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GOE 803 (HACKLINGER) AIRFOIL (goe803h-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 803 (HACKLINGER) AIRFOIL (goe803h-il)
Reynolds number: 500,000
Max Cl/Cd: 112.85 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe803h-il-500000.txt
Download as CSV file: xf-goe803h-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.2464   0.10171   0.09949  -0.0259   1.0000   0.0177
  -7.750  -0.2428   0.09934   0.09716  -0.0248   1.0000   0.0179
  -7.500  -0.2440   0.09772   0.09558  -0.0230   1.0000   0.0180
  -7.000  -0.2042   0.09115   0.08902  -0.0313   0.9932   0.0188
  -6.750  -0.1794   0.08745   0.08533  -0.0367   0.9862   0.0193
  -6.500  -0.1545   0.08379   0.08166  -0.0423   0.9764   0.0200
  -6.250  -0.1232   0.08000   0.07785  -0.0507   0.9623   0.0210
  -6.000  -0.0765   0.07562   0.07342  -0.0659   0.9492   0.0211
  -5.750  -0.0501   0.07102   0.06880  -0.0697   0.9402   0.0213
  -5.500  -0.0233   0.06742   0.06516  -0.0730   0.9298   0.0216
  -5.250   0.0068   0.06433   0.06199  -0.0780   0.9152   0.0221
  -5.000   0.0346   0.06148   0.05905  -0.0828   0.8991   0.0228
  -4.750   0.0622   0.05865   0.05612  -0.0875   0.8839   0.0235
  -4.500   0.1003   0.05541   0.05277  -0.0956   0.8694   0.0249
  -4.250   0.1565   0.05070   0.04790  -0.1099   0.8557   0.0253
  -4.000   0.1705   0.04828   0.04545  -0.1089   0.8425   0.0256
  -3.750   0.1939   0.04606   0.04318  -0.1106   0.8296   0.0261
  -3.500   0.2242   0.04372   0.04075  -0.1142   0.8171   0.0268
  -2.750   0.3535   0.03416   0.03072  -0.1338   0.7817   0.0305
  -2.500   0.3809   0.03239   0.02887  -0.1354   0.7701   0.0311
  -2.250   0.4138   0.03052   0.02686  -0.1381   0.7579   0.0322
  -2.000   0.4720   0.02770   0.02365  -0.1448   0.7463   0.0355
  -1.750   0.5037   0.02466   0.02050  -0.1477   0.7355   0.0362
  -1.500   0.5315   0.02348   0.01923  -0.1488   0.7255   0.0371
  -1.250   0.5634   0.02220   0.01785  -0.1503   0.7159   0.0389
  -1.000   0.6065   0.02092   0.01610  -0.1522   0.7074   0.0423
  -0.750   0.6412   0.01799   0.01303  -0.1549   0.6985   0.0434
  -0.500   0.6708   0.01704   0.01199  -0.1558   0.6899   0.0445
  -0.250   0.7020   0.01610   0.01091  -0.1565   0.6805   0.0467
   0.000   0.7344   0.01611   0.01056  -0.1563   0.6715   0.0506
   0.250   0.7724   0.01265   0.00668  -0.1586   0.6626   0.0407
   0.500   0.8039   0.01156   0.00533  -0.1591   0.6529   0.0401
   0.750   0.8334   0.01099   0.00455  -0.1591   0.6428   0.0413
   1.000   0.8625   0.01050   0.00395  -0.1592   0.6314   0.0436
   1.250   0.8904   0.01039   0.00383  -0.1590   0.6193   0.0468
   1.500   0.9184   0.01024   0.00359  -0.1588   0.6065   0.0499
   1.750   0.9467   0.00995   0.00326  -0.1588   0.5919   0.0543
   2.000   0.9739   0.00999   0.00324  -0.1585   0.5753   0.0599
   2.250   1.0017   0.00982   0.00304  -0.1584   0.5571   0.0652
   2.500   1.0286   0.00989   0.00304  -0.1581   0.5373   0.0707
   2.750   1.0556   0.00993   0.00300  -0.1578   0.5151   0.0755
   3.000   1.0818   0.01009   0.00304  -0.1574   0.4859   0.0802
   3.250   1.1072   0.01036   0.00315  -0.1569   0.4472   0.0852
   3.500   1.1318   0.01075   0.00331  -0.1562   0.4004   0.0932
   3.750   1.1562   0.01117   0.00359  -0.1556   0.3574   0.1344
   4.000   1.1782   0.01044   0.00404  -0.1549   0.3293   1.0000
   4.250   1.2032   0.01083   0.00427  -0.1543   0.3096   1.0000
   4.500   1.2284   0.01119   0.00451  -0.1538   0.2955   1.0000
   4.750   1.2538   0.01151   0.00475  -0.1533   0.2843   1.0000
   5.000   1.2794   0.01179   0.00500  -0.1528   0.2757   1.0000
   5.250   1.3045   0.01212   0.00526  -0.1523   0.2679   1.0000
   5.500   1.3301   0.01238   0.00551  -0.1518   0.2616   1.0000
   5.750   1.3553   0.01266   0.00577  -0.1513   0.2555   1.0000
   6.000   1.3799   0.01301   0.00609  -0.1507   0.2500   1.0000
   6.250   1.4056   0.01322   0.00634  -0.1502   0.2454   1.0000
   6.500   1.4305   0.01351   0.00662  -0.1497   0.2399   1.0000
   6.750   1.4545   0.01389   0.00697  -0.1490   0.2344   1.0000
   7.000   1.4800   0.01408   0.00722  -0.1485   0.2293   1.0000
   7.250   1.5043   0.01439   0.00753  -0.1479   0.2236   1.0000
   7.500   1.5281   0.01474   0.00788  -0.1472   0.2183   1.0000
   7.750   1.5531   0.01496   0.00817  -0.1467   0.2124   1.0000
   8.000   1.5764   0.01533   0.00852  -0.1459   0.2055   1.0000
   8.250   1.6009   0.01556   0.00881  -0.1454   0.1983   1.0000
   8.500   1.6238   0.01594   0.00917  -0.1446   0.1888   1.0000
   8.750   1.6469   0.01629   0.00950  -0.1438   0.1747   1.0000
   9.000   1.6680   0.01682   0.00992  -0.1428   0.1492   1.0000
   9.250   1.6837   0.01786   0.01071  -0.1410   0.1156   1.0000
   9.500   1.6977   0.01903   0.01169  -0.1390   0.0867   1.0000
   9.750   1.7098   0.02033   0.01278  -0.1366   0.0609   1.0000
  10.000   1.7254   0.02122   0.01365  -0.1348   0.0541   1.0000
  10.250   1.7413   0.02202   0.01449  -0.1329   0.0502   1.0000
  10.500   1.7567   0.02280   0.01533  -0.1310   0.0477   1.0000
  10.750   1.7695   0.02369   0.01627  -0.1288   0.0455   1.0000
  11.000   1.7784   0.02467   0.01731  -0.1259   0.0435   1.0000
  11.250   1.7852   0.02572   0.01844  -0.1227   0.0420   1.0000
  11.500   1.7959   0.02655   0.01938  -0.1202   0.0410   1.0000
  11.750   1.8049   0.02754   0.02047  -0.1177   0.0398   1.0000
  12.000   1.8124   0.02869   0.02172  -0.1151   0.0385   1.0000
  12.250   1.8177   0.03007   0.02319  -0.1126   0.0372   1.0000
  12.500   1.8196   0.03182   0.02502  -0.1100   0.0358   1.0000
  12.750   1.8159   0.03420   0.02750  -0.1073   0.0343   1.0000
  13.000   1.8253   0.03552   0.02894  -0.1058   0.0334   1.0000
  13.250   1.8347   0.03688   0.03041  -0.1045   0.0319   1.0000
  13.500   1.8412   0.03858   0.03220  -0.1032   0.0303   1.0000
  13.750   1.8418   0.04094   0.03463  -0.1017   0.0286   1.0000
  14.000   1.8403   0.04365   0.03744  -0.1005   0.0270   1.0000
  14.250   1.8559   0.04453   0.03841  -0.0998   0.0239   1.0000
  14.500   1.8579   0.04695   0.04087  -0.0989   0.0213   1.0000
  14.750   1.8610   0.04933   0.04328  -0.0982   0.0184   1.0000
  15.000   1.8557   0.05280   0.04683  -0.0975   0.0166   1.0000
  15.250   1.8494   0.05646   0.05061  -0.0970   0.0155   1.0000
  15.500   1.8404   0.06061   0.05486  -0.0967   0.0147   1.0000
  15.750   1.8270   0.06556   0.05992  -0.0969   0.0140   1.0000
  16.000   1.8133   0.07075   0.06525  -0.0973   0.0137   1.0000
  16.250   1.8008   0.07596   0.07062  -0.0981   0.0133   1.0000
  16.500   1.7867   0.08162   0.07644  -0.0992   0.0130   1.0000
  16.750   1.7711   0.08766   0.08263  -0.1006   0.0128   1.0000
  17.000   1.7545   0.09405   0.08917  -0.1023   0.0126   1.0000
  17.250   1.7369   0.10078   0.09605  -0.1044   0.0124   1.0000
  17.500   1.7189   0.10773   0.10314  -0.1067   0.0123   1.0000
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