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GOE 229 (MVA H.39) AIRFOIL (goe229-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 229 (MVA H.39) AIRFOIL (goe229-il)
Reynolds number: 50,000
Max Cl/Cd: 10.8 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe229-il-50000.txt
Download as CSV file: xf-goe229-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.2812   0.12735   0.12242  -0.0317   0.9663   0.2979
  -7.500  -0.4596   0.10348   0.09881  -0.0460   0.9672   0.1494
  -7.250  -0.5388   0.08233   0.07745  -0.0669   0.9662   0.1339
  -7.000  -0.5358   0.07475   0.06960  -0.0742   0.9604   0.1306
  -6.750  -0.5089   0.06447   0.05837  -0.0887   0.9548   0.1256
  -6.500  -0.4776   0.05946   0.05261  -0.0955   0.9471   0.1245
  -6.250  -0.4358   0.05663   0.04933  -0.1009   0.9393   0.1280
  -6.000  -0.4061   0.05457   0.04683  -0.1036   0.9318   0.1306
  -5.750  -0.3702   0.05295   0.04478  -0.1064   0.9251   0.1329
  -5.500  -0.3363   0.05184   0.04345  -0.1083   0.9183   0.1373
  -5.250  -0.4944   0.05227   0.04461  -0.0819   1.0000   0.1298
  -5.000  -0.4706   0.05107   0.04310  -0.0828   1.0000   0.1317
  -4.750  -0.4471   0.05027   0.04198  -0.0834   1.0000   0.1344
  -4.500  -0.4264   0.04959   0.04139  -0.0832   1.0000   0.1393
  -4.250  -0.4051   0.04929   0.04109  -0.0832   1.0000   0.1455
  -4.000  -0.3824   0.04917   0.04080  -0.0833   1.0000   0.1512
  -3.750  -0.3597   0.04902   0.04088  -0.0836   1.0000   0.1594
  -3.500  -0.3335   0.04891   0.04091  -0.0852   1.0000   0.1745
  -3.250  -0.3011   0.04862   0.04105  -0.0885   1.0000   0.2081
  -3.000  -0.2816   0.04985   0.04360  -0.0876   1.0000   0.3485
  -2.750  -0.2740   0.05373   0.04742  -0.0820   0.9973   0.4288
  -2.500  -0.2644   0.05784   0.05156  -0.0756   0.9924   0.4663
  -2.250  -0.2506   0.06082   0.05446  -0.0714   0.9855   0.4974
  -2.000  -0.2416   0.06382   0.05750  -0.0654   0.9812   0.5222
  -1.750  -0.2314   0.06523   0.05884  -0.0618   0.9748   0.5493
  -1.500  -0.2159   0.06731   0.06087  -0.0581   0.9692   0.5717
  -1.250  -0.2070   0.06796   0.06145  -0.0549   0.9634   0.5912
  -1.000  -0.1815   0.06944   0.06277  -0.0554   0.9561   0.6180
  -0.750  -0.1696   0.07058   0.06387  -0.0519   0.9525   0.6393
  -0.500  -0.1565   0.07056   0.06377  -0.0506   0.9440   0.6559
  -0.250  -0.1125   0.07252   0.06547  -0.0568   0.9381   0.6685
   0.000  -0.1010   0.07211   0.06499  -0.0561   0.9303   0.6730
   0.250  -0.0634   0.07353   0.06622  -0.0608   0.9234   0.6795
   0.500  -0.0358   0.07442   0.06695  -0.0646   0.9168   0.6851
   0.750  -0.0073   0.07539   0.06782  -0.0669   0.9078   0.6907
   1.000   0.0199   0.07674   0.06904  -0.0699   0.9022   0.6963
   1.250   0.0510   0.07785   0.07002  -0.0737   0.8917   0.7021
   1.500   0.0753   0.07927   0.07137  -0.0755   0.8857   0.7074
   1.750   0.1034   0.08041   0.07242  -0.0784   0.8745   0.7131
   2.000   0.1269   0.08179   0.07371  -0.0809   0.8661   0.7184
   2.250   0.1629   0.08385   0.07572  -0.0844   0.8560   0.7250
   2.500   0.1777   0.08456   0.07638  -0.0851   0.8438   0.7298
   2.750   0.2045   0.08631   0.07807  -0.0878   0.8322   0.7356
   3.000   0.2426   0.08885   0.08056  -0.0914   0.8204   0.7430
   3.250   0.2815   0.09126   0.08288  -0.0957   0.8048   0.7503
   3.500   0.2988   0.09214   0.08377  -0.0960   0.7891   0.7557
   3.750   0.3180   0.09345   0.08507  -0.0969   0.7735   0.7623
   4.000   0.3398   0.09511   0.08670  -0.0984   0.7576   0.7690
   4.250   0.3597   0.09671   0.08831  -0.0992   0.7416   0.7758
   4.750   0.4759   0.09595   0.08734  -0.1034   0.6550   0.8008
   5.000   0.4641   0.09937   0.09088  -0.1031   0.6573   0.8053
   5.250   0.4632   0.10271   0.09431  -0.1035   0.6580   0.8117
   5.500   0.5939   0.09120   0.08253  -0.1023   0.5702   0.8430
   5.750   0.6183   0.09040   0.08177  -0.1013   0.5494   0.8602
   6.250   0.7091   0.08532   0.07685  -0.1010   0.5232   1.0000
   6.500   0.7322   0.08634   0.07783  -0.1025   0.5077   1.0000
   6.750   0.7590   0.08682   0.07827  -0.1039   0.4925   1.0000
   7.000   0.7848   0.08729   0.07868  -0.1050   0.4779   1.0000
   7.250   0.8586   0.08297   0.07422  -0.1074   0.4731   1.0000
   7.500   0.8593   0.08602   0.07726  -0.1075   0.4585   1.0000
   7.750   0.8610   0.08904   0.08026  -0.1076   0.4450   1.0000
   8.000   0.9120   0.08643   0.07755  -0.1083   0.4409   1.0000
   8.250   0.9038   0.09055   0.08167  -0.1080   0.4271   1.0000
   8.500   0.9506   0.08803   0.07910  -0.1080   0.4240   1.0000
   8.750   0.9298   0.09406   0.08515  -0.1079   0.4103   1.0000
   9.000   0.9674   0.09263   0.08368  -0.1076   0.4073   1.0000
   9.250   0.9386   0.10014   0.09124  -0.1080   0.3946   1.0000
   9.500   0.9289   0.10527   0.09639  -0.1083   0.3864   1.0000
   9.750   0.9406   0.10725   0.09840  -0.1083   0.3799   1.0000
  10.000   0.9859   0.10399   0.09511  -0.1072   0.3764   1.0000
  10.250   0.9532   0.11234   0.10352  -0.1082   0.3650   1.0000
  10.500   1.0021   0.10802   0.09919  -0.1066   0.3609   1.0000
  10.750   0.9666   0.11721   0.10843  -0.1081   0.3504   1.0000
  11.000   1.0061   0.11428   0.10553  -0.1067   0.3459   1.0000
  11.250   0.9821   0.12171   0.11301  -0.1081   0.3362   1.0000
  11.500   1.0076   0.12112   0.11246  -0.1073   0.3313   1.0000
  11.750   1.0454   0.11854   0.10993  -0.1059   0.3287   1.0000
  12.000   1.0142   0.12705   0.11848  -0.1078   0.3167   1.0000
  12.250   1.0436   0.12590   0.11739  -0.1067   0.3139   1.0000
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