467   0.0332
 -14.250  -0.9924   0.03122   0.02458  -0.0646   0.7205   0.0336
 -14.000  -0.9809   0.02988   0.02308  -0.0645   0.6988   0.0340
 -13.750  -0.9687   0.02862   0.02167  -0.0643   0.6813   0.0344
 -13.500  -0.9557   0.02745   0.02038  -0.0640   0.6683   0.0348
 -13.250  -0.9438   0.02627   0.01909  -0.0635   0.6573   0.0352
 -13.000  -0.9314   0.02515   0.01792  -0.0629   0.6485   0.0356
 -12.750  -0.9174   0.02421   0.01691  -0.0622   0.6400   0.0361
 -12.500  -0.9023   0.02339   0.01602  -0.0614   0.6332   0.0367
 -12.250  -0.8864   0.02264   0.01520  -0.0605   0.6266   0.0373
 -12.000  -0.8700   0.02196   0.01444  -0.0595   0.6199   0.0379
 -11.750  -0.8531   0.02134   0.01372  -0.0584   0.6137   0.0384
 -11.500  -0.8356   0.02076   0.01308  -0.0573   0.6088   0.0390
 -11.250  -0.8205   0.02019   0.01247  -0.0557   0.6038   0.0396
 -11.000  -0.8049   0.01971   0.01195  -0.0540   0.5991   0.0402
 -10.750  -0.7855   0.01927   0.01146  -0.0529   0.5946   0.0410
 -10.500  -0.7647   0.01886   0.01100  -0.0519   0.5907   0.0419
 -10.250  -0.7431   0.01847   0.01056  -0.0511   0.5870   0.0429
 -10.000  -0.7211   0.01808   0.01013  -0.0502   0.5830   0.0438
  -9.750  -0.6993   0.01767   0.00969  -0.0494   0.5787   0.0448
  -9.500  -0.6765   0.01732   0.00930  -0.0486   0.5745   0.0460
  -9.250  -0.6531   0.01701   0.00893  -0.0480   0.5706   0.0473
  -9.000  -0.6288   0.01669   0.00858  -0.0474   0.5677   0.0486
  -8.750  -0.6050   0.01634   0.00823  -0.0468   0.5646   0.0501
  -8.500  -0.5804   0.01604   0.00792  -0.0462   0.5612   0.0519
  -8.250  -0.5552   0.01578   0.00762  -0.0458   0.5576   0.0538
  -8.000  -0.5305   0.01549   0.00731  -0.0452   0.5540   0.0559
  -7.750  -0.5051   0.01526   0.00703  -0.0448   0.5505   0.0582
  -7.500  -0.4792   0.01501   0.00677  -0.0444   0.5479   0.0606
  -7.250  -0.4533   0.01475   0.00652  -0.0441   0.5451   0.0634
  -6.750  -0.4008   0.01430   0.00607  -0.0434   0.5385   0.0698
  -6.500  -0.3741   0.01412   0.00585  -0.0432   0.5352   0.0735
  -6.250  -0.3477   0.01392   0.00564  -0.0429   0.5321   0.0774
  -6.000  -0.3208   0.01377   0.00545  -0.0426   0.5290   0.0813
  -5.750  -0.2939   0.01355   0.00527  -0.0424   0.5259   0.0857
  -5.500  -0.2666   0.01338   0.00509  -0.0422   0.5220   0.0903
  -5.250  -0.2397   0.01318   0.00489  -0.0420   0.5178   0.0958
  -5.000  -0.2126   0.01302   0.00471  -0.0418   0.5141   0.1013
  -4.750  -0.1857   0.01286   0.00454  -0.0416   0.5107   0.1079
  -4.500  -0.1586   0.01266   0.00436  -0.0414   0.5080   0.1165
  -4.250  -0.1319   0.01240   0.00418  -0.0412   0.5050   0.1313
  -4.000  -0.1084   0.01185   0.00391  -0.0407   0.5018   0.1909
  -3.750  -0.0828   0.01150   0.00378  -0.0404   0.4987   0.2453
  -3.500  -0.0555   0.01134   0.00368  -0.0403   0.4956   0.2704
  -3.250  -0.0279   0.01122   0.00357  -0.0402   0.4924   0.2883
  -3.000   0.0000   0.01111   0.00348  -0.0401   0.4893   0.3033
  -2.750   0.0282   0.01098   0.00339  -0.0401   0.4862   0.3179
  -2.500   0.0556   0.01080   0.00329  -0.0400   0.4829   0.3389
  -2.250   0.0815   0.01050   0.00319  -0.0397   0.4797   0.3852
  -2.000   0.1077   0.01030   0.00319  -0.0395   0.4765   0.4498
  -1.750   0.1358   0.01028   0.00319  -0.0394   0.4732   0.4750
  -1.500   0.1646   0.01027   0.00319  -0.0395   0.4700   0.4926
  -1.250   0.1933   0.01024   0.00320  -0.0396   0.4664   0.5051
  -1.000   0.2224   0.01026   0.00320  -0.0397   0.4623   0.5153
  -0.750   0.2509   0.01026   0.00321  -0.0398   0.4585   0.5245
  -0.500   0.2796   0.01031   0.00322  -0.0399   0.4548   0.5336
  -0.250   0.3084   0.01031   0.00324  -0.0400   0.4516   0.5418
   0.000   0.3373   0.01032   0.00327  -0.0401   0.4478   0.5503
   0.250   0.3663   0.01037   0.00329  -0.0403   0.4436   0.5571
   0.500   0.3948   0.01040   0.00331  -0.0404   0.4393   0.5624
   0.750   0.4231   0.01045   0.00335  -0.0405   0.4351   0.5683
   1.000   0.4520   0.01048   0.00339  -0.0407   0.4306   0.5744
   1.250   0.4808   0.01054   0.00343  -0.0408   0.4255   0.5791
   1.500   0.5089   0.01061   0.00347  -0.0409   0.4207   0.5837
   1.750   0.5371   0.01066   0.00353  -0.0410   0.4165   0.5890
   2.000   0.5656   0.01071   0.00360  -0.0412   0.4117   0.5952
   2.250   0.5938   0.01079   0.00367  -0.0413   0.4066   0.6016
   2.500   0.6211   0.01089   0.00375  -0.0413   0.4018   0.6086
   2.750   0.6493   0.01094   0.00384  -0.0414   0.3973   0.6167
   3.000   0.6772   0.01103   0.00393  -0.0415   0.3923   0.6240
   3.250   0.7043   0.01114   0.00404  -0.0414   0.3873   0.6314
   3.500   0.7314   0.01124   0.00416  -0.0414   0.3827   0.6411
   3.750   0.7588   0.01132   0.00428  -0.0414   0.3778   0.6518
   4.000   0.7854   0.01143   0.00442  -0.0413   0.3728   0.6648
   4.250   0.8112   0.01156   0.00457  -0.0411   0.3682   0.6804
   4.500   0.8379   0.01163   0.00472  -0.0410   0.3646   0.6994
   4.750   0.8642   0.01172   0.00489  -0.0409   0.3607   0.7201
   5.000   0.8899   0.01183   0.00507  -0.0406   0.3568   0.7409
   5.250   0.9148   0.01196   0.00526  -0.0403   0.3532   0.7638
   5.500   0.9394   0.01208   0.00547  -0.0398   0.3500   0.7899
   5.750   0.9645   0.01216   0.00567  -0.0394   0.3472   0.8192
   6.000   0.9889   0.01227   0.00589  -0.0389   0.3441   0.8502
   6.250   1.0126   0.01241   0.00612  -0.0382   0.3412   0.8823
   6.500   1.0375   0.01260   0.00638  -0.0378   0.3382   0.9157
   6.750   1.0685   0.01287   0.00668  -0.0388   0.3349   0.9468
   7.000   1.1036   0.01312   0.00695  -0.0406   0.3323   0.9697
   7.250   1.1376   0.01335   0.00721  -0.0423   0.3297   0.9867
   7.500   1.1715   0.01361   0.00749  -0.0441   0.3271   0.9984
   7.750   1.1926   0.01387   0.00774  -0.0432   0.3241   1.0000
   8.000   1.2106   0.01415   0.00801  -0.0418   0.3211   1.0000
   8.250   1.2278   0.01448   0.00832  -0.0403   0.3181   1.0000
   8.500   1.2463   0.01474   0.00861  -0.0390   0.3159   1.0000
   8.750   1.2649   0.01500   0.00891  -0.0377   0.3136   1.0000
   9.000   1.2829   0.01531   0.00924  -0.0364   0.3108   1.0000
   9.250   1.3006   0.01567   0.00962  -0.0352   0.3081   1.0000
   9.500   1.3173   0.01610   0.01006  -0.0340   0.3052   1.0000
   9.750   1.3322   0.01665   0.01060  -0.0326   0.3018   1.0000
  10.000   1.3504   0.01711   0.01109  -0.0318   0.2988   1.0000
  10.250   1.3689   0.01758   0.01161  -0.0311   0.2958   1.0000
  10.500   1.3861   0.01814   0.01221  -0.0304   0.2928   1.0000
  10.750   1.4016   0.01882   0.01292  -0.0295   0.2896   1.0000
  11.000   1.4156   0.01964   0.01375  -0.0287   0.2866   1.0000
  11.250   1.4302   0.02048   0.01461  -0.0280   0.2840   1.0000
  11.500   1.4474   0.02120   0.01540  -0.0277   0.2814   1.0000
  11.750   1.4625   0.02209   0.01635  -0.0273   0.2778   1.0000
  12.000   1.4749   0.02321   0.01750  -0.0268   0.2738   1.0000
  12.250   1.4848   0.02455   0.01885  -0.0262   0.2703   1.0000
  12.500   1.4976   0.02571   0.02007  -0.0259   0.2674   1.0000
  12.750   1.5104   0.02692   0.02135  -0.0257   0.2636   1.0000
  13.000   1.5191   0.02848   0.02295  -0.0253   0.2590   1.0000
  13.250   1.5234   0.03043   0.02491  -0.0249   0.2547   1.0000
  13.500   1.5331   0.03196   0.02652  -0.0247   0.2505   1.0000
  13.750   1.5381   0.03391   0.02852  -0.0244   0.2449   1.0000
  14.000   1.5368   0.03643   0.03105  -0.0239   0.2391   1.0000
  14.250   1.5392   0.03863   0.03330  -0.0236   0.2319   1.0000
  14.500   1.5332   0.04164   0.03632  -0.0232   0.2244   1.0000
  14.750   1.5285   0.04459   0.03929  -0.0229   0.2153   1.0000
  15.000   1.5185   0.04813   0.04283  -0.0225   0.2054   1.0000
  15.250   1.5037   0.05222   0.04692  -0.0223   0.1950   1.0000
  15.500   1.4873   0.05660   0.05129  -0.0221   0.1853   1.0000
  15.750   1.4720   0.06095   0.05564  -0.0220   0.1761   1.0000
  16.000   1.4591   0.06512   0.05982  -0.0221   0.1688   1.0000
  16.250   1.4461   0.06939   0.06410  -0.0222   0.1622   1.0000
  16.500   1.4393   0.07301   0.06776  -0.0225   0.1569   1.0000
  16.750   1.4307   0.07688   0.07166  -0.0228   0.1521   1.0000
  17.000   1.4238   0.08061   0.07542  -0.0231   0.1478   1.0000
  17.250   1.4189   0.08417   0.07904  -0.0236   0.1435   1.0000
  17.500   1.4110   0.08807   0.08296  -0.0241   0.1390   1.0000
  17.750   1.4049   0.09183   0.08677  -0.0247   0.1349   1.0000
  18.000   1.3992   0.09558   0.09056  -0.0254   0.1301   1.0000
  18.250   1.3902   0.09979   0.09479  -0.0262   0.1257   1.0000
  18.500   1.3854   0.10349   0.09854  -0.0269   0.1208   1.0000
<< Back to GOE 770 AIRFOIL (goe770-il)

Polar data table (+)

Polar graphs


<< Back to GOE 770 AIRFOIL (goe770-il)