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GOE 776 AIRFOIL (goe776-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 776 AIRFOIL (goe776-il)
Reynolds number: 50,000
Max Cl/Cd: 19.25 at α=8.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe776-il-50000-n5.txt
Download as CSV file: xf-goe776-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 776 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.4795   0.10744   0.09714  -0.0420   1.0000   0.2304
 -12.000  -0.5135   0.09660   0.08626  -0.0439   1.0000   0.2447
 -11.750  -0.4940   0.09671   0.08642  -0.0427   1.0000   0.2472
 -11.250  -0.5364   0.08568   0.07537  -0.0435   1.0000   0.2631
 -10.750  -0.5955   0.07417   0.06383  -0.0429   1.0000   0.2804
 -10.250  -0.6953   0.06136   0.05089  -0.0388   1.0000   0.2982
 -10.000  -0.6540   0.06367   0.05335  -0.0375   1.0000   0.3009
  -9.750  -0.6526   0.06271   0.05244  -0.0352   1.0000   0.3061
  -9.500  -0.8082   0.05175   0.04116  -0.0244   1.0000   0.3161
  -9.250  -0.7746   0.05290   0.04248  -0.0237   1.0000   0.3204
  -9.000  -0.7939   0.05154   0.04114  -0.0189   1.0000   0.3256
  -8.750  -0.8573   0.04868   0.03814  -0.0094   1.0000   0.3307
  -8.500  -0.9193   0.04664   0.03595   0.0014   1.0000   0.3346
  -8.250  -0.8734   0.04716   0.03666  -0.0012   0.9968   0.3408
  -8.000  -0.8589   0.04597   0.03536  -0.0014   0.9872   0.3492
  -7.750  -0.8360   0.04504   0.03438  -0.0024   0.9778   0.3571
  -7.500  -0.8009   0.04480   0.03418  -0.0043   0.9692   0.3649
  -7.250  -0.7938   0.04312   0.03229  -0.0037   0.9583   0.3745
  -7.000  -0.7500   0.04337   0.03269  -0.0061   0.9492   0.3814
  -6.750  -0.7263   0.04233   0.03154  -0.0071   0.9404   0.3911
  -6.500  -0.7033   0.04187   0.03111  -0.0070   0.9282   0.3986
  -6.250  -0.6609   0.04154   0.03079  -0.0100   0.9213   0.4077
  -6.000  -0.6598   0.04040   0.02951  -0.0069   0.9066   0.4165
  -5.750  -0.6033   0.04051   0.02976  -0.0115   0.9010   0.4248
  -5.500  -0.5980   0.03969   0.02884  -0.0087   0.8866   0.4338
  -5.250  -0.5513   0.03939   0.02860  -0.0120   0.8799   0.4426
  -5.000  -0.5321   0.03908   0.02828  -0.0108   0.8672   0.4510
  -4.750  -0.5068   0.03826   0.02739  -0.0110   0.8582   0.4609
  -4.500  -0.4746   0.03827   0.02749  -0.0114   0.8471   0.4686
  -4.250  -0.4611   0.03738   0.02647  -0.0097   0.8363   0.4794
  -4.000  -0.4205   0.03737   0.02656  -0.0114   0.8273   0.4871
  -3.750  -0.4002   0.03702   0.02620  -0.0102   0.8154   0.4965
  -3.500  -0.3632   0.03642   0.02557  -0.0116   0.8088   0.5066
  -3.250  -0.3467   0.03649   0.02570  -0.0095   0.7943   0.5144
  -3.000  -0.3233   0.03566   0.02476  -0.0089   0.7864   0.5262
  -2.750  -0.2970   0.03590   0.02511  -0.0082   0.7732   0.5334
  -2.500  -0.2719   0.03530   0.02443  -0.0077   0.7644   0.5448
  -2.250  -0.2481   0.03531   0.02449  -0.0067   0.7523   0.5532
  -2.000  -0.2171   0.03507   0.02426  -0.0068   0.7426   0.5632
  -1.750  -0.1977   0.03472   0.02386  -0.0053   0.7323   0.5738
  -1.500  -0.1666   0.03478   0.02398  -0.0053   0.7208   0.5826
  -1.250  -0.1408   0.03407   0.02316  -0.0048   0.7137   0.5952
  -1.000  -0.1184   0.03450   0.02370  -0.0035   0.6993   0.6028
  -0.750  -0.0906   0.03399   0.02310  -0.0031   0.6913   0.6152
  -0.500  -0.0706   0.03426   0.02344  -0.0016   0.6783   0.6237
  -0.250  -0.0365   0.03408   0.02324  -0.0020   0.6692   0.6344
   0.000  -0.0211   0.03408   0.02324   0.0001   0.6578   0.6454
   0.250   0.0133   0.03417   0.02335  -0.0003   0.6475   0.6546
   0.500   0.0321   0.03389   0.02301   0.0013   0.6384   0.6674
   0.750   0.0615   0.03429   0.02349   0.0016   0.6262   0.6756
   1.000   0.0848   0.03380   0.02288   0.0026   0.6188   0.6897
   1.250   0.1095   0.03447   0.02367   0.0034   0.6057   0.6971
   1.500   0.1400   0.03431   0.02345   0.0035   0.5971   0.7090
   1.750   0.1595   0.03468   0.02386   0.0050   0.5860   0.7189
   2.000   0.1909   0.03483   0.02400   0.0049   0.5761   0.7291
   2.250   0.2134   0.03486   0.02401   0.0061   0.5671   0.7409
   2.500   0.2399   0.03535   0.02455   0.0065   0.5559   0.7499
   2.750   0.2686   0.03506   0.02416   0.0069   0.5486   0.7629
   3.000   0.2894   0.03587   0.02508   0.0080   0.5364   0.7711
   3.250   0.3080   0.03571   0.02486   0.0098   0.5286   0.7854
   3.500   0.3415   0.03636   0.02555   0.0090   0.5180   0.7924
   3.750   0.3613   0.03655   0.02573   0.0104   0.5088   0.8051
   4.000   0.3997   0.03673   0.02585   0.0090   0.5005   0.8136
   4.250   0.4159   0.03740   0.02661   0.0107   0.4898   0.8246
   4.500   0.4512   0.03732   0.02643   0.0098   0.4823   0.8353
   4.750   0.4708   0.03818   0.02739   0.0107   0.4718   0.8449
   5.000   0.4925   0.03834   0.02753   0.0117   0.4636   0.8575
   5.250   0.5317   0.03880   0.02797   0.0097   0.4545   0.8650
   5.500   0.5397   0.03940   0.02863   0.0124   0.4457   0.8792
   5.750   0.6005   0.03926   0.02833   0.0073   0.4375   0.8845
   6.000   0.5956   0.04037   0.02961   0.0115   0.4282   0.9001
   6.250   0.6450   0.04057   0.02975   0.0077   0.4191   0.9061
   6.500   0.6637   0.04122   0.03043   0.0084   0.4109   0.9186
   6.750   0.6924   0.04195   0.03122   0.0072   0.4014   0.9274
   7.000   0.7382   0.04177   0.03088   0.0044   0.3942   0.9362
   7.250   0.7439   0.04329   0.03261   0.0058   0.3844   0.9480
   7.500   0.7786   0.04339   0.03264   0.0043   0.3770   0.9582
   7.750   0.8017   0.04444   0.03377   0.0033   0.3682   0.9673
   8.000   0.8242   0.04521   0.03459   0.0027   0.3599   0.9775
   8.250   0.8699   0.04519   0.03447  -0.0007   0.3525   0.9843
   8.500   0.8677   0.04710   0.03660   0.0008   0.3438   0.9960
   8.750   0.8918   0.04722   0.03665   0.0006   0.3375   1.0000
   9.000   0.8828   0.04772   0.03709   0.0054   0.3330   1.0000
   9.250   0.8091   0.05069   0.04024   0.0164   0.3284   1.0000
   9.500   0.7638   0.05327   0.04288   0.0233   0.3228   1.0000
   9.750   0.7789   0.05299   0.04248   0.0255   0.3182   1.0000
  10.000   0.7431   0.05575   0.04527   0.0308   0.3129   1.0000
  10.250   0.6387   0.06473   0.05443   0.0369   0.3023   1.0000
  10.500   0.6718   0.06300   0.05258   0.0385   0.2993   1.0000
  11.000   0.5820   0.07532   0.06499   0.0420   0.2814   1.0000
  11.250   0.6173   0.07316   0.06273   0.0438   0.2796   1.0000
  11.750   0.5543   0.08518   0.07481   0.0442   0.2623   1.0000
  12.250   0.5101   0.09663   0.08629   0.0431   0.2461   1.0000
  12.750   0.4738   0.10777   0.09746   0.0412   0.2316   1.0000
  13.000   0.4890   0.10861   0.09826   0.0418   0.2287   1.0000
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