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GOE 184 (MVA H.29) AIRFOIL (goe184-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 184 (MVA H.29) AIRFOIL (goe184-il)
Reynolds number: 1,000,000
Max Cl/Cd: 111.86 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe184-il-1000000-n5.txt
Download as CSV file: xf-goe184-il-1000000-n5.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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.4076   0.12766   0.12599  -0.0076   1.0000   0.0055
 -10.000  -0.5787   0.01953   0.01639  -0.1027   0.9657   0.0100
  -9.750  -0.5527   0.01783   0.01447  -0.1035   0.9567   0.0106
  -9.500  -0.5271   0.01657   0.01300  -0.1038   0.9464   0.0110
  -9.250  -0.5014   0.01574   0.01206  -0.1037   0.9347   0.0117
  -9.000  -0.4752   0.01524   0.01148  -0.1035   0.9226   0.0123
  -8.750  -0.4491   0.01481   0.01095  -0.1032   0.9074   0.0130
  -8.500  -0.4235   0.01430   0.01026  -0.1029   0.8875   0.0136
  -8.250  -0.3975   0.01375   0.00950  -0.1026   0.8659   0.0142
  -8.000  -0.3707   0.01350   0.00915  -0.1023   0.8460   0.0148
  -7.750  -0.3435   0.01348   0.00905  -0.1020   0.8264   0.0153
  -7.500  -0.3161   0.01343   0.00891  -0.1018   0.8072   0.0159
  -7.250  -0.2886   0.01322   0.00857  -0.1017   0.7912   0.0166
  -7.000  -0.2610   0.01291   0.00811  -0.1016   0.7785   0.0172
  -6.750  -0.2332   0.01258   0.00765  -0.1016   0.7667   0.0178
  -6.500  -0.2053   0.01239   0.00733  -0.1015   0.7540   0.0182
  -6.250  -0.1776   0.01197   0.00679  -0.1016   0.7415   0.0187
  -6.000  -0.1497   0.01175   0.00648  -0.1015   0.7301   0.0192
  -5.750  -0.1216   0.01156   0.00621  -0.1015   0.7203   0.0196
  -5.500  -0.0934   0.01137   0.00594  -0.1015   0.7110   0.0202
  -5.250  -0.0653   0.01113   0.00560  -0.1015   0.7005   0.0208
  -5.000  -0.0370   0.01085   0.00523  -0.1015   0.6891   0.0214
  -4.750  -0.0087   0.01065   0.00492  -0.1015   0.6770   0.0220
  -4.500   0.0195   0.01045   0.00462  -0.1015   0.6636   0.0224
  -4.250   0.0477   0.01027   0.00432  -0.1014   0.6454   0.0227
  -4.000   0.0757   0.01016   0.00406  -0.1014   0.6194   0.0229
  -3.750   0.1035   0.00988   0.00361  -0.1013   0.5889   0.0234
  -3.500   0.1314   0.00961   0.00320  -0.1013   0.5644   0.0239
  -3.000   0.1879   0.00926   0.00266  -0.1014   0.5371   0.0246
  -2.750   0.2163   0.00912   0.00245  -0.1014   0.5280   0.0249
  -2.500   0.2448   0.00899   0.00227  -0.1014   0.5199   0.0253
  -2.250   0.2732   0.00888   0.00211  -0.1014   0.5130   0.0258
  -2.000   0.3017   0.00880   0.00197  -0.1014   0.5047   0.0265
  -1.750   0.3301   0.00873   0.00185  -0.1014   0.4960   0.0270
  -1.500   0.3585   0.00867   0.00174  -0.1014   0.4870   0.0275
  -1.250   0.3870   0.00862   0.00165  -0.1014   0.4809   0.0280
  -1.000   0.4155   0.00857   0.00157  -0.1014   0.4746   0.0284
  -0.750   0.4438   0.00856   0.00151  -0.1014   0.4676   0.0287
  -0.500   0.4723   0.00853   0.00146  -0.1015   0.4596   0.0290
  -0.250   0.5006   0.00852   0.00141  -0.1015   0.4512   0.0298
   0.000   0.5290   0.00851   0.00137  -0.1015   0.4424   0.0309
   0.250   0.5573   0.00852   0.00134  -0.1015   0.4337   0.0325
   0.500   0.5855   0.00854   0.00132  -0.1015   0.4211   0.0353
   0.750   0.6133   0.00857   0.00139  -0.1015   0.4018   0.0642
   1.000   0.6409   0.00872   0.00145  -0.1014   0.3813   0.0672
   1.250   0.6684   0.00887   0.00152  -0.1013   0.3618   0.0690
   1.750   0.7237   0.00910   0.00166  -0.1012   0.3340   0.0734
   2.000   0.7515   0.00919   0.00172  -0.1012   0.3262   0.0749
   2.250   0.7793   0.00927   0.00179  -0.1012   0.3196   0.0764
   2.500   0.8071   0.00936   0.00187  -0.1011   0.3141   0.0777
   2.750   0.8350   0.00943   0.00195  -0.1011   0.3095   0.0788
   3.000   0.8627   0.00950   0.00202  -0.1011   0.3041   0.0817
   3.250   0.8904   0.00959   0.00212  -0.1010   0.2988   0.0837
   3.500   0.9181   0.00967   0.00221  -0.1010   0.2936   0.0857
   3.750   0.9456   0.00977   0.00231  -0.1010   0.2871   0.0880
   4.250   1.0006   0.00992   0.00258  -0.1009   0.2743   0.1483
   4.500   1.0280   0.00990   0.00279  -0.1011   0.2634   0.2907
   5.000   1.0727   0.00959   0.00349  -0.0996   0.1864   1.0000
   5.250   1.0978   0.01004   0.00381  -0.0993   0.1645   1.0000
   5.500   1.1240   0.01031   0.00405  -0.0990   0.1560   1.0000
   5.750   1.1506   0.01053   0.00426  -0.0989   0.1510   1.0000
   6.000   1.1764   0.01084   0.00453  -0.0986   0.1422   1.0000
   6.250   1.2019   0.01116   0.00480  -0.0984   0.1301   1.0000
   6.500   1.2256   0.01171   0.00518  -0.0979   0.1008   1.0000
   6.750   1.2496   0.01221   0.00557  -0.0974   0.0842   1.0000
   7.000   1.2747   0.01255   0.00589  -0.0971   0.0772   1.0000
   7.250   1.2991   0.01295   0.00626  -0.0966   0.0683   1.0000
   7.500   1.3197   0.01378   0.00691  -0.0957   0.0360   1.0000
   7.750   1.3431   0.01427   0.00738  -0.0951   0.0283   1.0000
   8.000   1.3668   0.01468   0.00780  -0.0946   0.0247   1.0000
   8.250   1.3899   0.01514   0.00827  -0.0940   0.0209   1.0000
   8.500   1.4134   0.01554   0.00868  -0.0935   0.0187   1.0000
   8.750   1.4356   0.01604   0.00919  -0.0927   0.0157   1.0000
   9.000   1.4580   0.01649   0.00966  -0.0921   0.0138   1.0000
   9.250   1.4795   0.01701   0.01018  -0.0912   0.0120   1.0000
   9.500   1.5007   0.01752   0.01072  -0.0904   0.0108   1.0000
   9.750   1.5218   0.01802   0.01126  -0.0895   0.0099   1.0000
  10.000   1.5418   0.01858   0.01184  -0.0885   0.0091   1.0000
  10.250   1.5604   0.01921   0.01250  -0.0874   0.0083   1.0000
  10.500   1.5789   0.01982   0.01315  -0.0862   0.0078   1.0000
  10.750   1.5968   0.02041   0.01380  -0.0849   0.0073   1.0000
  11.000   1.6133   0.02106   0.01450  -0.0835   0.0068   1.0000
  11.250   1.6263   0.02177   0.01525  -0.0814   0.0064   1.0000
  11.500   1.6370   0.02258   0.01611  -0.0791   0.0061   1.0000
  11.750   1.6456   0.02358   0.01717  -0.0767   0.0057   1.0000
  12.000   1.6560   0.02451   0.01817  -0.0748   0.0056   1.0000
  12.250   1.6654   0.02556   0.01930  -0.0729   0.0054   1.0000
  12.500   1.6740   0.02675   0.02057  -0.0711   0.0052   1.0000
  12.750   1.6815   0.02808   0.02198  -0.0695   0.0050   1.0000
  13.000   1.6884   0.02957   0.02355  -0.0680   0.0049   1.0000
  13.250   1.6940   0.03126   0.02532  -0.0667   0.0047   1.0000
  13.500   1.6987   0.03316   0.02729  -0.0656   0.0046   1.0000
  13.750   1.7020   0.03529   0.02951  -0.0647   0.0044   1.0000
  14.000   1.7038   0.03769   0.03200  -0.0639   0.0043   1.0000
  14.250   1.7030   0.04047   0.03487  -0.0633   0.0041   1.0000
  14.500   1.6992   0.04370   0.03821  -0.0629   0.0040   1.0000
  14.750   1.6961   0.04695   0.04157  -0.0627   0.0039   1.0000
  15.000   1.6934   0.05023   0.04496  -0.0627   0.0039   1.0000
  15.250   1.6893   0.05379   0.04863  -0.0628   0.0038   1.0000
  15.500   1.6840   0.05762   0.05257  -0.0632   0.0038   1.0000
  15.750   1.6774   0.06175   0.05681  -0.0637   0.0037   1.0000
  16.000   1.6699   0.06610   0.06127  -0.0645   0.0036   1.0000
  16.250   1.6608   0.07078   0.06606  -0.0654   0.0036   1.0000
  16.500   1.6508   0.07563   0.07103  -0.0664   0.0035   1.0000
  16.750   1.6396   0.08072   0.07622  -0.0675   0.0035   1.0000
  17.000   1.6273   0.08608   0.08170  -0.0689   0.0035   1.0000
  17.250   1.6151   0.09151   0.08724  -0.0704   0.0034   1.0000
  17.500   1.6024   0.09705   0.09289  -0.0719   0.0034   1.0000
  17.750   1.5899   0.10269   0.09865  -0.0736   0.0033   1.0000
  18.000   1.5776   0.10841   0.10447  -0.0755   0.0033   1.0000
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