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GOE 225 (MVA H.35) AIRFOIL (goe225-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 225 (MVA H.35) AIRFOIL (goe225-il)
Reynolds number: 50,000
Max Cl/Cd: 33.43 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe225-il-50000-n5.txt
Download as CSV file: xf-goe225-il-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.2074   0.12324   0.11649  -0.0499   0.9617   0.1293
  -7.750  -0.2079   0.12163   0.11490  -0.0531   0.9545   0.1302
  -7.500  -0.2075   0.11962   0.11291  -0.0555   0.9462   0.1306
  -7.250  -0.2003   0.11677   0.11007  -0.0587   0.9386   0.1307
  -6.250  -0.1527   0.09684   0.08998  -0.0728   0.9121   0.0880
  -6.000  -0.1394   0.09397   0.08711  -0.0736   0.9058   0.0872
  -5.750  -0.1271   0.09102   0.08415  -0.0750   0.8984   0.0860
  -5.500  -0.1028   0.08688   0.07996  -0.0805   0.8934   0.0846
  -5.250  -0.0948   0.08377   0.07685  -0.0826   0.8839   0.0835
  -5.000  -0.0669   0.07900   0.07201  -0.0902   0.8779   0.0826
  -4.750  -0.0429   0.07475   0.06769  -0.0967   0.8703   0.0832
  -4.500  -0.0066   0.06920   0.06202  -0.1071   0.8631   0.0847
  -4.250   0.0700   0.05811   0.05047  -0.1315   0.8599   0.0856
  -4.000   0.1752   0.04686   0.03810  -0.1606   0.8590   0.0901
  -3.750   0.2066   0.04545   0.03654  -0.1633   0.8506   0.0944
  -3.500   0.2690   0.04170   0.03192  -0.1735   0.8462   0.1018
  -3.250   0.3148   0.04026   0.03034  -0.1775   0.8420   0.1095
  -3.000   0.3473   0.03924   0.02908  -0.1795   0.8336   0.1196
  -2.750   0.3870   0.03822   0.02787  -0.1823   0.8272   0.1339
  -2.500   0.4314   0.03746   0.02710  -0.1854   0.8231   0.1539
  -2.250   0.4525   0.03754   0.02720  -0.1848   0.8114   0.1707
  -2.000   0.4943   0.03698   0.02654  -0.1872   0.8065   0.1916
  -1.750   0.5171   0.03703   0.02658  -0.1866   0.7954   0.2042
  -1.500   0.5567   0.03649   0.02592  -0.1885   0.7898   0.2205
  -1.250   0.5808   0.03655   0.02594  -0.1880   0.7789   0.2359
  -1.000   0.6180   0.03613   0.02540  -0.1894   0.7728   0.2582
  -0.750   0.6414   0.03627   0.02548  -0.1888   0.7618   0.2812
  -0.500   0.6766   0.03594   0.02514  -0.1896   0.7555   0.3138
  -0.250   0.6961   0.03629   0.02552  -0.1883   0.7438   0.3383
   0.000   0.7312   0.03599   0.02516  -0.1889   0.7383   0.3701
   0.250   0.7479   0.03655   0.02575  -0.1872   0.7262   0.3914
   0.500   0.7830   0.03620   0.02537  -0.1877   0.7213   0.4178
   0.750   0.7979   0.03690   0.02609  -0.1858   0.7091   0.4420
   1.000   0.8325   0.03655   0.02576  -0.1860   0.7048   0.4760
   1.250   0.8470   0.03730   0.02650  -0.1842   0.6929   0.4981
   1.500   0.8835   0.03672   0.02588  -0.1848   0.6889   0.5199
   1.750   0.8988   0.03748   0.02661  -0.1833   0.6776   0.5342
   2.000   0.9355   0.03690   0.02597  -0.1841   0.6735   0.5533
   2.250   0.9517   0.03764   0.02671  -0.1827   0.6630   0.5688
   2.500   0.9865   0.03712   0.02617  -0.1832   0.6584   0.5903
   2.750   1.0059   0.03769   0.02675  -0.1822   0.6496   0.6106
   3.000   1.0363   0.03743   0.02653  -0.1822   0.6438   0.6368
   3.250   1.0751   0.03654   0.02574  -0.1832   0.6403   0.6734
   3.500   1.0845   0.03756   0.02694  -0.1809   0.6298   0.7121
   3.750   1.1131   0.03672   0.02628  -0.1801   0.6251   1.0000
   4.000   1.1289   0.03790   0.02738  -0.1789   0.6156   1.0000
   4.250   1.1625   0.03783   0.02718  -0.1794   0.6101   1.0000
   4.500   1.2012   0.03744   0.02668  -0.1805   0.6055   1.0000
   4.750   1.2099   0.03894   0.02819  -0.1783   0.5952   1.0000
   5.000   1.2521   0.03828   0.02741  -0.1796   0.5907   1.0000
   5.250   1.2580   0.03994   0.02912  -0.1770   0.5802   1.0000
   5.500   1.2971   0.03940   0.02850  -0.1779   0.5745   1.0000
   5.750   1.3077   0.04069   0.02982  -0.1757   0.5646   1.0000
   6.000   1.3427   0.04037   0.02946  -0.1761   0.5575   1.0000
   6.250   1.3560   0.04146   0.03059  -0.1741   0.5480   1.0000
   6.500   1.3859   0.04146   0.03057  -0.1739   0.5401   1.0000
   6.750   1.3998   0.04251   0.03167  -0.1721   0.5309   1.0000
   7.000   1.4243   0.04287   0.03206  -0.1713   0.5225   1.0000
   7.250   1.4380   0.04393   0.03318  -0.1695   0.5136   1.0000
   7.500   1.4577   0.04457   0.03387  -0.1682   0.5047   1.0000
   7.750   1.4679   0.04587   0.03526  -0.1661   0.4956   1.0000
   8.000   1.4855   0.04662   0.03608  -0.1646   0.4867   1.0000
   8.250   1.4874   0.04851   0.03808  -0.1618   0.4769   1.0000
   8.500   1.5086   0.04895   0.03858  -0.1606   0.4683   1.0000
   8.750   1.4978   0.05187   0.04165  -0.1570   0.4575   1.0000
   9.000   1.5273   0.05161   0.04145  -0.1565   0.4500   1.0000
   9.250   1.5045   0.05571   0.04572  -0.1524   0.4382   1.0000
   9.500   1.5438   0.05447   0.04450  -0.1523   0.4317   1.0000
   9.750   1.5113   0.05966   0.04988  -0.1481   0.4190   1.0000
  10.000   1.5301   0.06019   0.05049  -0.1468   0.4114   1.0000
  10.250   1.5188   0.06372   0.05415  -0.1442   0.4006   1.0000
  10.500   1.4962   0.06879   0.05936  -0.1418   0.3887   1.0000
  10.750   1.5259   0.06796   0.05862  -0.1407   0.3828   1.0000
  11.000   1.4910   0.07485   0.06566  -0.1386   0.3700   1.0000
  11.250   1.5276   0.07311   0.06398  -0.1375   0.3657   1.0000
  11.500   1.4841   0.08159   0.07262  -0.1360   0.3524   1.0000
  11.750   1.5235   0.07925   0.07035  -0.1347   0.3490   1.0000
  12.000   1.4735   0.08926   0.08049  -0.1342   0.3354   1.0000
  12.250   1.5117   0.08682   0.07816  -0.1326   0.3327   1.0000
  12.500   1.4551   0.09873   0.09018  -0.1336   0.3189   1.0000
  12.750   1.4871   0.09701   0.08859  -0.1318   0.3167   1.0000
  13.250   1.4516   0.10995   0.10173  -0.1330   0.2998   1.0000
  13.750   1.4353   0.12003   0.11202  -0.1341   0.2847   1.0000
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