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GOE 803 (HACKLINGER) AIRFOIL (goe803h-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 803 (HACKLINGER) AIRFOIL (goe803h-il)
Reynolds number: 100,000
Max Cl/Cd: 69.74 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe803h-il-100000-n5.txt
Download as CSV file: xf-goe803h-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.2358   0.10157   0.09681  -0.0242   1.0000   0.0382
  -7.000  -0.2431   0.10072   0.09608  -0.0220   1.0000   0.0387
  -6.750  -0.2501   0.10012   0.09560  -0.0207   0.9990   0.0392
  -6.500  -0.2118   0.09787   0.09331  -0.0354   0.9862   0.0398
  -6.250  -0.1913   0.09307   0.08853  -0.0380   0.9789   0.0402
  -6.000  -0.1723   0.08850   0.08396  -0.0391   0.9726   0.0408
  -5.750  -0.1486   0.08476   0.08021  -0.0430   0.9639   0.0416
  -5.500  -0.1233   0.08130   0.07673  -0.0478   0.9538   0.0426
  -5.250  -0.0944   0.07783   0.07323  -0.0537   0.9447   0.0438
  -5.000  -0.0592   0.07420   0.06956  -0.0612   0.9376   0.0454
  -4.750  -0.0146   0.07103   0.06630  -0.0726   0.9277   0.0470
  -4.500   0.0480   0.06742   0.06253  -0.0893   0.9208   0.0477
  -4.250   0.0558   0.06334   0.05851  -0.0857   0.9127   0.0486
  -4.000   0.0856   0.05995   0.05508  -0.0891   0.9070   0.0505
  -3.750   0.1210   0.05690   0.05198  -0.0949   0.8974   0.0526
  -3.500   0.1779   0.05358   0.04847  -0.1065   0.8912   0.0557
  -3.250   0.2466   0.05075   0.04531  -0.1208   0.8816   0.0568
  -3.000   0.2652   0.04692   0.04155  -0.1208   0.8742   0.0577
  -2.750   0.2916   0.04433   0.03894  -0.1226   0.8642   0.0592
  -2.500   0.3279   0.04187   0.03639  -0.1267   0.8559   0.0621
  -2.250   0.3849   0.03916   0.03337  -0.1357   0.8474   0.0687
  -2.000   0.4113   0.03691   0.03112  -0.1369   0.8383   0.0713
  -1.750   0.4500   0.03480   0.02886  -0.1406   0.8300   0.0751
  -1.500   0.4991   0.03269   0.02639  -0.1464   0.8206   0.0815
  -1.250   0.5415   0.02929   0.02269  -0.1496   0.8122   0.0547
  -1.000   0.5777   0.02725   0.02041  -0.1519   0.7997   0.0520
  -0.750   0.6141   0.02558   0.01842  -0.1536   0.7856   0.0537
  -0.500   0.6492   0.02388   0.01637  -0.1549   0.7695   0.0526
  -0.250   0.6834   0.02237   0.01446  -0.1558   0.7530   0.0516
   0.000   0.7163   0.02114   0.01287  -0.1564   0.7384   0.0517
   0.250   0.7479   0.02023   0.01162  -0.1568   0.7266   0.0537
   0.500   0.7793   0.01955   0.01051  -0.1569   0.7164   0.0569
   0.750   0.8084   0.01878   0.00963  -0.1570   0.7046   0.0586
   1.000   0.8368   0.01825   0.00899  -0.1568   0.6934   0.0610
   1.250   0.8650   0.01790   0.00846  -0.1565   0.6820   0.0665
   1.500   0.8928   0.01746   0.00797  -0.1562   0.6694   0.0714
   1.750   0.9200   0.01724   0.00769  -0.1558   0.6556   0.0790
   2.000   0.9472   0.01695   0.00739  -0.1554   0.6413   0.0853
   2.250   0.9738   0.01685   0.00720  -0.1548   0.6265   0.0939
   2.500   1.0006   0.01674   0.00704  -0.1543   0.6111   0.1004
   2.750   1.0272   0.01673   0.00700  -0.1537   0.5945   0.1126
   3.000   1.0536   0.01675   0.00697  -0.1532   0.5767   0.1273
   3.250   1.0781   0.01575   0.00719  -0.1526   0.5578   0.7267
   3.500   1.1010   0.01583   0.00716  -0.1511   0.5358   1.0000
   3.750   1.1256   0.01614   0.00726  -0.1501   0.5115   1.0000
   4.000   1.1497   0.01650   0.00743  -0.1492   0.4849   1.0000
   4.250   1.1734   0.01691   0.00765  -0.1482   0.4580   1.0000
   4.500   1.1967   0.01737   0.00795  -0.1472   0.4319   1.0000
   4.750   1.2199   0.01787   0.00829  -0.1463   0.4079   1.0000
   5.000   1.2427   0.01842   0.00867  -0.1453   0.3875   1.0000
   5.250   1.2655   0.01899   0.00911  -0.1443   0.3703   1.0000
   5.500   1.2883   0.01956   0.00961  -0.1434   0.3558   1.0000
   5.750   1.3114   0.02014   0.01012  -0.1425   0.3440   1.0000
   6.000   1.3343   0.02074   0.01065  -0.1416   0.3339   1.0000
   6.250   1.3565   0.02137   0.01120  -0.1406   0.3225   1.0000
   6.500   1.3788   0.02195   0.01180  -0.1397   0.3104   1.0000
   6.750   1.4007   0.02256   0.01238  -0.1387   0.2995   1.0000
   7.000   1.4220   0.02323   0.01297  -0.1377   0.2900   1.0000
   7.250   1.4441   0.02378   0.01362  -0.1368   0.2802   1.0000
   7.500   1.4651   0.02444   0.01428  -0.1357   0.2717   1.0000
   7.750   1.4865   0.02502   0.01496  -0.1347   0.2632   1.0000
   8.000   1.5072   0.02570   0.01565  -0.1336   0.2564   1.0000
   8.250   1.5284   0.02630   0.01640  -0.1326   0.2494   1.0000
   8.500   1.5482   0.02700   0.01713  -0.1314   0.2430   1.0000
   8.750   1.5683   0.02763   0.01795  -0.1302   0.2356   1.0000
   9.000   1.5867   0.02832   0.01873  -0.1288   0.2280   1.0000
   9.250   1.6051   0.02901   0.01957  -0.1274   0.2203   1.0000
   9.500   1.6213   0.02974   0.02039  -0.1258   0.2113   1.0000
   9.750   1.6377   0.03043   0.02131  -0.1241   0.2013   1.0000
  10.000   1.6522   0.03122   0.02221  -0.1223   0.1924   1.0000
  10.250   1.6660   0.03201   0.02318  -0.1203   0.1814   1.0000
  10.500   1.6783   0.03285   0.02419  -0.1182   0.1681   1.0000
  10.750   1.6858   0.03384   0.02527  -0.1155   0.1530   1.0000
  11.000   1.6901   0.03511   0.02658  -0.1125   0.1370   1.0000
  11.250   1.6915   0.03674   0.02819  -0.1096   0.1227   1.0000
  11.500   1.6906   0.03871   0.03017  -0.1067   0.1105   1.0000
  11.750   1.6882   0.04099   0.03247  -0.1041   0.1001   1.0000
  12.000   1.6870   0.04332   0.03492  -0.1018   0.0909   1.0000
  12.250   1.6831   0.04602   0.03770  -0.0998   0.0844   1.0000
  12.500   1.6797   0.04882   0.04062  -0.0981   0.0789   1.0000
  12.750   1.6729   0.05210   0.04401  -0.0967   0.0752   1.0000
  13.000   1.6680   0.05535   0.04742  -0.0956   0.0722   1.0000
  13.250   1.6618   0.05887   0.05111  -0.0948   0.0694   1.0000
  13.500   1.6532   0.06284   0.05520  -0.0944   0.0669   1.0000
  13.750   1.6417   0.06731   0.05978  -0.0943   0.0649   1.0000
  14.000   1.6313   0.07180   0.06441  -0.0944   0.0629   1.0000
  14.250   1.6216   0.07635   0.06916  -0.0948   0.0608   1.0000
  14.500   1.6101   0.08135   0.07432  -0.0955   0.0589   1.0000
  14.750   1.5973   0.08673   0.07986  -0.0967   0.0573   1.0000
  15.000   1.5838   0.09242   0.08566  -0.0981   0.0559   1.0000
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