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GOE 229 (MVA H.39) AIRFOIL (goe229-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 229 (MVA H.39) AIRFOIL (goe229-il)
Reynolds number: 200,000
Max Cl/Cd: 53.83 at α=2.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe229-il-200000.txt
Download as CSV file: xf-goe229-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 229 (MVA H.39) 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.0866   0.10606   0.10277  -0.1014   0.9627   0.0809
 -11.250  -0.1144   0.09698   0.09372  -0.1148   0.9560   0.0897
 -11.000  -0.0751   0.09598   0.09270  -0.1111   0.9541   0.0925
 -10.750  -0.0545   0.09453   0.09123  -0.1107   0.9466   0.0957
 -10.500  -0.0902   0.08438   0.08114  -0.1220   0.9384   0.1056
 -10.250  -0.0589   0.08487   0.08159  -0.1178   0.9311   0.1076
 -10.000  -0.0416   0.08321   0.07991  -0.1172   0.9240   0.1109
  -9.750  -0.2719   0.04454   0.03950  -0.1558   0.8914   0.0541
  -9.500  -0.2611   0.03811   0.03293  -0.1565   0.8862   0.0499
  -9.250  -0.2531   0.03443   0.02866  -0.1568   0.8770   0.0473
  -9.000  -0.2306   0.03194   0.02578  -0.1576   0.8722   0.0470
  -8.750  -0.2113   0.03053   0.02433  -0.1571   0.8642   0.0482
  -8.500  -0.1872   0.02902   0.02265  -0.1573   0.8584   0.0497
  -8.250  -0.1607   0.02746   0.02088  -0.1576   0.8539   0.0506
  -8.000  -0.1397   0.02629   0.01958  -0.1568   0.8456   0.0513
  -7.750  -0.1127   0.02509   0.01822  -0.1568   0.8404   0.0524
  -7.500  -0.0875   0.02436   0.01734  -0.1566   0.8336   0.0539
  -7.250  -0.0645   0.02301   0.01596  -0.1559   0.8267   0.0553
  -7.000  -0.0382   0.02181   0.01477  -0.1557   0.8219   0.0569
  -6.750  -0.0163   0.02109   0.01409  -0.1551   0.8135   0.0586
  -6.500   0.0110   0.02030   0.01326  -0.1554   0.8076   0.0613
  -6.250   0.0374   0.01966   0.01255  -0.1556   0.8008   0.0635
  -6.000   0.0645   0.01903   0.01185  -0.1560   0.7934   0.0651
  -5.750   0.0953   0.01805   0.01078  -0.1574   0.7881   0.0691
  -5.500   0.1211   0.01753   0.01023  -0.1577   0.7789   0.0739
  -5.250   0.1525   0.01690   0.00950  -0.1588   0.7728   0.0813
  -5.000   0.1799   0.01634   0.00898  -0.1592   0.7642   0.1040
  -4.750   0.2101   0.01478   0.00831  -0.1616   0.7575   0.3285
  -4.500   0.2385   0.01509   0.00858  -0.1615   0.7495   0.3715
  -4.250   0.2681   0.01537   0.00872  -0.1615   0.7416   0.3929
  -4.000   0.2958   0.01566   0.00895  -0.1611   0.7327   0.4059
  -3.750   0.3244   0.01593   0.00916  -0.1607   0.7242   0.4177
  -3.500   0.3514   0.01613   0.00926  -0.1604   0.7141   0.4287
  -3.250   0.3806   0.01625   0.00928  -0.1602   0.7055   0.4360
  -3.000   0.4068   0.01634   0.00927  -0.1599   0.6945   0.4450
  -2.750   0.4339   0.01657   0.00950  -0.1593   0.6859   0.4529
  -2.500   0.4612   0.01666   0.00948  -0.1592   0.6764   0.4622
  -2.250   0.4873   0.01690   0.00975  -0.1584   0.6679   0.4697
  -2.000   0.5152   0.01692   0.00959  -0.1584   0.6576   0.4782
  -1.750   0.5400   0.01684   0.00952  -0.1577   0.6457   0.4825
  -1.500   0.5662   0.01680   0.00939  -0.1573   0.6342   0.4870
  -1.250   0.5933   0.01672   0.00917  -0.1573   0.6236   0.4920
  -1.000   0.6201   0.01661   0.00894  -0.1574   0.6126   0.4965
  -0.750   0.6459   0.01654   0.00882  -0.1570   0.6021   0.4997
  -0.500   0.6714   0.01652   0.00870  -0.1566   0.5904   0.5032
  -0.250   0.6970   0.01649   0.00862  -0.1564   0.5793   0.5071
   0.000   0.7237   0.01650   0.00849  -0.1564   0.5697   0.5118
   0.250   0.7491   0.01648   0.00839  -0.1561   0.5589   0.5154
   0.500   0.7734   0.01650   0.00838  -0.1556   0.5471   0.5185
   0.750   0.7981   0.01657   0.00837  -0.1551   0.5364   0.5222
   1.000   0.8218   0.01667   0.00834  -0.1546   0.5235   0.5266
   1.250   0.8449   0.01678   0.00832  -0.1540   0.5082   0.5311
   1.500   0.8661   0.01687   0.00837  -0.1529   0.4918   0.5342
   1.750   0.8871   0.01702   0.00846  -0.1519   0.4751   0.5376
   2.000   0.9082   0.01719   0.00855  -0.1509   0.4580   0.5417
   2.250   0.9290   0.01741   0.00865  -0.1500   0.4399   0.5466
   2.500   0.9485   0.01762   0.00879  -0.1488   0.4175   0.5505
   2.750   0.9630   0.01801   0.00904  -0.1467   0.3864   0.5542
   3.000   0.9679   0.01870   0.00947  -0.1430   0.3417   0.5579
   3.250   0.9561   0.02054   0.01074  -0.1374   0.2565   0.5611
   3.500   0.9641   0.02166   0.01160  -0.1350   0.2242   0.5655
   3.750   0.9767   0.02244   0.01232  -0.1332   0.2069   0.5691
   4.000   0.9911   0.02315   0.01301  -0.1317   0.1938   0.5738
   4.250   1.0059   0.02389   0.01369  -0.1303   0.1799   0.5793
   4.750   1.0188   0.02644   0.01594  -0.1259   0.1197   0.5882
   5.000   1.0317   0.02737   0.01687  -0.1246   0.1155   0.5935
   5.250   1.0464   0.02824   0.01774  -0.1235   0.1125   0.5997
   5.500   1.0616   0.02904   0.01860  -0.1225   0.1107   0.6049
   5.750   1.0772   0.02985   0.01946  -0.1216   0.1095   0.6115
   6.000   1.0928   0.03071   0.02036  -0.1207   0.1084   0.6190
   6.250   1.1073   0.03161   0.02136  -0.1197   0.1073   0.6258
   6.500   1.1219   0.03259   0.02237  -0.1189   0.1063   0.6344
   6.750   1.1360   0.03357   0.02344  -0.1180   0.1054   0.6417
   7.000   1.1499   0.03463   0.02455  -0.1172   0.1046   0.6513
   7.250   1.1635   0.03567   0.02570  -0.1163   0.1040   0.6601
   7.500   1.1772   0.03676   0.02687  -0.1156   0.1036   0.6712
   7.750   1.1909   0.03786   0.02806  -0.1148   0.1033   0.6839
   8.000   1.2044   0.03898   0.02929  -0.1141   0.1032   0.6977
   8.250   1.2179   0.04013   0.03057  -0.1135   0.1030   0.7140
   8.500   1.2310   0.04130   0.03187  -0.1128   0.1030   0.7344
   8.750   1.2437   0.04241   0.03318  -0.1120   0.1030   0.7645
   9.000   1.2482   0.04325   0.03439  -0.1098   0.1028   1.0000
   9.250   1.2594   0.04487   0.03603  -0.1093   0.1020   1.0000
   9.500   1.2692   0.04660   0.03777  -0.1088   0.1008   1.0000
   9.750   1.2782   0.04841   0.03959  -0.1082   0.0996   1.0000
  10.000   1.2902   0.04993   0.04116  -0.1077   0.0987   1.0000
  10.250   1.3015   0.05154   0.04282  -0.1073   0.0977   1.0000
  10.500   1.3121   0.05322   0.04456  -0.1068   0.0961   1.0000
  10.750   1.3217   0.05502   0.04641  -0.1064   0.0942   1.0000
  11.000   1.3301   0.05695   0.04838  -0.1059   0.0927   1.0000
  11.250   1.3380   0.05895   0.05043  -0.1054   0.0914   1.0000
  11.500   1.3444   0.06115   0.05268  -0.1049   0.0899   1.0000
  11.750   1.3557   0.06282   0.05443  -0.1046   0.0874   1.0000
  12.000   1.3657   0.06468   0.05644  -0.1043   0.0677   1.0000
  12.250   1.3607   0.06819   0.05976  -0.1037   0.0635   1.0000
  12.500   1.3589   0.07147   0.06314  -0.1032   0.0620   1.0000
  12.750   1.3573   0.07478   0.06658  -0.1028   0.0610   1.0000
  13.000   1.3569   0.07799   0.06990  -0.1026   0.0601   1.0000
  13.250   1.3571   0.08118   0.07321  -0.1024   0.0593   1.0000
  13.500   1.3561   0.08454   0.07671  -0.1023   0.0585   1.0000
  13.750   1.3513   0.08842   0.08074  -0.1022   0.0574   1.0000
  14.000   1.3418   0.09300   0.08548  -0.1022   0.0562   1.0000
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