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GOE 803 (HACKLINGER) AIRFOIL (goe803h-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 803 (HACKLINGER) AIRFOIL (goe803h-il)
Reynolds number: 200,000
Max Cl/Cd: 95.63 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe803h-il-200000.txt
Download as CSV file: xf-goe803h-il-200000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.2517   0.10439   0.10105  -0.0244   1.0000   0.0299
  -7.250  -0.2674   0.10460   0.10138  -0.0211   1.0000   0.0299
  -7.000  -0.2825   0.10485   0.10174  -0.0186   0.9996   0.0299
  -6.750  -0.2603   0.09927   0.09616  -0.0213   0.9966   0.0302
  -6.500  -0.2387   0.09439   0.09127  -0.0233   0.9938   0.0306
  -6.250  -0.2115   0.09031   0.08718  -0.0286   0.9881   0.0314
  -6.000  -0.1807   0.08638   0.08323  -0.0353   0.9828   0.0325
  -5.750  -0.1484   0.08258   0.07941  -0.0427   0.9751   0.0341
  -5.500  -0.0926   0.07948   0.07623  -0.0604   0.9650   0.0354
  -5.250  -0.0476   0.07469   0.07140  -0.0719   0.9602   0.0357
  -5.000  -0.0336   0.07043   0.06716  -0.0703   0.9534   0.0362
  -4.750  -0.0031   0.06655   0.06327  -0.0745   0.9488   0.0370
  -4.500   0.0349   0.06288   0.05956  -0.0814   0.9437   0.0383
  -4.250   0.0760   0.05931   0.05594  -0.0893   0.9362   0.0402
  -4.000   0.1617   0.05482   0.05123  -0.1113   0.9316   0.0426
  -3.750   0.1785   0.05139   0.04783  -0.1106   0.9225   0.0433
  -3.500   0.2130   0.04819   0.04458  -0.1147   0.9167   0.0445
  -3.250   0.2493   0.04543   0.04176  -0.1197   0.9063   0.0462
  -3.000   0.3251   0.04275   0.03873  -0.1342   0.8985   0.0505
  -2.750   0.3616   0.03902   0.03489  -0.1389   0.8879   0.0513
  -2.500   0.3825   0.03661   0.03249  -0.1391   0.8758   0.0523
  -2.250   0.4112   0.03467   0.03046  -0.1407   0.8642   0.0547
  -2.000   0.4758   0.03344   0.02862  -0.1489   0.8534   0.0609
  -1.750   0.4962   0.02999   0.02529  -0.1495   0.8405   0.0622
  -1.500   0.5229   0.02826   0.02351  -0.1503   0.8277   0.0643
  -1.250   0.5565   0.02669   0.02175  -0.1519   0.8146   0.0689
  -1.000   0.5963   0.02470   0.01942  -0.1547   0.8028   0.0747
  -0.750   0.6249   0.02337   0.01802  -0.1554   0.7912   0.0789
  -0.500   0.6595   0.02201   0.01644  -0.1571   0.7810   0.0895
  -0.250   0.6925   0.02101   0.01518  -0.1582   0.7719   0.1028
   0.000   0.7233   0.02014   0.01414  -0.1589   0.7610   0.1175
   0.250   0.7525   0.01913   0.01306  -0.1595   0.7504   0.1337
   1.000   0.8538   0.01549   0.00832  -0.1602   0.7185   0.0814
   1.250   0.8843   0.01467   0.00719  -0.1600   0.7084   0.0772
   1.500   0.9124   0.01427   0.00671  -0.1597   0.6962   0.0818
   1.750   0.9405   0.01400   0.00629  -0.1593   0.6842   0.0855
   2.000   0.9685   0.01350   0.00581  -0.1591   0.6722   0.0930
   2.250   0.9959   0.01334   0.00558  -0.1586   0.6595   0.0999
   2.500   1.0232   0.01308   0.00538  -0.1583   0.6452   0.1093
   2.750   1.0503   0.01296   0.00526  -0.1578   0.6296   0.1183
   3.000   1.0770   0.01291   0.00519  -0.1573   0.6125   0.1311
   3.250   1.1039   0.01282   0.00519  -0.1569   0.5920   0.1709
   3.500   1.1255   0.01180   0.00523  -0.1553   0.5702   1.0000
   3.750   1.1504   0.01203   0.00527  -0.1544   0.5437   1.0000
   4.000   1.1744   0.01235   0.00540  -0.1534   0.5113   1.0000
   4.250   1.1973   0.01279   0.00558  -0.1522   0.4727   1.0000
   4.500   1.2196   0.01334   0.00587  -0.1511   0.4335   1.0000
   4.750   1.2420   0.01395   0.00622  -0.1500   0.4020   1.0000
   5.000   1.2646   0.01456   0.00664  -0.1490   0.3782   1.0000
   5.250   1.2874   0.01517   0.00706  -0.1481   0.3601   1.0000
   5.500   1.3106   0.01572   0.00748  -0.1473   0.3446   1.0000
   5.750   1.3342   0.01622   0.00790  -0.1465   0.3308   1.0000
   6.000   1.3580   0.01669   0.00836  -0.1458   0.3199   1.0000
   6.250   1.3814   0.01726   0.00884  -0.1450   0.3115   1.0000
   6.500   1.4056   0.01769   0.00931  -0.1443   0.3039   1.0000
   6.750   1.4289   0.01832   0.00983  -0.1436   0.2972   1.0000
   7.000   1.4529   0.01870   0.01034  -0.1429   0.2900   1.0000
   7.250   1.4761   0.01925   0.01086  -0.1421   0.2834   1.0000
   7.500   1.4993   0.01972   0.01140  -0.1413   0.2765   1.0000
   7.750   1.5219   0.02019   0.01190  -0.1404   0.2691   1.0000
   8.000   1.5445   0.02074   0.01250  -0.1396   0.2625   1.0000
   8.250   1.5666   0.02116   0.01302  -0.1386   0.2553   1.0000
   8.500   1.5880   0.02174   0.01361  -0.1376   0.2481   1.0000
   8.750   1.6087   0.02211   0.01410  -0.1365   0.2393   1.0000
   9.000   1.6291   0.02266   0.01472  -0.1353   0.2319   1.0000
   9.250   1.6489   0.02307   0.01525  -0.1340   0.2232   1.0000
   9.500   1.6681   0.02357   0.01586  -0.1327   0.2148   1.0000
   9.750   1.6856   0.02407   0.01642  -0.1311   0.2050   1.0000
  10.000   1.7036   0.02445   0.01698  -0.1295   0.1922   1.0000
  10.250   1.7195   0.02494   0.01755  -0.1277   0.1756   1.0000
  10.500   1.7324   0.02567   0.01825  -0.1256   0.1468   1.0000
  10.750   1.7335   0.02722   0.01959  -0.1218   0.1173   1.0000
  11.000   1.7315   0.02901   0.02127  -0.1177   0.0992   1.0000
  11.250   1.7321   0.03072   0.02299  -0.1142   0.0881   1.0000
  11.500   1.7325   0.03253   0.02480  -0.1110   0.0811   1.0000
  11.750   1.7353   0.03426   0.02660  -0.1084   0.0755   1.0000
  12.000   1.7327   0.03654   0.02888  -0.1057   0.0715   1.0000
  12.250   1.7368   0.03837   0.03087  -0.1037   0.0680   1.0000
  12.500   1.7374   0.04061   0.03319  -0.1019   0.0646   1.0000
  12.750   1.7327   0.04346   0.03609  -0.1000   0.0619   1.0000
  13.000   1.7311   0.04615   0.03891  -0.0984   0.0598   1.0000
  13.250   1.7312   0.04875   0.04168  -0.0972   0.0576   1.0000
  13.500   1.7290   0.05170   0.04475  -0.0961   0.0555   1.0000
  13.750   1.7233   0.05511   0.04825  -0.0952   0.0535   1.0000
  14.000   1.7137   0.05902   0.05220  -0.0942   0.0517   1.0000
  14.250   1.7093   0.06247   0.05581  -0.0935   0.0500   1.0000
  14.500   1.7047   0.06604   0.05957  -0.0932   0.0480   1.0000
  14.750   1.6978   0.07000   0.06366  -0.0931   0.0460   1.0000
  15.000   1.6886   0.07432   0.06806  -0.0932   0.0442   1.0000
  15.250   1.6779   0.07856   0.07228  -0.0924   0.0420   1.0000
  15.500   1.6700   0.08318   0.07716  -0.0932   0.0404   1.0000
  15.750   1.6610   0.08800   0.08215  -0.0940   0.0384   1.0000
  16.000   1.6524   0.09267   0.08689  -0.0948   0.0365   1.0000
  16.250   1.6449   0.09639   0.09054  -0.0937   0.0340   1.0000
  16.500   1.6347   0.10188   0.09629  -0.0955   0.0327   1.0000
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