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GOE 532 AIRFOIL (goe532-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 532 AIRFOIL (goe532-il)
Reynolds number: 100,000
Max Cl/Cd: 55.99 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe532-il-100000-n5.txt
Download as CSV file: xf-goe532-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 532 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.2650   0.09635   0.09148  -0.0366   1.0000   0.0808
  -8.500  -0.2940   0.09463   0.08994  -0.0384   1.0000   0.0831
  -8.250  -0.3095   0.09163   0.08705  -0.0425   0.9928   0.0835
  -7.750  -0.2791   0.07463   0.06995  -0.0551   0.9705   0.0554
  -7.500  -0.2583   0.06958   0.06485  -0.0616   0.9583   0.0543
  -7.250  -0.2384   0.06311   0.05831  -0.0708   0.9445   0.0539
  -7.000  -0.2189   0.05589   0.05091  -0.0802   0.9299   0.0530
  -6.750  -0.2006   0.04872   0.04342  -0.0884   0.9149   0.0517
  -6.500  -0.1805   0.04235   0.03655  -0.0945   0.9005   0.0507
  -6.250  -0.1558   0.03768   0.03134  -0.0983   0.8873   0.0503
  -6.000  -0.1275   0.03471   0.02796  -0.1006   0.8747   0.0513
  -5.750  -0.1015   0.03221   0.02503  -0.1018   0.8594   0.0522
  -5.500  -0.0746   0.02996   0.02234  -0.1025   0.8444   0.0526
  -5.250  -0.0468   0.02806   0.02004  -0.1030   0.8294   0.0528
  -5.000  -0.0188   0.02645   0.01804  -0.1032   0.8143   0.0532
  -4.750   0.0091   0.02508   0.01632  -0.1031   0.7985   0.0536
  -4.500   0.0368   0.02396   0.01484  -0.1028   0.7818   0.0545
  -4.250   0.0634   0.02296   0.01366  -0.1024   0.7644   0.0558
  -4.000   0.0900   0.02214   0.01274  -0.1020   0.7469   0.0571
  -3.750   0.1168   0.02138   0.01183  -0.1016   0.7300   0.0582
  -3.500   0.1437   0.02068   0.01098  -0.1010   0.7138   0.0591
  -3.250   0.1706   0.02005   0.01022  -0.1005   0.6984   0.0602
  -3.000   0.1973   0.01951   0.00954  -0.0999   0.6838   0.0615
  -2.750   0.2241   0.01907   0.00896  -0.0993   0.6704   0.0633
  -2.500   0.2502   0.01859   0.00847  -0.0988   0.6579   0.0659
  -2.250   0.2764   0.01826   0.00808  -0.0983   0.6459   0.0689
  -2.000   0.3032   0.01799   0.00767  -0.0978   0.6359   0.0715
  -1.750   0.3297   0.01769   0.00731  -0.0973   0.6259   0.0747
  -1.500   0.3567   0.01747   0.00700  -0.0970   0.6172   0.0799
  -1.250   0.3834   0.01723   0.00674  -0.0966   0.6079   0.0896
  -1.000   0.4102   0.01691   0.00648  -0.0962   0.5995   0.1141
  -0.750   0.4354   0.01615   0.00647  -0.0961   0.5903   0.3119
  -0.500   0.4608   0.01584   0.00658  -0.0955   0.5826   0.4683
  -0.250   0.4852   0.01565   0.00674  -0.0944   0.5742   0.5776
   0.000   0.5072   0.01539   0.00682  -0.0925   0.5671   0.7085
   0.250   0.5476   0.01484   0.00670  -0.0940   0.5580   1.0000
   0.500   0.5751   0.01503   0.00667  -0.0938   0.5504   1.0000
   0.750   0.6023   0.01524   0.00671  -0.0936   0.5432   1.0000
   1.000   0.6292   0.01545   0.00677  -0.0933   0.5358   1.0000
   1.250   0.6566   0.01567   0.00679  -0.0930   0.5298   1.0000
   1.500   0.6830   0.01588   0.00694  -0.0927   0.5225   1.0000
   1.750   0.7097   0.01610   0.00704  -0.0923   0.5158   1.0000
   2.000   0.7366   0.01633   0.00714  -0.0920   0.5101   1.0000
   2.250   0.7627   0.01656   0.00733  -0.0916   0.5031   1.0000
   2.500   0.7892   0.01678   0.00746  -0.0912   0.4969   1.0000
   2.750   0.8155   0.01703   0.00763  -0.0908   0.4908   1.0000
   3.000   0.8411   0.01726   0.00784  -0.0903   0.4835   1.0000
   3.250   0.8672   0.01747   0.00794  -0.0898   0.4766   1.0000
   3.500   0.8920   0.01771   0.00820  -0.0892   0.4683   1.0000
   3.750   0.9176   0.01794   0.00839  -0.0887   0.4615   1.0000
   4.000   0.9431   0.01821   0.00863  -0.0882   0.4554   1.0000
   4.250   0.9680   0.01847   0.00892  -0.0876   0.4483   1.0000
   4.500   0.9934   0.01872   0.00912  -0.0870   0.4420   1.0000
   4.750   1.0175   0.01899   0.00945  -0.0863   0.4337   1.0000
   5.000   1.0417   0.01923   0.00966  -0.0856   0.4253   1.0000
   5.250   1.0650   0.01950   0.00999  -0.0848   0.4153   1.0000
   5.500   1.0881   0.01974   0.01018  -0.0839   0.4052   1.0000
   5.750   1.1102   0.02002   0.01051  -0.0829   0.3923   1.0000
   6.000   1.1318   0.02030   0.01083  -0.0818   0.3786   1.0000
   6.250   1.1530   0.02062   0.01116  -0.0807   0.3642   1.0000
   6.500   1.1736   0.02096   0.01151  -0.0795   0.3485   1.0000
   6.750   1.1935   0.02135   0.01189  -0.0782   0.3315   1.0000
   7.000   1.2124   0.02180   0.01231  -0.0769   0.3134   1.0000
   7.250   1.2299   0.02232   0.01276  -0.0753   0.2960   1.0000
   7.500   1.2462   0.02292   0.01328  -0.0736   0.2806   1.0000
   7.750   1.2616   0.02360   0.01390  -0.0719   0.2677   1.0000
   8.000   1.2762   0.02432   0.01457  -0.0701   0.2574   1.0000
   8.250   1.2895   0.02509   0.01530  -0.0682   0.2488   1.0000
   8.500   1.3027   0.02584   0.01606  -0.0662   0.2412   1.0000
   8.750   1.3131   0.02667   0.01687  -0.0639   0.2347   1.0000
   9.000   1.3246   0.02749   0.01772  -0.0618   0.2290   1.0000
   9.250   1.3358   0.02836   0.01863  -0.0598   0.2237   1.0000
   9.500   1.3445   0.02937   0.01963  -0.0577   0.2186   1.0000
   9.750   1.3553   0.03033   0.02067  -0.0559   0.2135   1.0000
  10.000   1.3649   0.03138   0.02180  -0.0541   0.2085   1.0000
  10.250   1.3732   0.03255   0.02298  -0.0524   0.2042   1.0000
  10.500   1.3824   0.03374   0.02422  -0.0508   0.2001   1.0000
  10.750   1.3906   0.03501   0.02562  -0.0494   0.1949   1.0000
  11.000   1.3967   0.03647   0.02714  -0.0479   0.1899   1.0000
  11.250   1.4027   0.03801   0.02869  -0.0465   0.1852   1.0000
  11.500   1.4088   0.03962   0.03047  -0.0454   0.1800   1.0000
  11.750   1.4128   0.04143   0.03236  -0.0444   0.1748   1.0000
  12.000   1.4168   0.04329   0.03421  -0.0433   0.1701   1.0000
  12.250   1.4204   0.04535   0.03649  -0.0427   0.1647   1.0000
  12.500   1.4221   0.04763   0.03889  -0.0421   0.1592   1.0000
  12.750   1.4230   0.04999   0.04125  -0.0415   0.1544   1.0000
  13.000   1.4237   0.05263   0.04412  -0.0414   0.1481   1.0000
  13.250   1.4221   0.05552   0.04712  -0.0413   0.1422   1.0000
  13.500   1.4211   0.05846   0.05019  -0.0414   0.1365   1.0000
  13.750   1.4195   0.06159   0.05347  -0.0417   0.1304   1.0000
  14.000   1.4172   0.06485   0.05682  -0.0421   0.1255   1.0000
  14.250   1.4155   0.06817   0.06027  -0.0425   0.1203   1.0000
  14.500   1.4125   0.07168   0.06383  -0.0432   0.1167   1.0000
  14.750   1.4114   0.07505   0.06730  -0.0438   0.1132   1.0000
  15.000   1.4090   0.07865   0.07099  -0.0446   0.1102   1.0000
  15.250   1.4057   0.08243   0.07483  -0.0455   0.1077   1.0000
  15.500   1.4032   0.08614   0.07859  -0.0465   0.1055   1.0000
  15.750   1.4012   0.08988   0.08244  -0.0475   0.1033   1.0000
  16.000   1.3988   0.09372   0.08637  -0.0486   0.1013   1.0000
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