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GOE 225 (MVA H.35) AIRFOIL (goe225-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 225 (MVA H.35) AIRFOIL (goe225-il)
Reynolds number: 500,000
Max Cl/Cd: 116.58 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe225-il-500000.txt
Download as CSV file: xf-goe225-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 225 (MVA H.35) AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.0130   0.08825   0.08536  -0.0996   0.8788   0.0413
  -8.750  -0.0022   0.08602   0.08311  -0.1007   0.8757   0.0423
  -8.000  -0.0109   0.02247   0.01813  -0.1947   0.8610   0.0371
  -7.750   0.0237   0.02031   0.01561  -0.1986   0.8584   0.0373
  -7.500   0.0565   0.01886   0.01389  -0.2010   0.8560   0.0377
  -7.250   0.0885   0.01773   0.01257  -0.2028   0.8534   0.0381
  -7.000   0.1200   0.01688   0.01155  -0.2041   0.8503   0.0387
  -6.750   0.1512   0.01617   0.01069  -0.2052   0.8471   0.0392
  -6.500   0.1822   0.01552   0.00989  -0.2061   0.8440   0.0395
  -6.250   0.2137   0.01460   0.00884  -0.2072   0.8414   0.0400
  -6.000   0.2448   0.01389   0.00806  -0.2081   0.8389   0.0407
  -5.750   0.2757   0.01342   0.00756  -0.2090   0.8363   0.0414
  -5.500   0.3065   0.01300   0.00713  -0.2097   0.8336   0.0422
  -5.250   0.3374   0.01263   0.00671  -0.2104   0.8304   0.0431
  -5.000   0.3682   0.01228   0.00631  -0.2110   0.8272   0.0442
  -4.750   0.3989   0.01200   0.00596  -0.2115   0.8241   0.0453
  -4.500   0.4304   0.01162   0.00553  -0.2123   0.8212   0.0473
  -4.250   0.4610   0.01136   0.00527  -0.2129   0.8180   0.0492
  -4.000   0.4915   0.01112   0.00500  -0.2133   0.8141   0.0517
  -3.750   0.5222   0.01084   0.00472  -0.2138   0.8100   0.0567
  -3.500   0.5529   0.01061   0.00452  -0.2143   0.8063   0.0691
  -3.250   0.5825   0.01060   0.00452  -0.2144   0.8027   0.0875
  -3.000   0.6118   0.01051   0.00447  -0.2146   0.7981   0.0977
  -2.750   0.6413   0.01040   0.00434  -0.2148   0.7930   0.1045
  -2.500   0.6711   0.01027   0.00417  -0.2150   0.7883   0.1105
  -2.250   0.7005   0.01021   0.00407  -0.2152   0.7834   0.1150
  -2.000   0.7302   0.01001   0.00390  -0.2155   0.7772   0.1214
  -1.750   0.7598   0.00986   0.00373  -0.2157   0.7712   0.1275
  -1.500   0.7891   0.00975   0.00360  -0.2158   0.7641   0.1331
  -1.250   0.8186   0.00957   0.00345  -0.2161   0.7559   0.1429
  -1.000   0.8480   0.00941   0.00333  -0.2163   0.7469   0.1586
  -0.750   0.8775   0.00918   0.00326  -0.2166   0.7360   0.2252
  -0.500   0.9059   0.00911   0.00326  -0.2166   0.7208   0.2703
  -0.250   0.9336   0.00911   0.00322  -0.2164   0.7005   0.2904
   0.000   0.9600   0.00921   0.00318  -0.2159   0.6726   0.3043
   0.250   0.9852   0.00944   0.00323  -0.2152   0.6417   0.3164
   0.500   1.0104   0.00971   0.00335  -0.2146   0.6170   0.3278
   0.750   1.0361   0.00997   0.00350  -0.2142   0.5987   0.3398
   1.000   1.0622   0.01020   0.00366  -0.2138   0.5849   0.3502
   1.250   1.0883   0.01042   0.00382  -0.2134   0.5732   0.3611
   1.500   1.1151   0.01059   0.00397  -0.2132   0.5636   0.3743
   1.750   1.1413   0.01082   0.00416  -0.2129   0.5550   0.3876
   2.000   1.1683   0.01095   0.00432  -0.2127   0.5466   0.4032
   2.500   1.2204   0.01134   0.00471  -0.2120   0.5284   0.4407
   2.750   1.2459   0.01159   0.00492  -0.2115   0.5206   0.4622
   3.000   1.2726   0.01172   0.00511  -0.2113   0.5143   0.4827
   3.250   1.2986   0.01190   0.00531  -0.2109   0.5079   0.5027
   3.500   1.3238   0.01216   0.00555  -0.2104   0.5019   0.5219
   3.750   1.3504   0.01226   0.00573  -0.2102   0.4966   0.5398
   4.000   1.3761   0.01244   0.00593  -0.2098   0.4906   0.5559
   4.250   1.4008   0.01269   0.00617  -0.2092   0.4849   0.5716
   4.500   1.4269   0.01280   0.00636  -0.2089   0.4799   0.5876
   4.750   1.4522   0.01295   0.00657  -0.2085   0.4742   0.6042
   5.000   1.4763   0.01318   0.00681  -0.2078   0.4685   0.6233
   5.250   1.5014   0.01329   0.00704  -0.2074   0.4627   0.6502
   5.500   1.5225   0.01306   0.00727  -0.2060   0.4568   0.8586
   5.750   1.5438   0.01328   0.00747  -0.2047   0.4511   1.0000
   6.000   1.5678   0.01347   0.00769  -0.2041   0.4446   1.0000
   6.250   1.5898   0.01374   0.00794  -0.2030   0.4367   1.0000
   6.500   1.6114   0.01401   0.00821  -0.2019   0.4285   1.0000
   6.750   1.6317   0.01431   0.00849  -0.2005   0.4198   1.0000
   7.000   1.6518   0.01461   0.00880  -0.1991   0.4117   1.0000
   7.250   1.6693   0.01496   0.00914  -0.1973   0.4028   1.0000
   7.500   1.6868   0.01532   0.00951  -0.1954   0.3938   1.0000
   7.750   1.7023   0.01580   0.00996  -0.1933   0.3840   1.0000
   8.000   1.7199   0.01623   0.01040  -0.1916   0.3728   1.0000
   8.250   1.7348   0.01679   0.01094  -0.1895   0.3600   1.0000
   8.500   1.7488   0.01744   0.01155  -0.1873   0.3466   1.0000
   8.750   1.7618   0.01817   0.01223  -0.1850   0.3317   1.0000
   9.000   1.7731   0.01903   0.01303  -0.1826   0.3137   1.0000
   9.250   1.7827   0.02005   0.01396  -0.1800   0.2940   1.0000
   9.500   1.7914   0.02116   0.01498  -0.1774   0.2758   1.0000
   9.750   1.8007   0.02227   0.01603  -0.1750   0.2602   1.0000
  10.000   1.8103   0.02340   0.01711  -0.1727   0.2465   1.0000
  10.250   1.8198   0.02456   0.01823  -0.1704   0.2346   1.0000
  10.500   1.8282   0.02582   0.01946  -0.1681   0.2236   1.0000
  10.750   1.8379   0.02701   0.02065  -0.1660   0.2134   1.0000
  11.000   1.8472   0.02826   0.02188  -0.1639   0.2038   1.0000
  11.250   1.8536   0.02973   0.02332  -0.1616   0.1939   1.0000
  11.500   1.8624   0.03105   0.02467  -0.1597   0.1842   1.0000
  11.750   1.8693   0.03254   0.02615  -0.1575   0.1741   1.0000
  12.000   1.8735   0.03427   0.02785  -0.1552   0.1631   1.0000
  12.250   1.8759   0.03618   0.02973  -0.1529   0.1501   1.0000
  12.500   1.8761   0.03835   0.03184  -0.1504   0.1330   1.0000
  12.750   1.8665   0.04146   0.03480  -0.1473   0.1069   1.0000
  13.250   1.8295   0.04993   0.04298  -0.1408   0.0597   1.0000
  13.500   1.8233   0.05322   0.04631  -0.1388   0.0549   1.0000
  13.750   1.8195   0.05639   0.04955  -0.1372   0.0512   1.0000
  14.000   1.8162   0.05961   0.05286  -0.1358   0.0483   1.0000
  14.250   1.8087   0.06344   0.05676  -0.1345   0.0458   1.0000
  14.500   1.8060   0.06678   0.06020  -0.1335   0.0436   1.0000
  14.750   1.8030   0.07024   0.06375  -0.1326   0.0414   1.0000
  15.000   1.7953   0.07440   0.06799  -0.1319   0.0395   1.0000
  15.250   1.7870   0.07875   0.07244  -0.1314   0.0378   1.0000
  15.500   1.7848   0.08228   0.07608  -0.1310   0.0360   1.0000
  15.750   1.7788   0.08639   0.08026  -0.1307   0.0345   1.0000
  16.000   1.7683   0.09120   0.08515  -0.1307   0.0332   1.0000
  16.250   1.7597   0.09578   0.08983  -0.1307   0.0319   1.0000
  16.500   1.7559   0.09968   0.09383  -0.1308   0.0306   1.0000
  16.750   1.7499   0.10390   0.09814  -0.1310   0.0295   1.0000
  17.000   1.7409   0.10862   0.10293  -0.1314   0.0286   1.0000
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