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GOE 242 (MVA PR.2) AIRFOIL (goe242-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 242 (MVA PR.2) AIRFOIL (goe242-il)
Reynolds number: 200,000
Max Cl/Cd: 78.59 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe242-il-200000.txt
Download as CSV file: xf-goe242-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500   0.0635   0.09396   0.09059  -0.0995   0.8944   0.0539
 -10.250   0.0738   0.09177   0.08837  -0.0987   0.8836   0.0563
 -10.000   0.0763   0.08894   0.08549  -0.0991   0.8745   0.0592
  -9.750   0.0583   0.08503   0.08160  -0.1042   0.8642   0.0621
  -9.500   0.0627   0.08067   0.07721  -0.1037   0.8547   0.0633
  -9.250   0.0800   0.07885   0.07532  -0.1013   0.8429   0.0650
  -9.000   0.0897   0.07656   0.07300  -0.1008   0.8306   0.0674
  -8.750   0.0921   0.07349   0.06989  -0.1018   0.8197   0.0711
  -8.500   0.0634   0.06773   0.06413  -0.1110   0.8105   0.0743
  -8.250   0.0888   0.06548   0.06183  -0.1055   0.7980   0.0767
  -8.000   0.0078   0.07178   0.06814  -0.1184   0.8262   0.0747
  -7.750   0.0355   0.07212   0.06841  -0.1101   0.8147   0.0766
  -7.500   0.0516   0.07093   0.06715  -0.1084   0.8028   0.0792
  -7.250   0.0377   0.05891   0.05509  -0.1326   0.7909   0.0888
  -7.000   0.0572   0.06214   0.05830  -0.1193   0.7788   0.0904
  -6.750   0.0761   0.06220   0.05829  -0.1156   0.7671   0.0945
  -6.500   0.0870   0.05468   0.05072  -0.1297   0.7575   0.1055
  -6.250   0.1052   0.05476   0.05074  -0.1261   0.7466   0.1095
  -6.000   0.2281   0.02621   0.01953  -0.1928   0.7389   0.0627
  -5.750   0.2610   0.02385   0.01693  -0.1946   0.7300   0.0614
  -5.500   0.2949   0.02192   0.01475  -0.1965   0.7214   0.0602
  -5.250   0.3280   0.02064   0.01321  -0.1977   0.7139   0.0599
  -5.000   0.3605   0.01989   0.01225  -0.1988   0.7066   0.0613
  -4.750   0.3920   0.01913   0.01133  -0.1995   0.6998   0.0618
  -4.500   0.4231   0.01847   0.01053  -0.2001   0.6942   0.0621
  -4.250   0.4535   0.01778   0.00984  -0.2006   0.6878   0.0629
  -4.000   0.4855   0.01710   0.00918  -0.2017   0.6825   0.0655
  -3.750   0.5186   0.01674   0.00879  -0.2030   0.6774   0.0681
  -3.500   0.5525   0.01642   0.00845  -0.2045   0.6717   0.0704
  -3.250   0.5870   0.01618   0.00807  -0.2061   0.6671   0.0733
  -3.000   0.6232   0.01592   0.00767  -0.2082   0.6633   0.0792
  -2.750   0.6579   0.01567   0.00746  -0.2100   0.6588   0.0946
  -2.500   0.7005   0.01490   0.00766  -0.2144   0.6546   0.3957
  -2.250   0.7281   0.01552   0.00818  -0.2138   0.6510   0.4386
  -2.000   0.7540   0.01622   0.00883  -0.2127   0.6478   0.4577
  -1.750   0.7792   0.01685   0.00948  -0.2117   0.6440   0.4733
  -1.500   0.8047   0.01732   0.00997  -0.2109   0.6402   0.4825
  -1.250   0.8313   0.01774   0.01036  -0.2103   0.6369   0.4919
  -1.000   0.8586   0.01814   0.01070  -0.2099   0.6341   0.5013
  -0.750   0.8830   0.01869   0.01124  -0.2087   0.6315   0.5104
  -0.500   0.9104   0.01907   0.01163  -0.2086   0.6285   0.5222
  -0.250   0.9335   0.01945   0.01210  -0.2073   0.6250   0.5277
   0.000   0.9640   0.01959   0.01218  -0.2081   0.6218   0.5344
   0.250   0.9937   0.01970   0.01222  -0.2086   0.6186   0.5394
   0.500   1.0223   0.01989   0.01230  -0.2086   0.6148   0.5426
   0.750   1.0494   0.01994   0.01241  -0.2088   0.6090   0.5462
   1.000   1.0802   0.01991   0.01227  -0.2096   0.6030   0.5506
   1.250   1.1121   0.01996   0.01214  -0.2106   0.5983   0.5548
   1.500   1.1368   0.02010   0.01240  -0.2101   0.5934   0.5580
   1.750   1.1642   0.02023   0.01256  -0.2101   0.5891   0.5623
   2.000   1.1950   0.02030   0.01256  -0.2110   0.5854   0.5665
   2.250   1.2279   0.02041   0.01251  -0.2124   0.5821   0.5697
   2.500   1.2546   0.02055   0.01274  -0.2125   0.5784   0.5714
   2.750   1.2815   0.02068   0.01295  -0.2126   0.5743   0.5735
   3.000   1.3096   0.02079   0.01306  -0.2128   0.5703   0.5762
   3.250   1.3397   0.02088   0.01309  -0.2134   0.5667   0.5796
   3.500   1.3683   0.02106   0.01327  -0.2139   0.5627   0.5828
   3.750   1.3956   0.02120   0.01347  -0.2142   0.5578   0.5858
   4.000   1.4230   0.02127   0.01358  -0.2143   0.5536   0.5880
   4.250   1.4523   0.02135   0.01362  -0.2147   0.5499   0.5906
   4.500   1.4782   0.02156   0.01391  -0.2146   0.5454   0.5936
   4.750   1.5036   0.02170   0.01415  -0.2145   0.5402   0.5973
   5.000   1.5327   0.02176   0.01416  -0.2149   0.5355   0.6016
   5.250   1.5603   0.02184   0.01425  -0.2150   0.5309   0.6045
   5.500   1.5824   0.02199   0.01457  -0.2142   0.5245   0.6076
   5.750   1.6096   0.02198   0.01457  -0.2142   0.5190   0.6112
   6.000   1.6356   0.02210   0.01471  -0.2141   0.5133   0.6152
   6.250   1.6583   0.02221   0.01494  -0.2134   0.5063   0.6187
   6.500   1.6853   0.02218   0.01490  -0.2133   0.5006   0.6224
   6.750   1.7046   0.02236   0.01525  -0.2120   0.4924   0.6267
   7.000   1.7294   0.02233   0.01519  -0.2116   0.4847   0.6318
   7.250   1.7463   0.02246   0.01549  -0.2098   0.4742   0.6355
   7.500   1.7639   0.02251   0.01560  -0.2081   0.4628   0.6394
   7.750   1.7793   0.02264   0.01574  -0.2060   0.4498   0.6438
   8.000   1.7919   0.02292   0.01605  -0.2036   0.4351   0.6485
   8.250   1.8005   0.02333   0.01653  -0.2005   0.4191   0.6523
   8.500   1.8022   0.02393   0.01714  -0.1963   0.4030   0.6566
   8.750   1.8052   0.02481   0.01798  -0.1927   0.3858   0.6617
   9.000   1.8074   0.02595   0.01906  -0.1892   0.3696   0.6663
   9.250   1.8089   0.02729   0.02034  -0.1860   0.3552   0.6708
   9.500   1.8107   0.02878   0.02179  -0.1830   0.3428   0.6759
   9.750   1.8126   0.03040   0.02336  -0.1803   0.3316   0.6810
  10.000   1.8166   0.03195   0.02496  -0.1779   0.3215   0.6861
  10.250   1.8193   0.03366   0.02665  -0.1756   0.3130   0.6923
  10.500   1.8225   0.03540   0.02845  -0.1734   0.3040   0.6986
  10.750   1.8248   0.03725   0.03034  -0.1713   0.2959   0.7056
  11.000   1.8280   0.03911   0.03227  -0.1694   0.2885   0.7132
  11.250   1.8299   0.04110   0.03431  -0.1674   0.2816   0.7214
  11.500   1.8319   0.04317   0.03649  -0.1658   0.2740   0.7303
  11.750   1.8314   0.04549   0.03884  -0.1639   0.2671   0.7406
  12.000   1.8326   0.04779   0.04130  -0.1625   0.2593   0.7532
  12.250   1.8307   0.05042   0.04400  -0.1610   0.2524   0.7712
  12.500   1.8274   0.05284   0.04672  -0.1593   0.2442   0.9210
  12.750   1.8241   0.05592   0.04981  -0.1581   0.2370   1.0000
  13.000   1.8237   0.05893   0.05292  -0.1573   0.2285   1.0000
  13.250   1.8197   0.06235   0.05638  -0.1565   0.2202   1.0000
  13.500   1.8148   0.06595   0.06003  -0.1557   0.2108   1.0000
  13.750   1.8074   0.06996   0.06408  -0.1551   0.1982   1.0000
  14.000   1.7989   0.07415   0.06829  -0.1545   0.1843   1.0000
  14.250   1.7851   0.07908   0.07317  -0.1540   0.1642   1.0000
  14.500   1.7571   0.08587   0.07977  -0.1535   0.1265   1.0000
  14.750   1.7261   0.09320   0.08689  -0.1533   0.0939   1.0000
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