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GOE 431 AIRFOIL (goe431-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 431 AIRFOIL (goe431-il)
Reynolds number: 200,000
Max Cl/Cd: 81.05 at α=2.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe431-il-200000.txt
Download as CSV file: xf-goe431-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 431 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.1025   0.10838   0.10479  -0.0903   0.9588   0.0631
  -9.750  -0.1128   0.10602   0.10246  -0.0954   0.9515   0.0649
  -9.500  -0.1015   0.10143   0.09788  -0.0970   0.9489   0.0663
  -9.250  -0.0769   0.09866   0.09508  -0.0970   0.9475   0.0681
  -9.000  -0.0589   0.09571   0.09212  -0.0995   0.9458   0.0707
  -8.750   0.0231   0.07735   0.07393  -0.1082   0.9306   0.0789
  -8.500   0.0451   0.07459   0.07114  -0.1095   0.9297   0.0829
  -8.250  -0.0856   0.07525   0.07172  -0.1127   0.9306   0.0461
  -8.000  -0.2310   0.04448   0.04048  -0.1426   0.9049   0.0361
  -7.750  -0.1907   0.03570   0.03086  -0.1608   0.9025   0.0361
  -7.500  -0.1556   0.03150   0.02610  -0.1675   0.9013   0.0368
  -7.250  -0.1234   0.02902   0.02345  -0.1706   0.9004   0.0382
  -7.000  -0.0890   0.02764   0.02191  -0.1733   0.8995   0.0407
  -6.750  -0.0857   0.02742   0.02157  -0.1699   0.8945   0.0423
  -6.500  -0.0664   0.02685   0.02076  -0.1693   0.8918   0.0442
  -6.250  -0.0406   0.02544   0.01934  -0.1701   0.8901   0.0471
  -6.000  -0.0120   0.02469   0.01852  -0.1710   0.8887   0.0511
  -5.750   0.0241   0.02353   0.01726  -0.1733   0.8871   0.0590
  -5.500   0.0711   0.02182   0.01540  -0.1776   0.8857   0.0788
  -5.250   0.1227   0.02230   0.01608  -0.1812   0.8842   0.1424
  -5.000   0.1154   0.02356   0.01729  -0.1751   0.8770   0.1506
  -4.750   0.1482   0.02434   0.01812  -0.1753   0.8731   0.1647
  -4.500   0.1906   0.02482   0.01870  -0.1771   0.8709   0.1780
  -4.250   0.2405   0.02459   0.01840  -0.1806   0.8698   0.1896
  -4.000   0.2416   0.02536   0.01921  -0.1759   0.8626   0.1934
  -3.750   0.2750   0.02511   0.01867  -0.1769   0.8590   0.2003
  -3.500   0.3175   0.02451   0.01817  -0.1793   0.8572   0.2066
  -3.250   0.3675   0.02394   0.01741  -0.1830   0.8561   0.2152
  -3.000   0.4138   0.02293   0.01630  -0.1863   0.8549   0.2203
  -2.750   0.4589   0.02198   0.01524  -0.1892   0.8536   0.2222
  -2.500   0.4569   0.02256   0.01577  -0.1842   0.8456   0.2225
  -2.250   0.4944   0.02185   0.01491  -0.1859   0.8431   0.2233
  -2.000   0.5357   0.02107   0.01402  -0.1882   0.8413   0.2250
  -1.750   0.5781   0.02028   0.01310  -0.1905   0.8395   0.2268
  -1.500   0.6214   0.01946   0.01215  -0.1930   0.8378   0.2280
  -1.250   0.6316   0.01971   0.01238  -0.1898   0.8300   0.2287
  -1.000   0.6700   0.01903   0.01160  -0.1913   0.8265   0.2302
  -0.750   0.7121   0.01828   0.01075  -0.1934   0.8238   0.2319
  -0.500   0.7416   0.01791   0.01035  -0.1934   0.8188   0.2336
  -0.250   0.7666   0.01763   0.01010  -0.1926   0.8125   0.2356
   0.000   0.8055   0.01697   0.00944  -0.1941   0.8086   0.2386
   0.250   0.8334   0.01667   0.00917  -0.1937   0.8022   0.2417
   0.500   0.8631   0.01628   0.00877  -0.1936   0.7952   0.2457
   0.750   0.9007   0.01568   0.00815  -0.1948   0.7897   0.2510
   1.000   0.9220   0.01549   0.00806  -0.1932   0.7803   0.2558
   1.250   0.9535   0.01505   0.00762  -0.1933   0.7721   0.2627
   1.500   0.9816   0.01459   0.00723  -0.1928   0.7613   0.2704
   1.750   1.0047   0.01428   0.00697  -0.1913   0.7476   0.2809
   2.000   1.0292   0.01386   0.00663  -0.1901   0.7305   0.2961
   2.250   1.0481   0.01353   0.00643  -0.1878   0.7043   0.3190
   2.500   1.0666   0.01316   0.00609  -0.1854   0.6497   0.3631
   2.750   1.0753   0.01355   0.00588  -0.1809   0.5414   0.4221
   3.000   1.0849   0.01434   0.00643  -0.1774   0.5046   0.4835
   3.250   1.1021   0.01497   0.00692  -0.1754   0.4849   0.5367
   3.500   1.1233   0.01542   0.00733  -0.1741   0.4711   0.5800
   3.750   1.1460   0.01573   0.00769  -0.1732   0.4608   0.6234
   4.000   1.1688   0.01590   0.00803  -0.1723   0.4529   0.7161
   4.250   1.1918   0.01596   0.00828  -0.1712   0.4457   1.0000
   4.500   1.2172   0.01641   0.00864  -0.1709   0.4393   1.0000
   4.750   1.2439   0.01687   0.00902  -0.1708   0.4338   1.0000
   5.000   1.2689   0.01724   0.00939  -0.1703   0.4284   1.0000
   5.250   1.2949   0.01767   0.00976  -0.1701   0.4233   1.0000
   5.500   1.3220   0.01814   0.01019  -0.1701   0.4182   1.0000
   5.750   1.3453   0.01850   0.01060  -0.1693   0.4130   1.0000
   6.000   1.3705   0.01891   0.01100  -0.1689   0.4082   1.0000
   6.250   1.4005   0.01946   0.01147  -0.1695   0.4039   1.0000
   6.500   1.4232   0.01981   0.01194  -0.1686   0.4002   1.0000
   6.750   1.4481   0.02022   0.01242  -0.1682   0.3965   1.0000
   7.000   1.4732   0.02065   0.01287  -0.1678   0.3921   1.0000
   7.250   1.5025   0.02121   0.01339  -0.1683   0.3877   1.0000
   7.500   1.5226   0.02158   0.01392  -0.1670   0.3838   1.0000
   7.750   1.5428   0.02196   0.01438  -0.1657   0.3783   1.0000
   8.000   1.5652   0.02244   0.01482  -0.1648   0.3712   1.0000
   8.250   1.5740   0.02271   0.01525  -0.1614   0.3638   1.0000
   8.500   1.5921   0.02315   0.01562  -0.1598   0.3557   1.0000
   8.750   1.5968   0.02346   0.01611  -0.1557   0.3485   1.0000
   9.000   1.6126   0.02392   0.01649  -0.1537   0.3404   1.0000
   9.250   1.6167   0.02433   0.01713  -0.1498   0.3332   1.0000
   9.500   1.6280   0.02483   0.01761  -0.1472   0.3249   1.0000
   9.750   1.6321   0.02537   0.01836  -0.1435   0.3165   1.0000
  10.000   1.6399   0.02601   0.01902  -0.1406   0.3077   1.0000
  10.250   1.6423   0.02674   0.01990  -0.1370   0.2962   1.0000
  10.500   1.6454   0.02759   0.02087  -0.1337   0.2821   1.0000
  10.750   1.6462   0.02867   0.02202  -0.1303   0.2620   1.0000
  11.000   1.6419   0.03029   0.02351  -0.1267   0.2107   1.0000
  11.250   1.6224   0.03360   0.02630  -0.1221   0.1552   1.0000
  11.500   1.6058   0.03721   0.02956  -0.1182   0.1030   1.0000
  11.750   1.5860   0.04130   0.03325  -0.1145   0.0582   1.0000
  12.000   1.5751   0.04476   0.03665  -0.1118   0.0465   1.0000
  12.250   1.5701   0.04780   0.03979  -0.1096   0.0416   1.0000
  12.500   1.5652   0.05095   0.04305  -0.1077   0.0385   1.0000
  12.750   1.5561   0.05469   0.04691  -0.1060   0.0364   1.0000
  13.000   1.5489   0.05842   0.05078  -0.1046   0.0351   1.0000
  13.250   1.5439   0.06203   0.05456  -0.1036   0.0339   1.0000
  13.500   1.5373   0.06602   0.05869  -0.1028   0.0328   1.0000
  13.750   1.5299   0.07029   0.06310  -0.1024   0.0319   1.0000
  14.000   1.5219   0.07484   0.06777  -0.1023   0.0310   1.0000
  14.250   1.5126   0.07973   0.07277  -0.1025   0.0301   1.0000
  14.500   1.5028   0.08479   0.07790  -0.1029   0.0293   1.0000
  14.750   1.4967   0.08927   0.08244  -0.1031   0.0285   1.0000
  15.000   1.4973   0.09295   0.08625  -0.1034   0.0277   1.0000
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