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GOE 242 (MVA PR.2) AIRFOIL (goe242-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 242 (MVA PR.2) AIRFOIL (goe242-il)
Reynolds number: 100,000
Max Cl/Cd: 54.4 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe242-il-100000-n5.txt
Download as CSV file: xf-goe242-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 242 (MVA PR.2) 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750   0.0091   0.10222   0.09724  -0.0961   0.8712   0.0679
  -9.500  -0.0025   0.09930   0.09434  -0.1022   0.8601   0.0727
  -9.250  -0.0032   0.09574   0.09078  -0.1055   0.8493   0.0730
  -8.750   0.0055   0.08028   0.07519  -0.1091   0.8327   0.0412
  -8.500   0.0124   0.07722   0.07212  -0.1099   0.8222   0.0408
  -8.250   0.0167   0.07338   0.06824  -0.1117   0.8130   0.0404
  -8.000   0.0149   0.06836   0.06323  -0.1149   0.8018   0.0403
  -7.750   0.0067   0.06156   0.05640  -0.1206   0.7913   0.0401
  -7.500   0.0024   0.05209   0.04670  -0.1353   0.7814   0.0398
  -7.250   0.0330   0.04189   0.03578  -0.1605   0.7691   0.0403
  -7.000   0.0755   0.03657   0.02967  -0.1731   0.7597   0.0409
  -6.750   0.1132   0.03314   0.02573  -0.1794   0.7506   0.0421
  -6.500   0.1431   0.03139   0.02386  -0.1817   0.7409   0.0440
  -6.250   0.1783   0.02951   0.02164  -0.1849   0.7331   0.0457
  -6.000   0.2122   0.02784   0.01964  -0.1873   0.7240   0.0466
  -5.750   0.2462   0.02651   0.01796  -0.1892   0.7170   0.0485
  -5.500   0.2791   0.02557   0.01669  -0.1908   0.7089   0.0503
  -5.250   0.3081   0.02446   0.01550  -0.1912   0.7023   0.0513
  -5.000   0.3362   0.02369   0.01470  -0.1913   0.6954   0.0525
  -4.750   0.3649   0.02310   0.01407  -0.1915   0.6887   0.0542
  -4.500   0.3946   0.02265   0.01352  -0.1919   0.6832   0.0570
  -4.250   0.4234   0.02235   0.01316  -0.1921   0.6765   0.0590
  -4.000   0.4538   0.02207   0.01275  -0.1925   0.6713   0.0604
  -3.750   0.4878   0.02169   0.01227  -0.1941   0.6668   0.0626
  -3.500   0.5230   0.02134   0.01184  -0.1964   0.6614   0.0660
  -3.250   0.5586   0.02104   0.01138  -0.1985   0.6568   0.0722
  -3.000   0.5969   0.02061   0.01085  -0.2013   0.6531   0.0824
  -2.750   0.6441   0.01953   0.01022  -0.2073   0.6485   0.2206
  -2.500   0.6731   0.01980   0.01110  -0.2076   0.6438   0.3756
  -2.250   0.7021   0.02025   0.01139  -0.2075   0.6398   0.4174
  -2.000   0.7310   0.02069   0.01164  -0.2074   0.6365   0.4402
  -1.750   0.7587   0.02108   0.01192  -0.2073   0.6328   0.4535
  -1.500   0.7833   0.02161   0.01244  -0.2063   0.6291   0.4656
  -1.250   0.8079   0.02216   0.01296  -0.2053   0.6257   0.4803
  -1.000   0.8339   0.02260   0.01333  -0.2046   0.6227   0.4935
  -0.750   0.8636   0.02280   0.01339  -0.2049   0.6199   0.5015
  -0.500   0.8921   0.02302   0.01354  -0.2054   0.6164   0.5076
  -0.250   0.9182   0.02329   0.01381  -0.2051   0.6127   0.5122
   0.000   0.9475   0.02349   0.01394  -0.2058   0.6097   0.5183
   0.250   0.9772   0.02367   0.01403  -0.2064   0.6069   0.5239
   0.500   1.0051   0.02388   0.01419  -0.2064   0.6043   0.5282
   0.750   1.0343   0.02409   0.01433  -0.2069   0.6015   0.5329
   1.000   1.0627   0.02436   0.01459  -0.2077   0.5978   0.5370
   1.250   1.0908   0.02458   0.01480  -0.2082   0.5942   0.5395
   1.500   1.1189   0.02472   0.01490  -0.2084   0.5899   0.5417
   1.750   1.1492   0.02475   0.01481  -0.2089   0.5854   0.5445
   2.000   1.1724   0.02502   0.01516  -0.2085   0.5782   0.5475
   2.250   1.2013   0.02507   0.01513  -0.2089   0.5723   0.5507
   2.500   1.2314   0.02516   0.01512  -0.2096   0.5676   0.5539
   2.750   1.2550   0.02548   0.01553  -0.2092   0.5619   0.5562
   3.000   1.2811   0.02566   0.01573  -0.2092   0.5571   0.5585
   3.250   1.3101   0.02576   0.01580  -0.2095   0.5532   0.5614
   3.500   1.3342   0.02610   0.01620  -0.2092   0.5484   0.5648
   3.750   1.3583   0.02643   0.01660  -0.2090   0.5432   0.5684
   4.000   1.3858   0.02660   0.01677  -0.2092   0.5387   0.5718
   4.250   1.4143   0.02670   0.01684  -0.2094   0.5349   0.5742
   4.500   1.4331   0.02721   0.01755  -0.2083   0.5290   0.5769
   4.750   1.4570   0.02749   0.01789  -0.2079   0.5239   0.5802
   5.000   1.4851   0.02761   0.01799  -0.2081   0.5197   0.5844
   5.250   1.5048   0.02809   0.01859  -0.2072   0.5140   0.5882
   5.500   1.5251   0.02845   0.01908  -0.2062   0.5080   0.5913
   5.750   1.5515   0.02852   0.01916  -0.2060   0.5030   0.5950
   6.000   1.5663   0.02912   0.01992  -0.2043   0.4959   0.5986
   6.250   1.5870   0.02943   0.02030  -0.2034   0.4894   0.6027
   6.500   1.6061   0.02976   0.02071  -0.2021   0.4832   0.6061
   6.750   1.6184   0.03037   0.02148  -0.2000   0.4755   0.6097
   7.000   1.6397   0.03055   0.02168  -0.1990   0.4695   0.6144
   7.250   1.6442   0.03151   0.02284  -0.1958   0.4605   0.6187
   7.500   1.6590   0.03181   0.02319  -0.1938   0.4537   0.6226
   7.750   1.6570   0.03300   0.02457  -0.1899   0.4439   0.6260
   8.000   1.6653   0.03384   0.02549  -0.1874   0.4351   0.6302
   8.250   1.6714   0.03488   0.02661  -0.1849   0.4252   0.6348
   8.500   1.6721   0.03637   0.02825  -0.1820   0.4143   0.6385
   8.750   1.6771   0.03765   0.02960  -0.1797   0.4040   0.6431
   9.000   1.6840   0.03887   0.03084  -0.1776   0.3939   0.6485
   9.250   1.6855   0.04065   0.03270  -0.1753   0.3831   0.6532
   9.500   1.6909   0.04214   0.03423  -0.1733   0.3735   0.6582
   9.750   1.6975   0.04359   0.03567  -0.1715   0.3644   0.6640
  10.000   1.6989   0.04561   0.03776  -0.1696   0.3546   0.6692
  10.250   1.7028   0.04736   0.03949  -0.1677   0.3449   0.6749
  10.500   1.7026   0.04957   0.04168  -0.1658   0.3342   0.6813
  10.750   1.6997   0.05217   0.04434  -0.1639   0.3239   0.6872
  11.000   1.6990   0.05452   0.04667  -0.1622   0.3138   0.6945
  11.250   1.6959   0.05729   0.04950  -0.1606   0.3044   0.7017
  11.500   1.6959   0.05982   0.05212  -0.1592   0.2965   0.7104
  11.750   1.6948   0.06257   0.05496  -0.1580   0.2885   0.7198
  12.000   1.6941   0.06532   0.05781  -0.1569   0.2809   0.7315
  12.500   1.6900   0.07135   0.06411  -0.1551   0.2655   0.7710
  12.750   1.6825   0.07454   0.06752  -0.1539   0.2588   1.0000
  13.000   1.6833   0.07736   0.07033  -0.1533   0.2521   1.0000
  13.250   1.6790   0.08115   0.07429  -0.1529   0.2456   1.0000
  13.500   1.6776   0.08437   0.07757  -0.1525   0.2388   1.0000
  13.750   1.6738   0.08812   0.08146  -0.1523   0.2324   1.0000
  14.000   1.6683   0.09209   0.08551  -0.1522   0.2247   1.0000
  14.250   1.6611   0.09639   0.08992  -0.1522   0.2167   1.0000
  14.500   1.6544   0.10063   0.09424  -0.1523   0.2085   1.0000
  14.750   1.6473   0.10509   0.09885  -0.1526   0.2008   1.0000
  15.000   1.6398   0.10958   0.10340  -0.1530   0.1920   1.0000
  15.250   1.6311   0.11446   0.10846  -0.1537   0.1822   1.0000
  15.500   1.6220   0.11942   0.11353  -0.1546   0.1697   1.0000
  15.750   1.6100   0.12481   0.11892  -0.1557   0.1438   1.0000
  16.000   1.5848   0.13232   0.12608  -0.1577   0.1017   1.0000
  16.250   1.5614   0.13991   0.13353  -0.1601   0.0876   1.0000
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