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GOE 803 (HACKLINGER) AIRFOIL (goe803h-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 803 (HACKLINGER) AIRFOIL (goe803h-il)
Reynolds number: 1,000,000
Max Cl/Cd: 128.65 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe803h-il-1000000.txt
Download as CSV file: xf-goe803h-il-1000000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.2533   0.10504   0.10342  -0.0244   1.0000   0.0133
  -8.250  -0.2491   0.10268   0.10108  -0.0244   1.0000   0.0139
  -8.000  -0.2454   0.10031   0.09873  -0.0247   0.9999   0.0143
  -7.750  -0.1047   0.07682   0.07528  -0.0497   0.9582   0.0145
  -7.500  -0.0812   0.07215   0.07058  -0.0536   0.9413   0.0147
  -7.250  -0.0645   0.06879   0.06709  -0.0563   0.9134   0.0148
  -7.000  -0.0554   0.06629   0.06450  -0.0571   0.8922   0.0150
  -6.750  -0.0467   0.06382   0.06197  -0.0579   0.8760   0.0153
  -6.500  -0.0378   0.06128   0.05939  -0.0588   0.8614   0.0156
  -6.250  -0.0270   0.05854   0.05660  -0.0604   0.8475   0.0162
  -6.000  -0.0137   0.05552   0.05353  -0.0629   0.8328   0.0169
  -5.750   0.0056   0.05193   0.04987  -0.0685   0.8186   0.0175
  -5.500   0.0265   0.04831   0.04619  -0.0742   0.8057   0.0175
  -5.250   0.0491   0.04469   0.04251  -0.0796   0.7923   0.0176
  -5.000   0.0681   0.04062   0.03837  -0.0832   0.7796   0.0177
  -4.750   0.0842   0.03806   0.03576  -0.0840   0.7675   0.0179
  -4.500   0.1057   0.03551   0.03314  -0.0867   0.7567   0.0181
  -4.250   0.1308   0.03281   0.03040  -0.0905   0.7471   0.0184
  -4.000   0.1579   0.03014   0.02767  -0.0947   0.7376   0.0190
  -3.750   0.2038   0.02618   0.02359  -0.1049   0.7295   0.0210
  -3.500   0.2456   0.02259   0.01988  -0.1128   0.7209   0.0211
  -3.250   0.2776   0.01898   0.01617  -0.1180   0.7117   0.0214
  -3.000   0.3035   0.01735   0.01448  -0.1198   0.7014   0.0217
  -2.750   0.3330   0.01579   0.01284  -0.1225   0.6915   0.0222
  -2.500   0.3677   0.01395   0.01091  -0.1264   0.6832   0.0231
  -2.250   0.4227   0.01110   0.00780  -0.1344   0.6773   0.0252
  -2.000   0.4583   0.00882   0.00538  -0.1386   0.6709   0.0259
  -1.750   0.4877   0.00804   0.00453  -0.1401   0.6629   0.0265
  -1.500   0.5207   0.00715   0.00352  -0.1422   0.6556   0.0276
  -1.250   0.5651   0.00588   0.00190  -0.1456   0.6487   0.0300
  -1.000   0.6407   0.00972   0.00436  -0.1605   0.6539   0.0257
  -0.500   0.6993   0.00887   0.00327  -0.1609   0.6349   0.0269
  -0.250   0.7278   0.00874   0.00307  -0.1609   0.6249   0.0280
   0.000   0.7564   0.00854   0.00277  -0.1609   0.6135   0.0292
   0.250   0.7850   0.00839   0.00255  -0.1608   0.6017   0.0300
   0.500   0.8138   0.00814   0.00223  -0.1609   0.5892   0.0318
   0.750   0.8418   0.00815   0.00220  -0.1607   0.5749   0.0334
   1.000   0.8696   0.00818   0.00215  -0.1605   0.5588   0.0353
   1.250   0.8974   0.00819   0.00212  -0.1604   0.5415   0.0384
   1.500   0.9247   0.00832   0.00219  -0.1601   0.5235   0.0417
   1.750   0.9522   0.00837   0.00216  -0.1600   0.5029   0.0457
   2.000   0.9789   0.00856   0.00224  -0.1596   0.4741   0.0493
   2.250   1.0054   0.00876   0.00227  -0.1593   0.4380   0.0528
   2.500   1.0313   0.00905   0.00239  -0.1590   0.3960   0.0564
   2.750   1.0568   0.00942   0.00255  -0.1585   0.3546   0.0593
   3.000   1.0826   0.00972   0.00269  -0.1581   0.3224   0.0620
   3.250   1.1090   0.00995   0.00280  -0.1578   0.2995   0.0658
   3.500   1.1354   0.01016   0.00293  -0.1575   0.2832   0.0694
   3.750   1.1620   0.01033   0.00306  -0.1572   0.2714   0.0724
   4.000   1.1888   0.01049   0.00320  -0.1569   0.2616   0.0829
   4.250   1.2141   0.00950   0.00365  -0.1569   0.2528   1.0000
   4.500   1.2407   0.00969   0.00379  -0.1565   0.2463   1.0000
   4.750   1.2671   0.00989   0.00394  -0.1562   0.2399   1.0000
   5.000   1.2933   0.01012   0.00413  -0.1558   0.2341   1.0000
   5.250   1.3199   0.01027   0.00428  -0.1555   0.2305   1.0000
   5.500   1.3460   0.01047   0.00446  -0.1551   0.2257   1.0000
   5.750   1.3717   0.01073   0.00468  -0.1547   0.2198   1.0000
   6.000   1.3981   0.01088   0.00485  -0.1544   0.2166   1.0000
   6.250   1.4242   0.01107   0.00503  -0.1540   0.2125   1.0000
   6.500   1.4497   0.01130   0.00525  -0.1536   0.2074   1.0000
   6.750   1.4753   0.01152   0.00547  -0.1531   0.2023   1.0000
   7.000   1.5010   0.01172   0.00566  -0.1527   0.1961   1.0000
   7.250   1.5258   0.01200   0.00591  -0.1522   0.1885   1.0000
   7.500   1.5511   0.01223   0.00613  -0.1517   0.1801   1.0000
   7.750   1.5749   0.01259   0.00642  -0.1511   0.1639   1.0000
   8.000   1.5943   0.01344   0.00699  -0.1498   0.1253   1.0000
   8.250   1.6134   0.01429   0.00765  -0.1484   0.0989   1.0000
   8.500   1.6292   0.01547   0.00855  -0.1466   0.0597   1.0000
   8.750   1.6485   0.01624   0.00923  -0.1452   0.0468   1.0000
   9.000   1.6696   0.01680   0.00978  -0.1441   0.0422   1.0000
   9.250   1.6916   0.01722   0.01023  -0.1432   0.0410   1.0000
   9.500   1.7129   0.01769   0.01074  -0.1421   0.0398   1.0000
   9.750   1.7333   0.01822   0.01130  -0.1409   0.0384   1.0000
  10.000   1.7527   0.01882   0.01192  -0.1396   0.0366   1.0000
  10.250   1.7713   0.01945   0.01260  -0.1382   0.0350   1.0000
  10.500   1.7899   0.02004   0.01325  -0.1367   0.0340   1.0000
  10.750   1.8095   0.02048   0.01375  -0.1355   0.0334   1.0000
  11.000   1.8282   0.02097   0.01429  -0.1341   0.0324   1.0000
  11.250   1.8457   0.02152   0.01488  -0.1325   0.0313   1.0000
  11.500   1.8607   0.02216   0.01556  -0.1306   0.0299   1.0000
  11.750   1.8721   0.02292   0.01636  -0.1280   0.0285   1.0000
  12.000   1.8812   0.02373   0.01723  -0.1251   0.0273   1.0000
  12.250   1.8971   0.02414   0.01769  -0.1233   0.0265   1.0000
  12.500   1.9111   0.02469   0.01828  -0.1214   0.0248   1.0000
  12.750   1.9213   0.02552   0.01911  -0.1190   0.0222   1.0000
  13.000   1.9313   0.02641   0.02000  -0.1167   0.0186   1.0000
  13.250   1.9346   0.02785   0.02140  -0.1138   0.0137   1.0000
  13.750   1.9399   0.03117   0.02483  -0.1088   0.0098   1.0000
  14.000   1.9415   0.03308   0.02681  -0.1066   0.0090   1.0000
  14.250   1.9417   0.03525   0.02907  -0.1045   0.0084   1.0000
  14.500   1.9440   0.03731   0.03123  -0.1029   0.0081   1.0000
  14.750   1.9445   0.03964   0.03367  -0.1014   0.0078   1.0000
  15.000   1.9435   0.04226   0.03639  -0.1001   0.0075   1.0000
  15.250   1.9405   0.04519   0.03943  -0.0989   0.0073   1.0000
  15.500   1.9359   0.04842   0.04276  -0.0980   0.0072   1.0000
  15.750   1.9288   0.05206   0.04653  -0.0973   0.0070   1.0000
  16.000   1.9203   0.05599   0.05057  -0.0968   0.0068   1.0000
  16.250   1.9087   0.06048   0.05519  -0.0966   0.0067   1.0000
  16.500   1.8953   0.06542   0.06027  -0.0968   0.0066   1.0000
  16.750   1.8795   0.07092   0.06592  -0.0973   0.0065   1.0000
  17.000   1.8625   0.07681   0.07196  -0.0983   0.0064   1.0000
  17.250   1.8456   0.08293   0.07821  -0.0995   0.0064   1.0000
  17.500   1.8286   0.08918   0.08461  -0.1011   0.0064   1.0000
  17.750   1.8103   0.09582   0.09139  -0.1029   0.0063   1.0000
  18.000   1.7910   0.10281   0.09853  -0.1051   0.0063   1.0000
  18.250   1.7699   0.11026   0.10611  -0.1076   0.0063   1.0000
  18.500   1.7492   0.11773   0.11373  -0.1104   0.0063   1.0000
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