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GOE 803 (HACKLINGER) AIRFOIL (goe803h-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 803 (HACKLINGER) AIRFOIL (goe803h-il)
Reynolds number: 200,000
Max Cl/Cd: 85.78 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe803h-il-200000-n5.txt
Download as CSV file: xf-goe803h-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.2404   0.10382   0.10029  -0.0265   1.0000   0.0238
  -7.750  -0.2372   0.10160   0.09812  -0.0258   1.0000   0.0240
  -7.500  -0.2364   0.09974   0.09633  -0.0248   1.0000   0.0242
  -7.250  -0.2263   0.09715   0.09377  -0.0263   0.9968   0.0246
  -7.000  -0.2062   0.09376   0.09038  -0.0306   0.9881   0.0251
  -6.500  -0.1647   0.08704   0.08367  -0.0395   0.9609   0.0266
  -6.250  -0.1373   0.08352   0.08012  -0.0464   0.9474   0.0275
  -6.000  -0.1006   0.07989   0.07643  -0.0571   0.9351   0.0279
  -5.750  -0.0682   0.07569   0.07220  -0.0647   0.9252   0.0282
  -5.500  -0.0467   0.07200   0.06849  -0.0662   0.9168   0.0288
  -5.250  -0.0160   0.06860   0.06503  -0.0717   0.9071   0.0296
  -5.000   0.0141   0.06541   0.06177  -0.0773   0.8952   0.0304
  -4.750   0.0449   0.06229   0.05859  -0.0830   0.8832   0.0314
  -4.500   0.0823   0.05914   0.05534  -0.0908   0.8713   0.0328
  -4.250   0.1350   0.05563   0.05166  -0.1036   0.8599   0.0333
  -4.000   0.1788   0.05213   0.04802  -0.1123   0.8484   0.0335
  -3.750   0.1932   0.04919   0.04510  -0.1115   0.8376   0.0338
  -3.500   0.2125   0.04699   0.04286  -0.1117   0.8275   0.0348
  -3.250   0.2433   0.04471   0.04051  -0.1152   0.8168   0.0369
  -3.000   0.2986   0.04163   0.03721  -0.1250   0.8071   0.0394
  -2.750   0.3482   0.03856   0.03387  -0.1324   0.7971   0.0398
  -2.500   0.3875   0.03574   0.03084  -0.1368   0.7855   0.0398
  -2.250   0.4239   0.03305   0.02795  -0.1402   0.7737   0.0399
  -2.000   0.4564   0.02937   0.02411  -0.1431   0.7620   0.0332
  -1.500   0.5342   0.02435   0.01849  -0.1494   0.7370   0.0333
  -1.250   0.5670   0.02264   0.01657  -0.1511   0.7236   0.0329
  -1.000   0.6024   0.02074   0.01435  -0.1530   0.7103   0.0327
  -0.750   0.6386   0.01875   0.01193  -0.1547   0.6983   0.0328
  -0.500   0.6723   0.01727   0.01008  -0.1559   0.6874   0.0340
  -0.250   0.7005   0.01697   0.00972  -0.1561   0.6769   0.0358
   0.000   0.7319   0.01600   0.00845  -0.1566   0.6665   0.0368
   0.250   0.7627   0.01510   0.00725  -0.1569   0.6553   0.0378
   0.500   0.7927   0.01437   0.00623  -0.1570   0.6444   0.0394
   0.750   0.8210   0.01403   0.00580  -0.1569   0.6332   0.0415
   1.000   0.8487   0.01386   0.00555  -0.1567   0.6210   0.0450
   1.250   0.8770   0.01353   0.00507  -0.1565   0.6080   0.0478
   1.500   0.9047   0.01328   0.00483  -0.1564   0.5941   0.0511
   1.750   0.9318   0.01326   0.00470  -0.1560   0.5790   0.0568
   2.000   0.9590   0.01311   0.00457  -0.1558   0.5622   0.0628
   2.250   0.9857   0.01313   0.00449  -0.1554   0.5432   0.0680
   2.500   1.0121   0.01311   0.00444  -0.1551   0.5221   0.0741
   2.750   1.0383   0.01322   0.00445  -0.1546   0.4985   0.0782
   3.000   1.0642   0.01338   0.00450  -0.1541   0.4736   0.0835
   3.250   1.0894   0.01361   0.00461  -0.1535   0.4460   0.0923
   3.500   1.1143   0.01388   0.00479  -0.1529   0.4162   0.1081
   4.000   1.1589   0.01351   0.00536  -0.1508   0.3605   1.0000
   4.250   1.1826   0.01400   0.00565  -0.1500   0.3381   1.0000
   4.500   1.2065   0.01447   0.00597  -0.1493   0.3201   1.0000
   4.750   1.2304   0.01493   0.00630  -0.1486   0.3047   1.0000
   5.000   1.2545   0.01536   0.00663  -0.1479   0.2917   1.0000
   5.250   1.2789   0.01575   0.00697  -0.1472   0.2818   1.0000
   5.500   1.3026   0.01619   0.00736  -0.1465   0.2735   1.0000
   5.750   1.3271   0.01655   0.00771  -0.1459   0.2657   1.0000
   6.000   1.3503   0.01702   0.00811  -0.1451   0.2579   1.0000
   6.250   1.3746   0.01736   0.00849  -0.1444   0.2503   1.0000
   6.500   1.3978   0.01781   0.00892  -0.1436   0.2435   1.0000
   6.750   1.4215   0.01819   0.00934  -0.1429   0.2380   1.0000
   7.000   1.4450   0.01859   0.00977  -0.1421   0.2323   1.0000
   7.250   1.4675   0.01905   0.01024  -0.1413   0.2272   1.0000
   7.500   1.4906   0.01946   0.01073  -0.1405   0.2225   1.0000
   7.750   1.5136   0.01986   0.01121  -0.1396   0.2170   1.0000
   8.000   1.5349   0.02037   0.01172  -0.1386   0.2104   1.0000
   8.250   1.5576   0.02076   0.01221  -0.1377   0.2039   1.0000
   8.500   1.5788   0.02123   0.01276  -0.1367   0.1967   1.0000
   8.750   1.6003   0.02168   0.01329  -0.1357   0.1885   1.0000
   9.000   1.6206   0.02218   0.01383  -0.1345   0.1767   1.0000
   9.250   1.6402   0.02272   0.01440  -0.1333   0.1606   1.0000
   9.500   1.6574   0.02345   0.01509  -0.1318   0.1416   1.0000
   9.750   1.6716   0.02439   0.01595  -0.1298   0.1232   1.0000
  10.000   1.6841   0.02546   0.01697  -0.1277   0.1067   1.0000
  10.250   1.6944   0.02665   0.01811  -0.1252   0.0897   1.0000
  10.500   1.7006   0.02794   0.01935  -0.1222   0.0731   1.0000
  10.750   1.7054   0.02930   0.02069  -0.1191   0.0626   1.0000
  11.000   1.7106   0.03067   0.02209  -0.1161   0.0566   1.0000
  11.250   1.7156   0.03211   0.02358  -0.1134   0.0526   1.0000
  11.500   1.7205   0.03361   0.02517  -0.1109   0.0496   1.0000
  11.750   1.7233   0.03537   0.02702  -0.1085   0.0470   1.0000
  12.000   1.7243   0.03739   0.02911  -0.1062   0.0450   1.0000
  12.250   1.7288   0.03918   0.03108  -0.1044   0.0438   1.0000
  12.500   1.7320   0.04118   0.03324  -0.1028   0.0425   1.0000
  12.750   1.7335   0.04343   0.03564  -0.1013   0.0411   1.0000
  13.000   1.7331   0.04599   0.03834  -0.0999   0.0397   1.0000
  13.250   1.7304   0.04892   0.04139  -0.0988   0.0383   1.0000
  13.500   1.7249   0.05229   0.04489  -0.0979   0.0370   1.0000
  13.750   1.7169   0.05610   0.04883  -0.0972   0.0360   1.0000
  14.000   1.7134   0.05946   0.05236  -0.0967   0.0352   1.0000
  14.250   1.7107   0.06281   0.05589  -0.0965   0.0343   1.0000
  14.500   1.7063   0.06648   0.05974  -0.0964   0.0333   1.0000
  14.750   1.6999   0.07050   0.06393  -0.0965   0.0323   1.0000
  15.000   1.6922   0.07488   0.06847  -0.0969   0.0313   1.0000
  15.250   1.6829   0.07966   0.07341  -0.0977   0.0303   1.0000
  15.500   1.6714   0.08495   0.07884  -0.0988   0.0295   1.0000
  15.750   1.6578   0.09072   0.08475  -0.1003   0.0287   1.0000
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