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GOE 184 (MVA H.29) AIRFOIL (goe184-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 184 (MVA H.29) AIRFOIL (goe184-il)
Reynolds number: 100,000
Max Cl/Cd: 57.37 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe184-il-100000.txt
Download as CSV file: xf-goe184-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 184 (MVA H.29) AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3169   0.10593   0.10109  -0.0225   1.0000   0.0785
  -8.250  -0.3240   0.10573   0.10099  -0.0263   1.0000   0.0796
  -8.000  -0.3308   0.10538   0.10076  -0.0316   1.0000   0.0800
  -7.750  -0.3248   0.10053   0.09598  -0.0313   1.0000   0.0807
  -7.500  -0.3080   0.09466   0.09009  -0.0262   1.0000   0.0823
  -7.250  -0.3009   0.09162   0.08709  -0.0250   1.0000   0.0844
  -7.000  -0.2989   0.08928   0.08483  -0.0248   1.0000   0.0868
  -6.750  -0.3003   0.08730   0.08293  -0.0252   1.0000   0.0893
  -6.500  -0.3056   0.08599   0.08172  -0.0267   1.0000   0.0916
  -6.250  -0.3125   0.08620   0.08198  -0.0333   1.0000   0.0931
  -6.000  -0.3142   0.08391   0.07971  -0.0354   1.0000   0.0938
  -5.750  -0.3184   0.08025   0.07616  -0.0302   1.0000   0.0945
  -5.500  -0.3207   0.07765   0.07362  -0.0264   1.0000   0.0955
  -5.250  -0.3207   0.07544   0.07146  -0.0243   1.0000   0.0969
  -5.000  -0.2998   0.07212   0.06812  -0.0275   0.9966   0.1003
  -4.750  -0.2374   0.06631   0.06204  -0.0458   0.9877   0.1089
  -4.500  -0.2097   0.06251   0.05827  -0.0468   0.9818   0.1136
  -4.250  -0.1518   0.05755   0.05302  -0.0604   0.9728   0.1239
  -4.000  -0.1194   0.05407   0.04954  -0.0629   0.9651   0.1291
  -3.750  -0.0478   0.05115   0.04604  -0.0776   0.9569   0.1526
  -3.500  -0.0247   0.04666   0.04176  -0.0778   0.9480   0.1562
  -3.250   0.0257   0.04321   0.03815  -0.0845   0.9416   0.1716
  -3.000   0.0686   0.04033   0.03511  -0.0892   0.9313   0.1877
  -2.750   0.1542   0.03032   0.02349  -0.1024   0.9271   0.1087
  -2.500   0.1983   0.02719   0.02000  -0.1055   0.9159   0.1044
  -2.250   0.2443   0.02435   0.01659  -0.1084   0.9057   0.1046
  -2.000   0.2857   0.02247   0.01438  -0.1103   0.8949   0.1120
  -1.750   0.3202   0.02114   0.01265  -0.1106   0.8810   0.1217
  -1.500   0.3517   0.01979   0.01118  -0.1106   0.8669   0.1393
  -1.250   0.3811   0.01909   0.01044  -0.1102   0.8521   0.1607
  -1.000   0.4091   0.01876   0.01001  -0.1096   0.8368   0.1806
  -0.750   0.4364   0.01829   0.00949  -0.1088   0.8213   0.1901
  -0.500   0.4632   0.01800   0.00913  -0.1079   0.8057   0.2025
  -0.250   0.4899   0.01782   0.00881  -0.1070   0.7903   0.2134
   0.000   0.5161   0.01751   0.00853  -0.1062   0.7751   0.2215
   0.250   0.5424   0.01732   0.00824  -0.1053   0.7601   0.2287
   0.500   0.5680   0.01709   0.00803  -0.1043   0.7454   0.2371
   0.750   0.5943   0.01693   0.00786  -0.1034   0.7308   0.2515
   1.000   0.6208   0.01672   0.00774  -0.1027   0.7166   0.2860
   1.250   0.6448   0.01502   0.00746  -0.1011   0.7035   1.0000
   1.500   0.6716   0.01525   0.00742  -0.1004   0.6902   1.0000
   1.750   0.6984   0.01547   0.00744  -0.0998   0.6775   1.0000
   2.000   0.7250   0.01569   0.00750  -0.0992   0.6645   1.0000
   2.250   0.7513   0.01594   0.00765  -0.0987   0.6507   1.0000
   2.500   0.7776   0.01620   0.00780  -0.0982   0.6371   1.0000
   2.750   0.8039   0.01646   0.00797  -0.0976   0.6238   1.0000
   3.000   0.8303   0.01673   0.00815  -0.0971   0.6111   1.0000
   3.250   0.8568   0.01702   0.00836  -0.0966   0.5991   1.0000
   3.500   0.8836   0.01729   0.00851  -0.0961   0.5879   1.0000
   3.750   0.9097   0.01763   0.00881  -0.0957   0.5754   1.0000
   4.000   0.9355   0.01802   0.00919  -0.0952   0.5632   1.0000
   4.250   0.9617   0.01844   0.00958  -0.0948   0.5523   1.0000
   4.500   0.9888   0.01886   0.00989  -0.0944   0.5434   1.0000
   4.750   1.0140   0.01938   0.01050  -0.0941   0.5327   1.0000
   5.000   1.0399   0.01987   0.01102  -0.0937   0.5233   1.0000
   5.250   1.0661   0.02033   0.01147  -0.0933   0.5143   1.0000
   5.500   1.0911   0.02092   0.01217  -0.0929   0.5050   1.0000
   5.750   1.1179   0.02133   0.01253  -0.0925   0.4964   1.0000
   6.000   1.1418   0.02180   0.01316  -0.0919   0.4853   1.0000
   6.250   1.1664   0.02224   0.01369  -0.0913   0.4747   1.0000
   6.500   1.1926   0.02254   0.01396  -0.0908   0.4651   1.0000
   6.750   1.2162   0.02294   0.01456  -0.0901   0.4539   1.0000
   7.000   1.2399   0.02331   0.01506  -0.0893   0.4424   1.0000
   7.250   1.2635   0.02339   0.01520  -0.0883   0.4281   1.0000
   7.500   1.2863   0.02333   0.01519  -0.0872   0.4117   1.0000
   7.750   1.3088   0.02334   0.01529  -0.0860   0.3953   1.0000
   8.000   1.3306   0.02339   0.01537  -0.0848   0.3781   1.0000
   8.250   1.3508   0.02355   0.01559  -0.0834   0.3590   1.0000
   8.500   1.3699   0.02388   0.01605  -0.0819   0.3393   1.0000
   8.750   1.3882   0.02425   0.01652  -0.0804   0.3190   1.0000
   9.000   1.4045   0.02470   0.01710  -0.0787   0.2948   1.0000
   9.250   1.4189   0.02520   0.01772  -0.0768   0.2647   1.0000
   9.500   1.4300   0.02600   0.01849  -0.0746   0.2203   1.0000
   9.750   1.4290   0.02792   0.01997  -0.0712   0.1716   1.0000
  10.000   1.4221   0.03057   0.02238  -0.0675   0.1219   1.0000
  10.250   1.4113   0.03320   0.02467  -0.0634   0.0930   1.0000
  10.500   1.4011   0.03597   0.02735  -0.0601   0.0816   1.0000
  10.750   1.3953   0.03863   0.03010  -0.0576   0.0742   1.0000
  11.000   1.3874   0.04167   0.03316  -0.0556   0.0698   1.0000
  11.250   1.3845   0.04448   0.03607  -0.0540   0.0659   1.0000
  11.500   1.3838   0.04720   0.03890  -0.0528   0.0621   1.0000
  11.750   1.3813   0.05015   0.04185  -0.0518   0.0590   1.0000
  12.000   1.3826   0.05279   0.04454  -0.0504   0.0563   1.0000
  12.250   1.3876   0.05514   0.04701  -0.0491   0.0540   1.0000
  12.500   1.3943   0.05737   0.04933  -0.0476   0.0520   1.0000
  12.750   1.4035   0.05944   0.05141  -0.0460   0.0503   1.0000
  13.000   1.4231   0.06115   0.05301  -0.0434   0.0480   1.0000
  13.250   1.4277   0.06398   0.05610  -0.0425   0.0469   1.0000
  13.500   1.4313   0.06702   0.05940  -0.0415   0.0457   1.0000
  13.750   1.4347   0.07031   0.06293  -0.0407   0.0448   1.0000
  14.000   1.4351   0.07404   0.06692  -0.0400   0.0444   1.0000
  14.250   1.4302   0.07830   0.07146  -0.0397   0.0442   1.0000
  14.500   1.4202   0.08312   0.07657  -0.0401   0.0442   1.0000
  14.750   1.4057   0.08851   0.08224  -0.0411   0.0443   1.0000
  15.000   1.3878   0.09448   0.08850  -0.0429   0.0445   1.0000
  15.250   1.3672   0.10105   0.09534  -0.0455   0.0448   1.0000
  15.500   1.3445   0.10831   0.10286  -0.0490   0.0451   1.0000
  15.750   1.3204   0.11633   0.11112  -0.0534   0.0456   1.0000
  16.000   1.2949   0.12519   0.12020  -0.0588   0.0460   1.0000
  16.250   1.2684   0.13503   0.13022  -0.0651   0.0466   1.0000
  16.500   1.2419   0.14575   0.14109  -0.0723   0.0472   1.0000
  16.750   1.2181   0.15675   0.15218  -0.0794   0.0479   1.0000
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