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GOE 242 (MVA PR.2) AIRFOIL (goe242-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 242 (MVA PR.2) AIRFOIL (goe242-il)
Reynolds number: 200,000
Max Cl/Cd: 80.76 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe242-il-200000-n5.txt
Download as CSV file: xf-goe242-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.0395   0.10574   0.10176  -0.0866   0.8449   0.0216
 -10.500  -0.0348   0.10202   0.09802  -0.0883   0.8362   0.0217
 -10.250  -0.0364   0.09643   0.09240  -0.0915   0.8288   0.0223
 -10.000  -0.0258   0.09469   0.09064  -0.0919   0.8191   0.0232
  -9.750  -0.0173   0.09217   0.08808  -0.0929   0.8099   0.0238
  -9.500  -0.0160   0.08739   0.08327  -0.0955   0.8009   0.0234
  -9.250  -0.0155   0.08240   0.07827  -0.0983   0.7919   0.0232
  -9.000  -0.0137   0.07791   0.07375  -0.1008   0.7822   0.0233
  -8.750  -0.0113   0.07351   0.06933  -0.1036   0.7717   0.0234
  -8.500  -0.0087   0.06919   0.06498  -0.1065   0.7612   0.0238
  -8.250  -0.0093   0.06369   0.05946  -0.1106   0.7503   0.0245
  -8.000  -0.0454   0.04383   0.03927  -0.1373   0.7414   0.0241
  -7.750  -0.0100   0.03562   0.03048  -0.1589   0.7289   0.0252
  -7.500   0.0382   0.02984   0.02386  -0.1742   0.7167   0.0265
  -7.250   0.0796   0.02677   0.02015  -0.1816   0.7043   0.0280
  -7.000   0.1096   0.02559   0.01887  -0.1835   0.6929   0.0291
  -6.750   0.1423   0.02433   0.01735  -0.1859   0.6824   0.0303
  -6.500   0.1764   0.02296   0.01565  -0.1884   0.6724   0.0314
  -6.250   0.2104   0.02196   0.01430  -0.1905   0.6636   0.0329
  -6.000   0.2433   0.02100   0.01304  -0.1923   0.6552   0.0342
  -5.750   0.2733   0.02003   0.01200  -0.1932   0.6479   0.0351
  -5.500   0.3039   0.01934   0.01121  -0.1941   0.6409   0.0360
  -5.250   0.3347   0.01883   0.01057  -0.1951   0.6351   0.0375
  -5.000   0.3659   0.01835   0.01001  -0.1960   0.6295   0.0390
  -4.750   0.3971   0.01791   0.00947  -0.1969   0.6244   0.0399
  -4.500   0.4286   0.01755   0.00900  -0.1979   0.6201   0.0406
  -4.250   0.4607   0.01723   0.00861  -0.1990   0.6158   0.0414
  -4.000   0.4955   0.01670   0.00809  -0.2011   0.6114   0.0433
  -3.750   0.5299   0.01638   0.00770  -0.2029   0.6075   0.0450
  -3.500   0.5639   0.01615   0.00734  -0.2046   0.6040   0.0463
  -3.250   0.5974   0.01596   0.00703  -0.2061   0.6004   0.0478
  -3.000   0.6302   0.01580   0.00679  -0.2074   0.5965   0.0495
  -2.750   0.6629   0.01567   0.00657  -0.2086   0.5930   0.0523
  -2.500   0.6954   0.01556   0.00641  -0.2098   0.5900   0.0586
  -2.250   0.7346   0.01496   0.00616  -0.2132   0.5872   0.1917
  -2.000   0.7704   0.01460   0.00628  -0.2156   0.5846   0.3510
  -1.750   0.7996   0.01477   0.00649  -0.2158   0.5818   0.3942
  -1.500   0.8285   0.01497   0.00664  -0.2160   0.5791   0.4144
  -1.250   0.8571   0.01521   0.00684  -0.2160   0.5763   0.4315
  -1.000   0.8854   0.01547   0.00704  -0.2160   0.5736   0.4446
  -0.750   0.9146   0.01566   0.00712  -0.2163   0.5711   0.4528
  -0.250   0.9709   0.01621   0.00761  -0.2163   0.5666   0.4730
   0.000   0.9984   0.01642   0.00787  -0.2162   0.5642   0.4780
   0.250   1.0272   0.01656   0.00799  -0.2165   0.5616   0.4814
   0.500   1.0560   0.01667   0.00804  -0.2168   0.5580   0.4852
   0.750   1.0851   0.01678   0.00802  -0.2172   0.5538   0.4886
   1.000   1.1126   0.01688   0.00813  -0.2172   0.5488   0.4904
   1.250   1.1395   0.01699   0.00826  -0.2171   0.5433   0.4931
   1.500   1.1669   0.01711   0.00836  -0.2171   0.5385   0.4968
   1.750   1.1947   0.01727   0.00844  -0.2172   0.5342   0.5011
   2.000   1.2224   0.01738   0.00856  -0.2173   0.5296   0.5048
   2.250   1.2496   0.01750   0.00872  -0.2174   0.5257   0.5067
   2.500   1.2769   0.01763   0.00885  -0.2174   0.5223   0.5085
   2.750   1.3044   0.01779   0.00899  -0.2175   0.5194   0.5105
   3.000   1.3315   0.01795   0.00920  -0.2175   0.5162   0.5128
   3.250   1.3582   0.01810   0.00941  -0.2175   0.5125   0.5153
   3.500   1.3849   0.01825   0.00959  -0.2175   0.5085   0.5183
   3.750   1.4118   0.01842   0.00973  -0.2175   0.5047   0.5216
   4.000   1.4379   0.01859   0.00993  -0.2174   0.5009   0.5238
   4.250   1.4632   0.01876   0.01023  -0.2171   0.4961   0.5261
   4.500   1.4885   0.01894   0.01047  -0.2168   0.4915   0.5285
   4.750   1.5140   0.01912   0.01066  -0.2166   0.4873   0.5313
   5.000   1.5389   0.01933   0.01095  -0.2163   0.4826   0.5343
   5.250   1.5632   0.01954   0.01123  -0.2159   0.4771   0.5375
   5.500   1.5871   0.01974   0.01147  -0.2154   0.4719   0.5401
   5.750   1.6102   0.01997   0.01181  -0.2147   0.4660   0.5429
   6.000   1.6324   0.02022   0.01215  -0.2140   0.4590   0.5461
   6.250   1.6540   0.02048   0.01246  -0.2131   0.4519   0.5496
   6.500   1.6745   0.02077   0.01283  -0.2120   0.4429   0.5531
   6.750   1.6938   0.02109   0.01323  -0.2108   0.4335   0.5560
   7.000   1.7106   0.02147   0.01365  -0.2091   0.4222   0.5587
   7.250   1.7244   0.02194   0.01415  -0.2069   0.4072   0.5617
   7.500   1.7308   0.02255   0.01474  -0.2035   0.3896   0.5649
   7.750   1.7335   0.02348   0.01559  -0.1997   0.3696   0.5684
   8.000   1.7338   0.02477   0.01678  -0.1959   0.3501   0.5717
   8.250   1.7330   0.02628   0.01822  -0.1923   0.3330   0.5743
   8.500   1.7327   0.02795   0.01983  -0.1891   0.3178   0.5773
   8.750   1.7335   0.02967   0.02153  -0.1862   0.3042   0.5806
   9.000   1.7360   0.03141   0.02326  -0.1837   0.2929   0.5841
   9.250   1.7373   0.03331   0.02516  -0.1813   0.2835   0.5875
   9.500   1.7420   0.03502   0.02694  -0.1794   0.2744   0.5905
   9.750   1.7444   0.03697   0.02893  -0.1773   0.2672   0.5939
  10.000   1.7486   0.03884   0.03088  -0.1755   0.2591   0.5980
  10.250   1.7487   0.04113   0.03319  -0.1736   0.2513   0.6023
  10.500   1.7503   0.04335   0.03547  -0.1719   0.2424   0.6060
  10.750   1.7493   0.04587   0.03804  -0.1701   0.2344   0.6098
  11.000   1.7491   0.04841   0.04064  -0.1686   0.2258   0.6142
  11.250   1.7484   0.05110   0.04339  -0.1672   0.2179   0.6187
  11.500   1.7465   0.05400   0.04635  -0.1659   0.2090   0.6225
  11.750   1.7455   0.05691   0.04932  -0.1647   0.1995   0.6268
  12.000   1.7414   0.06024   0.05268  -0.1636   0.1886   0.6315
  12.250   1.7359   0.06383   0.05628  -0.1626   0.1742   0.6362
  12.500   1.7213   0.06857   0.06094  -0.1615   0.1485   0.6399
  12.750   1.6921   0.07521   0.06735  -0.1602   0.1038   0.6423
  13.000   1.6663   0.08152   0.07350  -0.1592   0.0801   0.6452
  13.250   1.6517   0.08653   0.07851  -0.1585   0.0675   0.6496
  13.500   1.6440   0.09077   0.08281  -0.1580   0.0579   0.6550
  13.750   1.6382   0.09482   0.08695  -0.1578   0.0486   0.6613
  14.250   1.6101   0.10547   0.09759  -0.1578   0.0204   0.6723
  14.500   1.6020   0.11013   0.10236  -0.1581   0.0185   0.6800
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