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GOE 803 (HACKLINGER) AIRFOIL (goe803h-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 803 (HACKLINGER) AIRFOIL (goe803h-il)
Reynolds number: 1,000,000
Max Cl/Cd: 122.21 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe803h-il-1000000-n5.txt
Download as CSV file: xf-goe803h-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 803 (HACKLINGER) AIRFOIL                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.1676   0.09050   0.08848  -0.0464   0.8803   0.0115
  -7.500  -0.1576   0.08792   0.08583  -0.0478   0.8644   0.0116
  -7.250  -0.1472   0.08532   0.08318  -0.0493   0.8496   0.0116
  -7.000  -0.1364   0.08271   0.08053  -0.0511   0.8349   0.0115
  -6.750  -0.1216   0.07994   0.07770  -0.0538   0.8197   0.0117
  -6.500  -0.1054   0.07711   0.07481  -0.0569   0.8039   0.0120
  -6.250  -0.0877   0.07409   0.07173  -0.0605   0.7886   0.0119
  -6.000  -0.0682   0.07098   0.06855  -0.0644   0.7738   0.0118
  -5.750  -0.0467   0.06780   0.06530  -0.0688   0.7595   0.0120
  -5.500  -0.0229   0.06448   0.06189  -0.0738   0.7459   0.0123
  -5.000   0.0348   0.05685   0.05412  -0.0864   0.7229   0.0128
  -4.750   0.0673   0.05308   0.05028  -0.0932   0.7144   0.0131
  -4.500   0.0943   0.05121   0.04837  -0.0964   0.7061   0.0134
  -4.250   0.1276   0.04815   0.04524  -0.1021   0.6982   0.0135
  -4.000   0.1648   0.04465   0.04166  -0.1087   0.6895   0.0135
  -3.750   0.2007   0.04184   0.03877  -0.1142   0.6809   0.0138
  -3.500   0.2386   0.03892   0.03574  -0.1198   0.6702   0.0142
  -2.500   0.4681   0.01044   0.00500  -0.1603   0.6228   0.0184
  -2.250   0.4975   0.00991   0.00427  -0.1606   0.6086   0.0189
  -2.000   0.5267   0.00952   0.00371  -0.1608   0.5972   0.0192
  -1.750   0.5556   0.00927   0.00332  -0.1609   0.5862   0.0194
  -1.500   0.5848   0.00889   0.00281  -0.1611   0.5742   0.0199
  -1.250   0.6134   0.00873   0.00256  -0.1611   0.5619   0.0204
  -1.000   0.6418   0.00863   0.00239  -0.1611   0.5491   0.0209
  -0.750   0.6701   0.00857   0.00225  -0.1610   0.5347   0.0214
  -0.500   0.6982   0.00854   0.00213  -0.1609   0.5182   0.0219
  -0.250   0.7262   0.00854   0.00203  -0.1608   0.4994   0.0225
   0.000   0.7538   0.00861   0.00197  -0.1606   0.4745   0.0231
   0.250   0.7805   0.00881   0.00195  -0.1603   0.4313   0.0242
   0.500   0.8070   0.00906   0.00201  -0.1600   0.3863   0.0256
   0.750   0.8335   0.00932   0.00208  -0.1597   0.3467   0.0269
   1.000   0.8605   0.00950   0.00214  -0.1595   0.3211   0.0287
   1.250   0.8876   0.00967   0.00223  -0.1592   0.3003   0.0319
   1.500   0.9147   0.00982   0.00233  -0.1590   0.2844   0.0354
   1.750   0.9418   0.00999   0.00243  -0.1587   0.2711   0.0389
   2.000   0.9690   0.01012   0.00253  -0.1585   0.2604   0.0418
   2.250   0.9962   0.01024   0.00263  -0.1583   0.2518   0.0443
   2.750   1.0503   0.01051   0.00283  -0.1578   0.2348   0.0477
   3.000   1.0775   0.01062   0.00291  -0.1576   0.2286   0.0511
   3.250   1.1047   0.01073   0.00301  -0.1573   0.2239   0.0536
   3.500   1.1318   0.01083   0.00311  -0.1571   0.2194   0.0553
   3.750   1.1586   0.01098   0.00323  -0.1568   0.2136   0.0566
   4.000   1.1854   0.01111   0.00335  -0.1565   0.2081   0.0600
   4.250   1.2124   0.01121   0.00348  -0.1563   0.2045   0.0650
   4.500   1.2392   0.01134   0.00362  -0.1560   0.2007   0.0772
   5.500   1.3431   0.01099   0.00458  -0.1549   0.1745   1.0000
   5.750   1.3685   0.01127   0.00479  -0.1545   0.1630   1.0000
   6.250   1.4152   0.01229   0.00551  -0.1530   0.1162   1.0000
   6.500   1.4388   0.01275   0.00589  -0.1522   0.1021   1.0000
   6.750   1.4623   0.01321   0.00627  -0.1515   0.0885   1.0000
   7.000   1.4801   0.01433   0.00708  -0.1499   0.0442   1.0000
   7.250   1.5038   0.01473   0.00746  -0.1492   0.0401   1.0000
   7.500   1.5274   0.01511   0.00783  -0.1484   0.0365   1.0000
   7.750   1.5512   0.01543   0.00817  -0.1477   0.0352   1.0000
   8.000   1.5749   0.01576   0.00852  -0.1470   0.0346   1.0000
   8.250   1.5982   0.01612   0.00891  -0.1463   0.0338   1.0000
   8.500   1.6212   0.01650   0.00930  -0.1455   0.0330   1.0000
   8.750   1.6437   0.01690   0.00971  -0.1446   0.0321   1.0000
   9.000   1.6658   0.01732   0.01015  -0.1437   0.0311   1.0000
   9.250   1.6875   0.01776   0.01062  -0.1427   0.0303   1.0000
   9.500   1.7086   0.01823   0.01112  -0.1417   0.0292   1.0000
   9.750   1.7292   0.01873   0.01165  -0.1405   0.0281   1.0000
  10.000   1.7500   0.01917   0.01213  -0.1394   0.0275   1.0000
  10.250   1.7709   0.01956   0.01256  -0.1384   0.0271   1.0000
  10.500   1.7914   0.01996   0.01301  -0.1372   0.0266   1.0000
  10.750   1.8112   0.02040   0.01348  -0.1360   0.0258   1.0000
  11.000   1.8301   0.02087   0.01399  -0.1347   0.0245   1.0000
  11.250   1.8473   0.02143   0.01458  -0.1331   0.0219   1.0000
  11.500   1.8612   0.02217   0.01527  -0.1310   0.0178   1.0000
  11.750   1.8713   0.02300   0.01608  -0.1283   0.0139   1.0000
  12.000   1.8773   0.02401   0.01709  -0.1249   0.0093   1.0000
  12.250   1.8831   0.02509   0.01821  -0.1217   0.0074   1.0000
  12.500   1.8902   0.02615   0.01933  -0.1189   0.0067   1.0000
  12.750   1.8970   0.02729   0.02053  -0.1162   0.0062   1.0000
  13.000   1.9037   0.02851   0.02183  -0.1137   0.0058   1.0000
  13.250   1.9109   0.02977   0.02317  -0.1116   0.0057   1.0000
  13.500   1.9172   0.03119   0.02467  -0.1095   0.0055   1.0000
  13.750   1.9225   0.03276   0.02634  -0.1076   0.0053   1.0000
  14.000   1.9267   0.03452   0.02819  -0.1058   0.0052   1.0000
  14.250   1.9300   0.03646   0.03022  -0.1041   0.0050   1.0000
  14.500   1.9318   0.03861   0.03247  -0.1026   0.0049   1.0000
  14.750   1.9322   0.04103   0.03497  -0.1012   0.0047   1.0000
  15.000   1.9313   0.04368   0.03773  -0.1001   0.0046   1.0000
  15.250   1.9286   0.04662   0.04078  -0.0990   0.0045   1.0000
  15.500   1.9243   0.04988   0.04415  -0.0982   0.0044   1.0000
  15.750   1.9176   0.05352   0.04791  -0.0976   0.0043   1.0000
  16.000   1.9096   0.05743   0.05194  -0.0972   0.0042   1.0000
  16.250   1.8994   0.06178   0.05642  -0.0971   0.0041   1.0000
  16.500   1.8906   0.06612   0.06088  -0.0972   0.0041   1.0000
  16.750   1.8805   0.07077   0.06566  -0.0976   0.0041   1.0000
  17.000   1.8691   0.07577   0.07079  -0.0983   0.0040   1.0000
  17.250   1.8565   0.08113   0.07627  -0.0993   0.0040   1.0000
  17.500   1.8409   0.08710   0.08237  -0.1006   0.0040   1.0000
  17.750   1.8244   0.09333   0.08874  -0.1022   0.0040   1.0000
  18.000   1.8066   0.09996   0.09552  -0.1042   0.0040   1.0000
  18.250   1.7873   0.10701   0.10270  -0.1065   0.0040   1.0000
  18.500   1.7670   0.11432   0.11015  -0.1091   0.0039   1.0000
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