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GOE 227 (MVA H.37) AIRFOIL (goe227-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 227 (MVA H.37) AIRFOIL (goe227-il)
Reynolds number: 500,000
Max Cl/Cd: 131.66 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe227-il-500000.txt
Download as CSV file: xf-goe227-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 227 (MVA H.37) 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.0159   0.09750   0.09446  -0.0979   0.8356   0.0441
  -9.750  -0.0065   0.09510   0.09201  -0.0990   0.8276   0.0454
  -9.500  -0.1831   0.02583   0.02170  -0.1860   0.8183   0.0416
  -9.250  -0.1481   0.02212   0.01751  -0.1939   0.8103   0.0425
  -9.000  -0.1183   0.02086   0.01613  -0.1961   0.8027   0.0433
  -8.750  -0.0888   0.02031   0.01552  -0.1974   0.7937   0.0441
  -8.500  -0.0585   0.01966   0.01473  -0.1988   0.7849   0.0451
  -8.250  -0.0277   0.01873   0.01362  -0.2005   0.7750   0.0461
  -8.000   0.0035   0.01778   0.01245  -0.2022   0.7648   0.0472
  -7.750   0.0344   0.01704   0.01147  -0.2036   0.7548   0.0481
  -7.500   0.0655   0.01586   0.01012  -0.2053   0.7439   0.0494
  -7.250   0.0954   0.01546   0.00966  -0.2060   0.7343   0.0505
  -7.000   0.1252   0.01522   0.00933  -0.2067   0.7250   0.0519
  -6.750   0.1555   0.01489   0.00888  -0.2074   0.7170   0.0535
  -6.500   0.1860   0.01454   0.00836  -0.2082   0.7096   0.0550
  -6.250   0.2170   0.01388   0.00757  -0.2093   0.7038   0.0567
  -6.000   0.2473   0.01360   0.00727  -0.2100   0.6985   0.0585
  -5.750   0.2774   0.01343   0.00703  -0.2106   0.6939   0.0605
  -5.500   0.3077   0.01330   0.00676  -0.2111   0.6901   0.0628
  -5.250   0.3387   0.01290   0.00629  -0.2120   0.6867   0.0652
  -5.000   0.3691   0.01265   0.00605  -0.2127   0.6828   0.0678
  -4.750   0.3992   0.01253   0.00586  -0.2132   0.6788   0.0704
  -4.500   0.4292   0.01246   0.00567  -0.2137   0.6747   0.0729
  -4.250   0.4602   0.01208   0.00525  -0.2146   0.6713   0.0761
  -4.000   0.4906   0.01192   0.00510  -0.2152   0.6681   0.0793
  -3.750   0.5208   0.01181   0.00496  -0.2157   0.6653   0.0824
  -3.500   0.5509   0.01177   0.00483  -0.2161   0.6626   0.0848
  -3.250   0.5820   0.01148   0.00451  -0.2170   0.6596   0.0890
  -3.000   0.6123   0.01144   0.00443  -0.2176   0.6564   0.0925
  -2.750   0.6424   0.01135   0.00434  -0.2180   0.6540   0.0961
  -2.500   0.6729   0.01122   0.00419  -0.2186   0.6518   0.0996
  -2.250   0.7035   0.01110   0.00409  -0.2193   0.6494   0.1047
  -2.000   0.7334   0.01107   0.00403  -0.2197   0.6468   0.1095
  -1.750   0.7637   0.01101   0.00394  -0.2202   0.6441   0.1152
  -1.500   0.7940   0.01101   0.00393  -0.2208   0.6417   0.1236
  -1.250   0.8245   0.01097   0.00390  -0.2214   0.6392   0.1360
  -1.000   0.8547   0.01084   0.00384  -0.2220   0.6366   0.1574
  -0.750   0.8860   0.01055   0.00385  -0.2230   0.6336   0.2562
  -0.500   0.9153   0.01058   0.00396  -0.2233   0.6308   0.3055
  -0.250   0.9444   0.01066   0.00404  -0.2236   0.6284   0.3250
   0.000   0.9735   0.01076   0.00413  -0.2238   0.6259   0.3396
   0.250   1.0029   0.01094   0.00426  -0.2241   0.6229   0.3514
   0.500   1.0314   0.01098   0.00433  -0.2242   0.6205   0.3622
   0.750   1.0600   0.01101   0.00441  -0.2244   0.6176   0.3710
   1.000   1.0885   0.01108   0.00449  -0.2245   0.6147   0.3803
   1.250   1.1172   0.01113   0.00456  -0.2247   0.6118   0.3893
   1.500   1.1458   0.01123   0.00464  -0.2248   0.6087   0.3983
   1.750   1.1747   0.01138   0.00479  -0.2251   0.6051   0.4090
   2.000   1.2024   0.01139   0.00486  -0.2251   0.6019   0.4189
   2.250   1.2303   0.01140   0.00495  -0.2251   0.5981   0.4294
   2.500   1.2583   0.01144   0.00503  -0.2252   0.5944   0.4411
   2.750   1.2863   0.01152   0.00511  -0.2252   0.5905   0.4538
   3.000   1.3141   0.01160   0.00524  -0.2253   0.5863   0.4690
   3.250   1.3410   0.01159   0.00534  -0.2251   0.5814   0.4875
   3.500   1.3680   0.01161   0.00543  -0.2250   0.5763   0.5094
   3.750   1.3952   0.01170   0.00554  -0.2249   0.5713   0.5333
   4.000   1.4215   0.01170   0.00566  -0.2246   0.5653   0.5567
   4.250   1.4475   0.01171   0.00574  -0.2243   0.5581   0.5786
   4.500   1.4733   0.01175   0.00584  -0.2240   0.5501   0.6006
   4.750   1.4982   0.01178   0.00593  -0.2234   0.5394   0.6239
   5.000   1.5228   0.01180   0.00605  -0.2229   0.5252   0.6527
   5.250   1.5449   0.01188   0.00623  -0.2219   0.5051   0.7078
   5.500   1.5589   0.01184   0.00641  -0.2191   0.4801   1.0000
   5.750   1.5757   0.01239   0.00679  -0.2172   0.4585   1.0000
   6.000   1.5930   0.01295   0.00723  -0.2154   0.4429   1.0000
   6.250   1.6114   0.01345   0.00765  -0.2138   0.4312   1.0000
   6.500   1.6296   0.01394   0.00810  -0.2122   0.4217   1.0000
   6.750   1.6443   0.01450   0.00859  -0.2099   0.4122   1.0000
   7.000   1.6609   0.01495   0.00903  -0.2080   0.4032   1.0000
   7.500   1.6926   0.01599   0.01004  -0.2041   0.3873   1.0000
   7.750   1.7074   0.01658   0.01060  -0.2021   0.3802   1.0000
   8.000   1.7241   0.01710   0.01114  -0.2004   0.3734   1.0000
   8.250   1.7399   0.01766   0.01171  -0.1986   0.3662   1.0000
   8.500   1.7536   0.01836   0.01240  -0.1966   0.3595   1.0000
   8.750   1.7700   0.01892   0.01300  -0.1951   0.3517   1.0000
   9.000   1.7813   0.01979   0.01383  -0.1928   0.3439   1.0000
   9.250   1.7979   0.02039   0.01449  -0.1914   0.3363   1.0000
   9.750   1.8228   0.02214   0.01627  -0.1876   0.3191   1.0000
  10.000   1.8322   0.02327   0.01738  -0.1854   0.3082   1.0000
  10.250   1.8392   0.02460   0.01868  -0.1831   0.2957   1.0000
  10.500   1.8450   0.02607   0.02011  -0.1808   0.2806   1.0000
  10.750   1.8477   0.02785   0.02183  -0.1782   0.2600   1.0000
  11.000   1.8407   0.03042   0.02427  -0.1748   0.2328   1.0000
  11.250   1.8246   0.03385   0.02748  -0.1708   0.1968   1.0000
  11.500   1.7999   0.03819   0.03156  -0.1665   0.1552   1.0000
  11.750   1.7759   0.04277   0.03593  -0.1626   0.1221   1.0000
  12.000   1.7563   0.04721   0.04021  -0.1595   0.0937   1.0000
  12.250   1.7282   0.05280   0.04557  -0.1564   0.0520   1.0000
  12.500   1.7121   0.05738   0.05011  -0.1542   0.0372   1.0000
  12.750   1.7078   0.06075   0.05354  -0.1528   0.0327   1.0000
  13.000   1.7041   0.06412   0.05697  -0.1515   0.0301   1.0000
  13.250   1.7036   0.06715   0.06009  -0.1504   0.0285   1.0000
  13.500   1.7005   0.07051   0.06352  -0.1494   0.0271   1.0000
  13.750   1.6941   0.07432   0.06741  -0.1483   0.0259   1.0000
  14.000   1.6917   0.07771   0.07089  -0.1474   0.0250   1.0000
  14.250   1.6900   0.08103   0.07430  -0.1467   0.0242   1.0000
  14.500   1.6868   0.08457   0.07793  -0.1460   0.0234   1.0000
  14.750   1.6817   0.08841   0.08186  -0.1454   0.0228   1.0000
  15.000   1.6747   0.09257   0.08611  -0.1449   0.0223   1.0000
  15.250   1.6645   0.09727   0.09091  -0.1445   0.0217   1.0000
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