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GOE 225 (MVA H.35) AIRFOIL (goe225-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 225 (MVA H.35) AIRFOIL (goe225-il)
Reynolds number: 100,000
Max Cl/Cd: 59.28 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe225-il-100000.txt
Download as CSV file: xf-goe225-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.000  -0.2323   0.11368   0.10920  -0.0414   0.9642   0.1113
  -6.750  -0.2415   0.11332   0.10888  -0.0467   0.9560   0.1147
  -6.500  -0.2436   0.11095   0.10656  -0.0554   0.9446   0.1160
  -6.250  -0.2163   0.10572   0.10130  -0.0518   0.9418   0.1176
  -6.000  -0.1989   0.10275   0.09832  -0.0511   0.9349   0.1199
  -5.750  -0.1798   0.09992   0.09548  -0.0536   0.9274   0.1244
  -5.500  -0.1633   0.09660   0.09214  -0.0715   0.9133   0.1317
  -5.250  -0.1424   0.09280   0.08834  -0.0670   0.9094   0.1336
  -5.000  -0.1276   0.09038   0.08592  -0.0660   0.9006   0.1363
  -4.750  -0.0983   0.08714   0.08264  -0.0715   0.8929   0.1428
  -4.500  -0.0722   0.08299   0.07846  -0.0820   0.8816   0.1493
  -4.250  -0.0091   0.07828   0.07359  -0.1009   0.8750   0.1640
  -3.750   0.2096   0.04408   0.03779  -0.1676   0.8743   0.1043
  -3.500   0.2576   0.04122   0.03452  -0.1742   0.8661   0.1072
  -3.250   0.3200   0.03808   0.03065  -0.1826   0.8613   0.1125
  -3.000   0.3801   0.03559   0.02768  -0.1893   0.8582   0.1200
  -2.750   0.2108   0.05716   0.05209  -0.1314   0.8279   0.1882
  -2.500   0.4641   0.03326   0.02513  -0.1948   0.8433   0.1539
  -2.250   0.5157   0.03224   0.02401  -0.1987   0.8399   0.1817
  -2.000   0.5408   0.03229   0.02414  -0.1981   0.8280   0.1998
  -1.750   0.5863   0.03183   0.02375  -0.2006   0.8236   0.2250
  -1.500   0.6195   0.03146   0.02337  -0.2012   0.8146   0.2394
  -1.250   0.6602   0.03077   0.02264  -0.2029   0.8081   0.2577
  -1.000   0.7081   0.02969   0.02151  -0.2055   0.8053   0.2847
  -0.750   0.7313   0.02967   0.02161  -0.2044   0.7930   0.3130
  -0.500   0.7736   0.02882   0.02089  -0.2058   0.7890   0.3633
  -0.250   0.7978   0.02890   0.02102  -0.2047   0.7781   0.3960
   0.000   0.8350   0.02839   0.02048  -0.2053   0.7727   0.4281
   0.250   0.8758   0.02759   0.01971  -0.2063   0.7696   0.4522
   0.500   0.8950   0.02785   0.01997  -0.2046   0.7566   0.4685
   0.750   0.9356   0.02702   0.01912  -0.2057   0.7532   0.4910
   1.000   0.9541   0.02735   0.01948  -0.2040   0.7407   0.5090
   1.250   0.9945   0.02650   0.01858  -0.2052   0.7370   0.5339
   1.500   1.0139   0.02677   0.01890  -0.2037   0.7252   0.5512
   1.750   1.0532   0.02588   0.01800  -0.2048   0.7210   0.5731
   2.000   1.0743   0.02612   0.01827  -0.2037   0.7100   0.5901
   2.250   1.1139   0.02527   0.01736  -0.2051   0.7052   0.6114
   2.500   1.1363   0.02547   0.01755  -0.2042   0.6952   0.6325
   2.750   1.1729   0.02469   0.01678  -0.2051   0.6897   0.6612
   3.000   1.1964   0.02473   0.01690  -0.2042   0.6805   0.6922
   3.250   1.2293   0.02399   0.01629  -0.2045   0.6742   0.7451
   3.500   1.2498   0.02378   0.01631  -0.2029   0.6655   1.0000
   3.750   1.2860   0.02361   0.01597  -0.2042   0.6581   1.0000
   4.000   1.3135   0.02389   0.01615  -0.2041   0.6489   1.0000
   4.250   1.3493   0.02362   0.01572  -0.2050   0.6407   1.0000
   4.500   1.3724   0.02406   0.01612  -0.2041   0.6301   1.0000
   4.750   1.4109   0.02380   0.01565  -0.2054   0.6224   1.0000
   5.000   1.4290   0.02451   0.01642  -0.2038   0.6116   1.0000
   5.250   1.4607   0.02468   0.01648  -0.2042   0.6033   1.0000
   5.500   1.4831   0.02523   0.01703  -0.2033   0.5935   1.0000
   5.750   1.5103   0.02564   0.01741  -0.2030   0.5846   1.0000
   6.000   1.5354   0.02610   0.01785  -0.2025   0.5753   1.0000
   6.250   1.5587   0.02670   0.01846  -0.2017   0.5661   1.0000
   6.500   1.5861   0.02709   0.01880  -0.2014   0.5570   1.0000
   6.750   1.6053   0.02783   0.01963  -0.2000   0.5472   1.0000
   7.000   1.6361   0.02812   0.01983  -0.2003   0.5382   1.0000
   7.250   1.6502   0.02899   0.02084  -0.1981   0.5278   1.0000
   7.500   1.6833   0.02927   0.02101  -0.1987   0.5190   1.0000
   7.750   1.6939   0.03016   0.02210  -0.1959   0.5081   1.0000
   8.000   1.7180   0.03069   0.02262  -0.1952   0.4982   1.0000
   8.250   1.7384   0.03120   0.02318  -0.1938   0.4875   1.0000
   8.500   1.7518   0.03198   0.02408  -0.1914   0.4763   1.0000
   8.750   1.7780   0.03223   0.02426  -0.1909   0.4655   1.0000
   9.000   1.7892   0.03283   0.02497  -0.1880   0.4534   1.0000
   9.250   1.7988   0.03351   0.02576  -0.1850   0.4414   1.0000
   9.500   1.8163   0.03382   0.02606  -0.1831   0.4297   1.0000
   9.750   1.8305   0.03416   0.02639  -0.1806   0.4177   1.0000
  10.000   1.8299   0.03507   0.02745  -0.1761   0.4060   1.0000
  10.250   1.8373   0.03565   0.02804  -0.1727   0.3951   1.0000
  10.500   1.8490   0.03609   0.02846  -0.1700   0.3843   1.0000
  10.750   1.8436   0.03737   0.02991  -0.1651   0.3740   1.0000
  11.000   1.8536   0.03811   0.03064  -0.1625   0.3642   1.0000
  11.250   1.8562   0.03921   0.03182  -0.1591   0.3542   1.0000
  11.500   1.8571   0.04053   0.03323  -0.1556   0.3446   1.0000
  11.750   1.8680   0.04121   0.03385  -0.1533   0.3345   1.0000
  12.000   1.8587   0.04317   0.03601  -0.1491   0.3249   1.0000
  12.250   1.8621   0.04447   0.03733  -0.1463   0.3155   1.0000
  12.500   1.8607   0.04612   0.03906  -0.1433   0.3061   1.0000
  12.750   1.8583   0.04801   0.04107  -0.1404   0.2972   1.0000
  13.000   1.8618   0.04941   0.04245  -0.1380   0.2879   1.0000
  13.250   1.8506   0.05213   0.04539  -0.1348   0.2789   1.0000
  13.500   1.8480   0.05412   0.04739  -0.1323   0.2693   1.0000
  13.750   1.8371   0.05701   0.05044  -0.1296   0.2600   1.0000
  14.000   1.8281   0.05989   0.05342  -0.1272   0.2504   1.0000
  14.250   1.8219   0.06254   0.05606  -0.1252   0.2402   1.0000
  14.500   1.8050   0.06678   0.06055  -0.1233   0.2305   1.0000
  14.750   1.7914   0.07078   0.06464  -0.1219   0.2196   1.0000
  15.000   1.7760   0.07524   0.06915  -0.1208   0.2078   1.0000
  15.250   1.7571   0.08048   0.07445  -0.1202   0.1948   1.0000
  15.500   1.7348   0.08666   0.08075  -0.1203   0.1809   1.0000
  15.750   1.7116   0.09321   0.08735  -0.1208   0.1657   1.0000
  16.000   1.6871   0.10029   0.09448  -0.1218   0.1491   1.0000
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