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GOE 184 (MVA H.29) AIRFOIL (goe184-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 184 (MVA H.29) AIRFOIL (goe184-il)
Reynolds number: 200,000
Max Cl/Cd: 79.41 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe184-il-200000.txt
Download as CSV file: xf-goe184-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3097   0.09511   0.09174  -0.0257   1.0000   0.0478
  -7.750  -0.3213   0.09393   0.09069  -0.0316   1.0000   0.0485
  -7.500  -0.3153   0.08963   0.08642  -0.0289   1.0000   0.0493
  -7.250  -0.3057   0.08700   0.08381  -0.0259   1.0000   0.0507
  -7.000  -0.3051   0.08500   0.08188  -0.0251   1.0000   0.0521
  -6.750  -0.3104   0.08336   0.08031  -0.0239   1.0000   0.0533
  -6.500  -0.3231   0.08231   0.07935  -0.0217   1.0000   0.0544
  -6.250  -0.2773   0.07516   0.07211  -0.0439   0.9913   0.0582
  -6.000  -0.2577   0.07169   0.06865  -0.0424   0.9873   0.0595
  -5.750  -0.2245   0.06790   0.06483  -0.0475   0.9831   0.0625
  -5.500  -0.1625   0.06041   0.05708  -0.0689   0.9732   0.0689
  -5.250  -0.1355   0.05675   0.05343  -0.0704   0.9701   0.0702
  -5.000  -0.1043   0.05339   0.05003  -0.0740   0.9622   0.0723
  -4.750  -0.0329   0.04787   0.04393  -0.0909   0.9560   0.0801
  -4.500  -0.0089   0.04264   0.03873  -0.0933   0.9462   0.0814
  -4.250   0.0221   0.03958   0.03562  -0.0956   0.9384   0.0827
  -4.000   0.0710   0.01415   0.00963  -0.0982   0.8978   0.0690
  -3.750   0.0935   0.01253   0.00793  -0.0980   0.8840   0.0702
  -3.500   0.1308   0.01953   0.01328  -0.1063   0.9044   0.0584
  -3.250   0.1585   0.01791   0.01136  -0.1059   0.8904   0.0592
  -3.000   0.1854   0.01694   0.01020  -0.1053   0.8756   0.0606
  -2.750   0.2120   0.01630   0.00938  -0.1045   0.8608   0.0635
  -2.500   0.2394   0.01537   0.00813  -0.1038   0.8467   0.0660
  -2.250   0.2666   0.01456   0.00705  -0.1031   0.8324   0.0686
  -2.000   0.2931   0.01396   0.00642  -0.1024   0.8176   0.0728
  -1.750   0.3202   0.01358   0.00583  -0.1017   0.8028   0.0800
  -1.500   0.3469   0.01303   0.00524  -0.1012   0.7875   0.0947
  -1.250   0.3737   0.01285   0.00499  -0.1007   0.7716   0.1096
  -1.000   0.4005   0.01283   0.00488  -0.1002   0.7552   0.1194
  -0.750   0.4272   0.01274   0.00472  -0.0997   0.7388   0.1269
  -0.500   0.4542   0.01269   0.00458  -0.0993   0.7226   0.1318
  -0.250   0.4813   0.01269   0.00445  -0.0988   0.7069   0.1363
   0.000   0.5082   0.01259   0.00435  -0.0985   0.6917   0.1436
   0.250   0.5353   0.01258   0.00427  -0.0982   0.6770   0.1498
   0.500   0.5625   0.01249   0.00414  -0.0979   0.6627   0.1549
   0.750   0.5897   0.01243   0.00406  -0.0976   0.6487   0.1625
   1.000   0.6169   0.01236   0.00397  -0.0973   0.6343   0.1695
   1.250   0.6441   0.01228   0.00390  -0.0970   0.6196   0.1799
   1.500   0.6712   0.01216   0.00385  -0.0968   0.6052   0.2069
   1.750   0.6929   0.01049   0.00386  -0.0953   0.5921   1.0000
   2.000   0.7201   0.01068   0.00387  -0.0949   0.5787   1.0000
   2.250   0.7471   0.01090   0.00395  -0.0946   0.5661   1.0000
   2.500   0.7740   0.01115   0.00405  -0.0943   0.5537   1.0000
   2.750   0.8008   0.01142   0.00417  -0.0940   0.5413   1.0000
   3.000   0.8276   0.01169   0.00434  -0.0937   0.5290   1.0000
   3.250   0.8544   0.01194   0.00455  -0.0934   0.5171   1.0000
   3.500   0.8812   0.01223   0.00476  -0.0932   0.5062   1.0000
   3.750   0.9079   0.01254   0.00497  -0.0929   0.4959   1.0000
   4.000   0.9345   0.01277   0.00521  -0.0927   0.4848   1.0000
   4.250   0.9612   0.01303   0.00546  -0.0924   0.4747   1.0000
   4.500   0.9877   0.01331   0.00566  -0.0921   0.4655   1.0000
   4.750   1.0141   0.01350   0.00591  -0.0918   0.4548   1.0000
   5.000   1.0404   0.01374   0.00615  -0.0915   0.4454   1.0000
   5.250   1.0666   0.01398   0.00636  -0.0912   0.4365   1.0000
   5.500   1.0929   0.01420   0.00666  -0.0909   0.4275   1.0000
   5.750   1.1190   0.01448   0.00692  -0.0906   0.4200   1.0000
   6.000   1.1449   0.01469   0.00722  -0.0903   0.4103   1.0000
   6.250   1.1703   0.01491   0.00747  -0.0899   0.3995   1.0000
   6.500   1.1953   0.01514   0.00773  -0.0894   0.3880   1.0000
   6.750   1.2199   0.01541   0.00800  -0.0888   0.3763   1.0000
   7.000   1.2442   0.01567   0.00831  -0.0883   0.3627   1.0000
   7.250   1.2681   0.01597   0.00865  -0.0877   0.3481   1.0000
   7.500   1.2911   0.01633   0.00902  -0.0869   0.3317   1.0000
   7.750   1.3141   0.01669   0.00943  -0.0862   0.3145   1.0000
   8.000   1.3368   0.01706   0.00987  -0.0855   0.2942   1.0000
   8.250   1.3584   0.01750   0.01032  -0.0846   0.2689   1.0000
   8.500   1.3783   0.01809   0.01085  -0.0836   0.2269   1.0000
   8.750   1.3899   0.01950   0.01183  -0.0817   0.1737   1.0000
   9.000   1.4026   0.02089   0.01305  -0.0798   0.1362   1.0000
   9.250   1.4085   0.02285   0.01455  -0.0773   0.0760   1.0000
   9.500   1.4148   0.02463   0.01613  -0.0746   0.0498   1.0000
   9.750   1.4224   0.02614   0.01763  -0.0721   0.0432   1.0000
  10.000   1.4239   0.02780   0.01938  -0.0688   0.0396   1.0000
  10.250   1.4277   0.02934   0.02107  -0.0660   0.0379   1.0000
  10.500   1.4291   0.03114   0.02301  -0.0634   0.0365   1.0000
  10.750   1.4286   0.03324   0.02524  -0.0611   0.0352   1.0000
  11.000   1.4261   0.03568   0.02780  -0.0592   0.0341   1.0000
  11.250   1.4214   0.03854   0.03074  -0.0575   0.0330   1.0000
  11.500   1.4146   0.04178   0.03405  -0.0560   0.0320   1.0000
  11.750   1.4123   0.04469   0.03705  -0.0546   0.0311   1.0000
  12.000   1.4157   0.04709   0.03957  -0.0536   0.0304   1.0000
  12.250   1.4189   0.04953   0.04214  -0.0525   0.0297   1.0000
  12.500   1.4228   0.05193   0.04463  -0.0513   0.0291   1.0000
  12.750   1.4279   0.05424   0.04704  -0.0500   0.0285   1.0000
  13.000   1.4342   0.05649   0.04938  -0.0487   0.0279   1.0000
  13.250   1.4401   0.05884   0.05182  -0.0475   0.0272   1.0000
  13.500   1.4456   0.06128   0.05434  -0.0464   0.0264   1.0000
  13.750   1.4545   0.06358   0.05666  -0.0449   0.0254   1.0000
  14.000   1.4731   0.06657   0.05977  -0.0421   0.0245   1.0000
  14.250   1.4728   0.07039   0.06380  -0.0413   0.0243   1.0000
  14.500   1.4657   0.07415   0.06780  -0.0412   0.0243   1.0000
  14.750   1.4581   0.07823   0.07211  -0.0413   0.0242   1.0000
  15.000   1.4487   0.08265   0.07676  -0.0417   0.0242   1.0000
  15.250   1.4379   0.08743   0.08176  -0.0424   0.0242   1.0000
  15.500   1.4261   0.09259   0.08714  -0.0435   0.0243   1.0000
  15.750   1.4163   0.09815   0.09293  -0.0442   0.0244   1.0000
  16.000   1.4028   0.10324   0.09822  -0.0463   0.0245   1.0000
  16.250   1.3890   0.10864   0.10380  -0.0490   0.0246   1.0000
  16.500   1.3749   0.11437   0.10972  -0.0522   0.0247   1.0000
  16.750   1.3592   0.12074   0.11630  -0.0562   0.0248   1.0000
  17.000   1.3419   0.12792   0.12370  -0.0611   0.0250   1.0000
  17.250   1.3200   0.13680   0.13283  -0.0675   0.0254   1.0000
  17.500   1.2809   0.15111   0.14751  -0.0785   0.0262   1.0000
  17.750   1.1558   0.20173   0.19852  -0.1124   0.0332   1.0000
  18.000   1.1674   0.20155   0.19839  -0.1122   0.0325   1.0000
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