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GOE 242 (MVA PR.2) AIRFOIL (goe242-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 242 (MVA PR.2) AIRFOIL (goe242-il)
Reynolds number: 100,000
Max Cl/Cd: 46.79 at α=9.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe242-il-100000.txt
Download as CSV file: xf-goe242-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000   0.0470   0.10355   0.09931  -0.1054   0.9241   0.1176
  -9.750   0.0917   0.09710   0.09281  -0.1033   0.9155   0.1233
  -9.500   0.0945   0.09435   0.09005  -0.1070   0.9088   0.1316
  -9.250   0.1014   0.09063   0.08633  -0.1078   0.8977   0.1350
  -9.000   0.0197   0.10148   0.09703  -0.0992   0.9319   0.1264
  -8.750  -0.0007   0.10060   0.09622  -0.1090   0.9153   0.1331
  -8.500   0.0531   0.09465   0.09016  -0.1056   0.9131   0.1406
  -8.250   0.0353   0.09334   0.08892  -0.1119   0.8962   0.1485
  -8.000   0.0781   0.08861   0.08409  -0.1095   0.8922   0.1542
  -7.750   0.1534   0.07360   0.06914  -0.1093   0.8409   0.1741
  -7.500   0.1420   0.07161   0.06720  -0.1106   0.8289   0.1806
  -7.250   0.1648   0.06889   0.06441  -0.1089   0.8220   0.1887
  -7.000   0.1078   0.07940   0.07480  -0.1108   0.8444   0.1844
  -6.500   0.1220   0.07531   0.07066  -0.1108   0.8257   0.2013
  -6.250   0.1141   0.07403   0.06943  -0.1151   0.8131   0.2133
  -6.000   0.1718   0.03871   0.03267  -0.1855   0.8039   0.0988
  -5.750   0.2302   0.03339   0.02625  -0.1965   0.7972   0.0901
  -5.500   0.2711   0.03102   0.02350  -0.1998   0.7928   0.0912
  -5.250   0.3025   0.02974   0.02191  -0.2013   0.7838   0.0905
  -5.000   0.3376   0.02829   0.02020  -0.2026   0.7786   0.0905
  -4.750   0.3682   0.02730   0.01912  -0.2032   0.7730   0.0922
  -4.500   0.3960   0.02677   0.01854  -0.2035   0.7660   0.0956
  -4.250   0.4270   0.02603   0.01773  -0.2035   0.7617   0.0981
  -4.000   0.4537   0.02578   0.01748  -0.2031   0.7564   0.1003
  -3.750   0.4788   0.02574   0.01747  -0.2024   0.7500   0.1032
  -3.500   0.5118   0.02526   0.01704  -0.2032   0.7459   0.1114
  -3.250   0.5504   0.02480   0.01658  -0.2059   0.7417   0.1253
  -3.000   0.5965   0.02397   0.01685  -0.2120   0.7358   0.3125
  -2.750   0.6182   0.02559   0.01844  -0.2092   0.7315   0.4380
  -2.500   0.6322   0.02716   0.02003  -0.2040   0.7284   0.4648
  -2.250   0.6462   0.02883   0.02170  -0.2010   0.7227   0.4879
  -2.000   0.6583   0.03000   0.02291  -0.1969   0.7177   0.4997
  -1.750   0.6777   0.03067   0.02352  -0.1941   0.7143   0.5158
  -1.500   0.7046   0.03109   0.02381  -0.1930   0.7118   0.5373
  -1.250   0.7051   0.03283   0.02570  -0.1886   0.7055   0.5460
  -1.000   0.7204   0.03364   0.02651  -0.1860   0.7013   0.5643
  -0.750   0.7474   0.03384   0.02661  -0.1853   0.6984   0.5861
  -0.500   0.7729   0.03367   0.02635  -0.1841   0.6961   0.5971
  -0.250   0.7782   0.03593   0.02870  -0.1834   0.6887   0.6037
   0.000   0.8011   0.03632   0.02905  -0.1831   0.6847   0.6109
   0.250   0.8417   0.03599   0.02856  -0.1859   0.6823   0.6189
   0.500   0.8744   0.03558   0.02807  -0.1862   0.6803   0.6271
   0.750   0.8693   0.03886   0.03146  -0.1847   0.6702   0.6335
   1.000   0.9022   0.03798   0.03052  -0.1843   0.6671   0.6438
   1.250   0.9499   0.03647   0.02886  -0.1863   0.6648   0.6536
   1.500   0.9425   0.03937   0.03189  -0.1837   0.6543   0.6570
   1.750   0.9911   0.03819   0.03057  -0.1866   0.6512   0.6619
   2.000   1.0462   0.03665   0.02884  -0.1905   0.6489   0.6648
   2.250   1.0359   0.03978   0.03214  -0.1873   0.6387   0.6662
   2.500   1.0797   0.03856   0.03084  -0.1891   0.6352   0.6694
   2.750   1.1324   0.03691   0.02905  -0.1921   0.6327   0.6721
   3.000   1.1249   0.03993   0.03222  -0.1894   0.6225   0.6731
   3.250   1.1715   0.03878   0.03100  -0.1918   0.6189   0.6763
   3.500   1.2249   0.03729   0.02936  -0.1951   0.6162   0.6804
   3.750   1.2160   0.04013   0.03239  -0.1917   0.6059   0.6819
   4.000   1.2604   0.03897   0.03118  -0.1936   0.6022   0.6851
   4.250   1.3115   0.03751   0.02961  -0.1964   0.5993   0.6888
   4.500   1.3036   0.04021   0.03250  -0.1930   0.5886   0.6905
   4.750   1.3538   0.03889   0.03110  -0.1958   0.5849   0.6952
   5.000   1.4041   0.03737   0.02950  -0.1982   0.5818   0.7001
   5.250   1.3970   0.03966   0.03200  -0.1944   0.5705   0.7026
   5.500   1.4499   0.03805   0.03031  -0.1974   0.5667   0.7078
   5.750   1.4521   0.03975   0.03216  -0.1947   0.5562   0.7106
   6.000   1.4980   0.03843   0.03080  -0.1966   0.5513   0.7155
   6.250   1.5098   0.03935   0.03185  -0.1947   0.5423   0.7197
   6.500   1.5485   0.03859   0.03107  -0.1960   0.5357   0.7261
   6.750   1.5699   0.03876   0.03131  -0.1951   0.5274   0.7311
   7.000   1.6005   0.03829   0.03087  -0.1952   0.5194   0.7371
   7.250   1.6186   0.03864   0.03129  -0.1939   0.5099   0.7423
   7.500   1.6554   0.03771   0.03034  -0.1947   0.5023   0.7492
   7.750   1.6619   0.03857   0.03134  -0.1919   0.4915   0.7551
   8.000   1.7087   0.03719   0.02988  -0.1940   0.4848   0.7646
   8.250   1.7056   0.03852   0.03139  -0.1900   0.4734   0.7707
   8.500   1.7416   0.03781   0.03065  -0.1908   0.4659   0.7804
   8.750   1.7461   0.03871   0.03169  -0.1877   0.4559   0.7881
   9.000   1.7553   0.03931   0.03240  -0.1851   0.4471   0.7977
   9.250   1.7817   0.03885   0.03196  -0.1846   0.4389   0.8120
   9.500   1.7716   0.04035   0.03364  -0.1798   0.4298   0.8242
   9.750   1.8084   0.03865   0.03195  -0.1801   0.4208   0.8743
  10.000   1.7866   0.04103   0.03453  -0.1744   0.4116   1.0000
  10.250   1.7987   0.04148   0.03495  -0.1727   0.4017   1.0000
  10.500   1.8240   0.04097   0.03428  -0.1721   0.3910   1.0000
  10.750   1.8089   0.04375   0.03723  -0.1683   0.3822   1.0000
  11.000   1.8249   0.04431   0.03774  -0.1672   0.3734   1.0000
  11.250   1.8267   0.04611   0.03959  -0.1651   0.3652   1.0000
  11.500   1.8361   0.04738   0.04086  -0.1636   0.3574   1.0000
  11.750   1.8401   0.04907   0.04257  -0.1618   0.3494   1.0000
  12.000   1.8450   0.05077   0.04430  -0.1600   0.3418   1.0000
  12.250   1.8471   0.05271   0.04629  -0.1583   0.3344   1.0000
  12.500   1.8536   0.05432   0.04795  -0.1567   0.3273   1.0000
  12.750   1.8476   0.05713   0.05088  -0.1548   0.3206   1.0000
  13.000   1.8611   0.05805   0.05176  -0.1536   0.3132   1.0000
  13.250   1.8451   0.06200   0.05593  -0.1516   0.3074   1.0000
  13.500   1.8571   0.06284   0.05669  -0.1503   0.2985   1.0000
  13.750   1.8356   0.06764   0.06175  -0.1487   0.2933   1.0000
  14.000   1.8441   0.06890   0.06297  -0.1475   0.2846   1.0000
  14.250   1.8233   0.07400   0.06832  -0.1464   0.2792   1.0000
  14.500   1.8146   0.07763   0.07206  -0.1456   0.2717   1.0000
  14.750   1.8012   0.08202   0.07659  -0.1450   0.2643   1.0000
  15.000   1.7875   0.08664   0.08135  -0.1447   0.2568   1.0000
  15.250   1.7745   0.09129   0.08613  -0.1446   0.2493   1.0000
  15.500   1.7578   0.09665   0.09163  -0.1449   0.2411   1.0000
  15.750   1.7402   0.10233   0.09747  -0.1454   0.2334   1.0000
  16.000   1.7298   0.10692   0.10210  -0.1460   0.2228   1.0000
  16.250   1.7031   0.11458   0.11005  -0.1475   0.2172   1.0000
  16.500   1.6864   0.12059   0.11617  -0.1489   0.2063   1.0000
  16.750   1.6602   0.12856   0.12438  -0.1513   0.1994   1.0000
  17.000   1.6364   0.13634   0.13231  -0.1539   0.1893   1.0000
  17.250   1.6115   0.14463   0.14075  -0.1572   0.1779   1.0000
  17.500   1.5816   0.15422   0.15057  -0.1614   0.1734   1.0000
  17.750   1.5641   0.16152   0.15780  -0.1650   0.1288   1.0000
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