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

GOE 776 AIRFOIL (goe776-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 776 AIRFOIL (goe776-il)
Reynolds number: 200,000
Max Cl/Cd: 41.19 at α=10.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe776-il-200000.txt
Download as CSV file: xf-goe776-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -19.750  -1.1498   0.09093   0.08445  -0.0532   1.0000   0.1299
 -19.500  -1.1478   0.08825   0.08175  -0.0541   1.0000   0.1322
 -19.250  -1.1685   0.08271   0.07603  -0.0560   1.0000   0.1346
 -19.000  -1.2032   0.07573   0.06873  -0.0582   1.0000   0.1368
 -18.750  -1.1825   0.07540   0.06852  -0.0579   1.0000   0.1392
 -18.500  -1.1703   0.07408   0.06725  -0.0581   1.0000   0.1416
 -18.250  -1.1738   0.07095   0.06405  -0.0588   1.0000   0.1442
 -18.000  -1.1901   0.06649   0.05938  -0.0597   1.0000   0.1467
 -17.750  -1.1935   0.06353   0.05632  -0.0601   1.0000   0.1491
 -17.500  -1.1763   0.06276   0.05567  -0.0599   1.0000   0.1517
 -17.250  -1.1714   0.06077   0.05365  -0.0600   1.0000   0.1544
 -17.000  -1.1767   0.05779   0.05055  -0.0602   1.0000   0.1572
 -16.750  -1.1911   0.05412   0.04665  -0.0602   1.0000   0.1596
 -16.500  -1.1693   0.05369   0.04637  -0.0599   1.0000   0.1625
 -16.250  -1.1606   0.05221   0.04491  -0.0597   1.0000   0.1654
 -16.000  -1.1596   0.05009   0.04273  -0.0593   1.0000   0.1684
 -15.750  -1.1664   0.04745   0.03991  -0.0588   1.0000   0.1712
 -15.500  -1.1527   0.04637   0.03888  -0.0583   1.0000   0.1744
 -15.250  -1.1425   0.04515   0.03771  -0.0577   1.0000   0.1774
 -15.000  -1.1385   0.04354   0.03606  -0.0569   1.0000   0.1807
 -14.750  -1.1414   0.04155   0.03394  -0.0558   1.0000   0.1839
 -14.500  -1.1303   0.04043   0.03285  -0.0549   1.0000   0.1873
 -14.250  -1.1203   0.03940   0.03187  -0.0539   1.0000   0.1906
 -14.000  -1.1161   0.03812   0.03056  -0.0526   1.0000   0.1942
 -13.750  -1.1184   0.03662   0.02893  -0.0506   1.0000   0.1978
 -13.500  -1.1078   0.03570   0.02808  -0.0492   1.0000   0.2015
 -13.250  -1.1011   0.03483   0.02725  -0.0473   1.0000   0.2051
 -13.000  -1.0999   0.03385   0.02625  -0.0449   1.0000   0.2090
 -12.750  -1.1051   0.03276   0.02505  -0.0416   1.0000   0.2127
 -12.500  -1.0963   0.03208   0.02446  -0.0395   1.0000   0.2167
 -12.250  -1.0951   0.03141   0.02384  -0.0364   1.0000   0.2205
 -12.000  -1.0993   0.03072   0.02312  -0.0325   1.0000   0.2245
 -11.750  -1.1095   0.03003   0.02233  -0.0276   1.0000   0.2281
 -11.500  -1.1066   0.02951   0.02190  -0.0243   1.0000   0.2321
 -11.250  -1.1112   0.02907   0.02151  -0.0199   1.0000   0.2358
 -11.000  -1.1204   0.02864   0.02106  -0.0148   1.0000   0.2396
 -10.750  -1.1338   0.02823   0.02058  -0.0089   1.0000   0.2432
 -10.500  -1.1403   0.02783   0.02019  -0.0041   1.0000   0.2470
 -10.250  -1.1170   0.02729   0.01973  -0.0046   0.9967   0.2528
 -10.000  -1.0880   0.02672   0.01907  -0.0063   0.9917   0.2600
  -9.750  -1.0557   0.02611   0.01855  -0.0081   0.9865   0.2666
  -9.500  -1.0260   0.02561   0.01804  -0.0096   0.9803   0.2738
  -9.250  -0.9909   0.02507   0.01746  -0.0119   0.9762   0.2814
  -9.000  -0.9643   0.02459   0.01706  -0.0124   0.9680   0.2880
  -8.750  -0.9340   0.02412   0.01650  -0.0137   0.9620   0.2957
  -8.500  -0.8904   0.02354   0.01605  -0.0173   0.9592   0.3037
  -8.250  -0.8713   0.02316   0.01564  -0.0162   0.9481   0.3106
  -8.000  -0.8312   0.02257   0.01506  -0.0190   0.9439   0.3188
  -7.750  -0.7870   0.02200   0.01455  -0.0226   0.9411   0.3274
  -7.500  -0.7714   0.02166   0.01409  -0.0205   0.9287   0.3343
  -7.250  -0.7291   0.02106   0.01365  -0.0234   0.9245   0.3425
  -7.000  -0.7009   0.02065   0.01319  -0.0236   0.9173   0.3507
  -6.750  -0.6753   0.02020   0.01279  -0.0232   0.9072   0.3580
  -6.500  -0.6423   0.01974   0.01236  -0.0241   0.9015   0.3662
  -6.250  -0.6282   0.01952   0.01203  -0.0214   0.8887   0.3736
  -6.000  -0.5950   0.01901   0.01166  -0.0222   0.8815   0.3816
  -5.750  -0.5745   0.01877   0.01138  -0.0207   0.8709   0.3896
  -5.500  -0.5503   0.01840   0.01099  -0.0198   0.8606   0.3975
  -5.250  -0.5241   0.01810   0.01074  -0.0193   0.8515   0.4054
  -5.000  -0.5049   0.01790   0.01046  -0.0175   0.8392   0.4136
  -4.750  -0.4758   0.01753   0.01014  -0.0174   0.8304   0.4217
  -4.500  -0.4553   0.01737   0.00999  -0.0159   0.8174   0.4297
  -4.250  -0.4298   0.01712   0.00962  -0.0152   0.8082   0.4384
  -4.000  -0.4067   0.01693   0.00954  -0.0141   0.7949   0.4462
  -3.750  -0.3813   0.01675   0.00924  -0.0134   0.7853   0.4554
  -3.500  -0.3587   0.01657   0.00913  -0.0123   0.7722   0.4636
  -3.250  -0.3319   0.01641   0.00892  -0.0118   0.7621   0.4725
  -3.000  -0.3117   0.01632   0.00879  -0.0102   0.7493   0.4815
  -2.750  -0.2831   0.01614   0.00864  -0.0101   0.7389   0.4902
  -2.500  -0.2620   0.01608   0.00855  -0.0087   0.7265   0.4998
  -2.250  -0.2347   0.01592   0.00840  -0.0083   0.7158   0.5088
  -2.000  -0.2118   0.01588   0.00837  -0.0072   0.7037   0.5184
  -1.750  -0.1866   0.01578   0.00820  -0.0065   0.6928   0.5282
  -1.500  -0.1620   0.01573   0.00821  -0.0057   0.6811   0.5376
  -1.250  -0.1389   0.01569   0.00806  -0.0046   0.6699   0.5483
  -1.000  -0.1124   0.01562   0.00809  -0.0041   0.6585   0.5576
  -0.750  -0.0894   0.01560   0.00800  -0.0030   0.6473   0.5688
  -0.500  -0.0630   0.01556   0.00801  -0.0025   0.6364   0.5786
  -0.250  -0.0397   0.01555   0.00798  -0.0015   0.6249   0.5897
   0.000  -0.0135   0.01554   0.00795  -0.0009   0.6145   0.6001
   0.250   0.0098   0.01554   0.00798   0.0001   0.6029   0.6112
   0.500   0.0361   0.01556   0.00793   0.0006   0.5930   0.6222
   0.750   0.0593   0.01556   0.00802   0.0017   0.5815   0.6331
   1.000   0.0851   0.01560   0.00796   0.0023   0.5719   0.6447
   1.250   0.1089   0.01562   0.00809   0.0033   0.5607   0.6554
   1.500   0.1330   0.01565   0.00804   0.0042   0.5511   0.6674
   1.750   0.1586   0.01572   0.00819   0.0048   0.5408   0.6781
   2.000   0.1811   0.01575   0.00818   0.0060   0.5310   0.6904
   2.250   0.2086   0.01586   0.00833   0.0063   0.5216   0.7009
   2.750   0.2592   0.01607   0.00850   0.0077   0.5028   0.7238
   3.000   0.2790   0.01612   0.00861   0.0093   0.4933   0.7366
   3.250   0.3065   0.01625   0.00876   0.0097   0.4843   0.7468
   3.500   0.3288   0.01639   0.00889   0.0108   0.4756   0.7597
   3.750   0.3543   0.01652   0.00910   0.0115   0.4664   0.7698
   4.000   0.3797   0.01674   0.00920   0.0122   0.4583   0.7826
   4.250   0.4029   0.01688   0.00949   0.0133   0.4492   0.7927
   4.500   0.4260   0.01705   0.00962   0.0144   0.4411   0.8053
   4.750   0.4521   0.01732   0.00991   0.0149   0.4328   0.8154
   5.000   0.4734   0.01751   0.01013   0.0164   0.4244   0.8276
   5.250   0.5015   0.01782   0.01035   0.0165   0.4165   0.8374
   5.500   0.5223   0.01807   0.01070   0.0181   0.4084   0.8487
   5.750   0.5449   0.01830   0.01093   0.0193   0.4004   0.8593
   6.000   0.5733   0.01873   0.01130   0.0194   0.3926   0.8684
   6.250   0.5907   0.01893   0.01158   0.0215   0.3847   0.8804
   6.500   0.6216   0.01937   0.01194   0.0211   0.3767   0.8876
   6.750   0.6383   0.01965   0.01224   0.0233   0.3695   0.9005
   7.000   0.6701   0.02010   0.01272   0.0226   0.3609   0.9062
   7.250   0.7031   0.02061   0.01311   0.0216   0.3533   0.9139
   7.500   0.7240   0.02095   0.01354   0.0229   0.3456   0.9238
   7.750   0.7627   0.02148   0.01399   0.0206   0.3374   0.9284
   8.000   0.7819   0.02188   0.01440   0.0221   0.3306   0.9406
   8.250   0.8245   0.02243   0.01497   0.0188   0.3217   0.9435
   8.500   0.8683   0.02305   0.01548   0.0153   0.3136   0.9469
   8.750   0.8923   0.02347   0.01597   0.0155   0.3061   0.9563
   9.000   0.9285   0.02396   0.01635   0.0133   0.2986   0.9615
   9.250   0.9616   0.02447   0.01693   0.0115   0.2908   0.9668
   9.500   0.9853   0.02492   0.01737   0.0115   0.2841   0.9759
   9.750   1.0238   0.02547   0.01786   0.0086   0.2766   0.9794
  10.000   1.0530   0.02596   0.01841   0.0072   0.2692   0.9856
  10.250   1.0857   0.02654   0.01884   0.0054   0.2626   0.9911
  10.500   1.1146   0.02711   0.01954   0.0037   0.2556   0.9959
  10.750   1.1397   0.02767   0.02008   0.0028   0.2493   1.0000
  11.000   1.1406   0.02805   0.02033   0.0065   0.2452   1.0000
  11.250   1.1246   0.02844   0.02084   0.0128   0.2418   1.0000
  11.500   1.1139   0.02887   0.02131   0.0181   0.2380   1.0000
  11.750   1.1068   0.02932   0.02175   0.0229   0.2343   1.0000
  12.000   1.1095   0.02978   0.02209   0.0263   0.2304   1.0000
  12.250   1.1035   0.03043   0.02279   0.0307   0.2267   1.0000
  12.500   1.0972   0.03115   0.02357   0.0349   0.2227   1.0000
  12.750   1.0964   0.03184   0.02426   0.0382   0.2189   1.0000
  13.000   1.1057   0.03244   0.02472   0.0403   0.2148   1.0000
  13.250   1.1040   0.03345   0.02580   0.0433   0.2111   1.0000
  13.500   1.1029   0.03450   0.02692   0.0460   0.2072   1.0000
  13.750   1.1070   0.03546   0.02787   0.0481   0.2034   1.0000
  14.000   1.1250   0.03604   0.02828   0.0490   0.1994   1.0000
  14.250   1.1200   0.03763   0.03003   0.0512   0.1961   1.0000
  14.500   1.1220   0.03902   0.03148   0.0527   0.1924   1.0000
  14.750   1.1293   0.04019   0.03265   0.0538   0.1890   1.0000
  15.000   1.1487   0.04083   0.03313   0.0543   0.1853   1.0000
  15.250   1.1429   0.04295   0.03543   0.0557   0.1823   1.0000
  15.500   1.1446   0.04471   0.03727   0.0565   0.1789   1.0000
  15.750   1.1523   0.04610   0.03865   0.0571   0.1758   1.0000
  16.000   1.1747   0.04654   0.03891   0.0575   0.1724   1.0000
  16.250   1.1650   0.04936   0.04195   0.0581   0.1698   1.0000
  16.500   1.1637   0.05167   0.04436   0.0585   0.1667   1.0000
  16.750   1.1698   0.05338   0.04608   0.0587   0.1637   1.0000
  17.000   1.1872   0.05414   0.04672   0.0590   0.1609   1.0000
  17.250   1.1838   0.05684   0.04955   0.0591   0.1582   1.0000
  17.500   1.1762   0.06004   0.05290   0.0589   0.1554   1.0000
  17.750   1.1784   0.06231   0.05521   0.0587   0.1527   1.0000
  18.000   1.1917   0.06347   0.05630   0.0588   0.1501   1.0000
  18.250   1.1998   0.06522   0.05804   0.0588   0.1475   1.0000
  18.500   1.1813   0.06989   0.06293   0.0578   0.1451   1.0000
  18.750   1.1752   0.07331   0.06646   0.0571   0.1425   1.0000
  19.000   1.1834   0.07510   0.06823   0.0567   0.1400   1.0000
  19.250   1.2143   0.07426   0.06719   0.0574   0.1375   1.0000
<< Back to GOE 776 AIRFOIL (goe776-il)

Polar data table (+)

Polar graphs


<< Back to GOE 776 AIRFOIL (goe776-il)