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GOE 507 AIRFOIL (goe507-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 507 AIRFOIL (goe507-il)
Reynolds number: 200,000
Max Cl/Cd: 67.39 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe507-il-200000-n5.txt
Download as CSV file: xf-goe507-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 507 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.6993   0.03626   0.03224  -0.0586   1.0000   0.0210
  -9.000  -0.7078   0.03104   0.02645  -0.0568   0.9993   0.0218
  -8.750  -0.6853   0.02720   0.02204  -0.0589   0.9940   0.0235
  -8.500  -0.6534   0.02734   0.02220  -0.0602   0.9902   0.0251
  -8.250  -0.6227   0.02637   0.02104  -0.0617   0.9865   0.0270
  -8.000  -0.5973   0.02397   0.01812  -0.0627   0.9814   0.0301
  -7.750  -0.5640   0.02434   0.01854  -0.0640   0.9781   0.0321
  -7.500  -0.5319   0.02422   0.01832  -0.0653   0.9749   0.0349
  -7.250  -0.5040   0.02285   0.01649  -0.0659   0.9701   0.0394
  -7.000  -0.4724   0.02205   0.01550  -0.0672   0.9670   0.0422
  -6.750  -0.4420   0.02187   0.01529  -0.0681   0.9629   0.0448
  -6.500  -0.4120   0.02131   0.01450  -0.0689   0.9588   0.0485
  -6.250  -0.3802   0.02068   0.01355  -0.0700   0.9558   0.0519
  -6.000  -0.3523   0.01982   0.01245  -0.0703   0.9509   0.0543
  -5.750  -0.3230   0.01902   0.01160  -0.0710   0.9467   0.0568
  -5.500  -0.2913   0.01842   0.01089  -0.0720   0.9436   0.0594
  -5.250  -0.2636   0.01781   0.01014  -0.0721   0.9386   0.0615
  -5.000  -0.2342   0.01727   0.00942  -0.0725   0.9342   0.0634
  -4.750  -0.2027   0.01672   0.00872  -0.0732   0.9309   0.0647
  -4.500  -0.1750   0.01621   0.00810  -0.0732   0.9256   0.0653
  -4.250  -0.1467   0.01558   0.00740  -0.0733   0.9206   0.0661
  -4.000  -0.1164   0.01486   0.00665  -0.0738   0.9163   0.0676
  -3.750  -0.0907   0.01440   0.00618  -0.0734   0.9086   0.0693
  -3.500  -0.0616   0.01396   0.00571  -0.0735   0.9023   0.0707
  -3.250  -0.0354   0.01359   0.00531  -0.0730   0.8943   0.0718
  -3.000  -0.0078   0.01325   0.00492  -0.0728   0.8874   0.0731
  -2.750   0.0190   0.01296   0.00460  -0.0724   0.8810   0.0747
  -2.500   0.0454   0.01273   0.00432  -0.0720   0.8745   0.0762
  -2.250   0.0736   0.01250   0.00404  -0.0719   0.8696   0.0778
  -2.000   0.0988   0.01229   0.00383  -0.0712   0.8621   0.0800
  -1.750   0.1260   0.01207   0.00360  -0.0709   0.8562   0.0831
  -1.500   0.1522   0.01190   0.00344  -0.0705   0.8493   0.0870
  -1.250   0.1788   0.01173   0.00329  -0.0701   0.8424   0.0930
  -1.000   0.2050   0.01148   0.00318  -0.0696   0.8357   0.1168
  -0.750   0.2306   0.01125   0.00317  -0.0691   0.8280   0.1764
  -0.500   0.2572   0.01110   0.00310  -0.0687   0.8209   0.2115
  -0.250   0.2829   0.01095   0.00306  -0.0682   0.8124   0.2412
   0.000   0.3092   0.01079   0.00300  -0.0677   0.8044   0.2689
   0.250   0.3340   0.01052   0.00296  -0.0671   0.7952   0.3357
   0.750   0.4231   0.00886   0.00305  -0.0732   0.7769   0.9707
   1.000   0.4717   0.00884   0.00295  -0.0775   0.7614   1.0000
   1.250   0.4951   0.00888   0.00291  -0.0763   0.7445   1.0000
   1.500   0.5189   0.00893   0.00290  -0.0752   0.7281   1.0000
   1.750   0.5428   0.00900   0.00291  -0.0742   0.7120   1.0000
   2.000   0.5662   0.00908   0.00292  -0.0731   0.6901   1.0000
   2.250   0.5890   0.00919   0.00290  -0.0718   0.6598   1.0000
   2.500   0.6109   0.00936   0.00290  -0.0703   0.6217   1.0000
   2.750   0.6324   0.00959   0.00294  -0.0688   0.5832   1.0000
   3.000   0.6541   0.00985   0.00304  -0.0674   0.5531   1.0000
   3.250   0.6758   0.01013   0.00319  -0.0660   0.5267   1.0000
   3.500   0.6974   0.01044   0.00337  -0.0647   0.4988   1.0000
   3.750   0.7194   0.01073   0.00357  -0.0635   0.4734   1.0000
   4.000   0.7414   0.01103   0.00379  -0.0623   0.4493   1.0000
   4.250   0.7635   0.01133   0.00402  -0.0611   0.4224   1.0000
   4.500   0.7846   0.01169   0.00426  -0.0598   0.3902   1.0000
   4.750   0.8056   0.01208   0.00454  -0.0585   0.3581   1.0000
   5.000   0.8260   0.01251   0.00485  -0.0572   0.3239   1.0000
   5.250   0.8459   0.01301   0.00520  -0.0558   0.2865   1.0000
   5.500   0.8648   0.01360   0.00561  -0.0543   0.2454   1.0000
   5.750   0.8833   0.01427   0.00606  -0.0528   0.2004   1.0000
   6.000   0.8998   0.01514   0.00661  -0.0511   0.1352   1.0000
   6.250   0.9159   0.01609   0.00727  -0.0493   0.0948   1.0000
   6.500   0.9348   0.01678   0.00790  -0.0479   0.0829   1.0000
   6.750   0.9550   0.01733   0.00849  -0.0466   0.0759   1.0000
   7.000   0.9739   0.01798   0.00915  -0.0452   0.0701   1.0000
   7.250   0.9939   0.01850   0.00976  -0.0440   0.0649   1.0000
   7.500   1.0110   0.01927   0.01053  -0.0424   0.0595   1.0000
   7.750   1.0316   0.01972   0.01110  -0.0412   0.0546   1.0000
   8.000   1.0493   0.02039   0.01181  -0.0397   0.0489   1.0000
   8.250   1.0680   0.02096   0.01247  -0.0384   0.0440   1.0000
   8.500   1.0865   0.02154   0.01314  -0.0369   0.0382   1.0000
   8.750   1.1017   0.02236   0.01394  -0.0351   0.0333   1.0000
   9.000   1.1174   0.02308   0.01477  -0.0333   0.0301   1.0000
   9.250   1.1313   0.02384   0.01557  -0.0313   0.0274   1.0000
   9.500   1.1413   0.02483   0.01657  -0.0288   0.0250   1.0000
   9.750   1.1517   0.02584   0.01769  -0.0264   0.0232   1.0000
  10.000   1.1623   0.02688   0.01883  -0.0242   0.0219   1.0000
  10.250   1.1726   0.02794   0.01999  -0.0220   0.0207   1.0000
  10.500   1.1816   0.02912   0.02123  -0.0199   0.0197   1.0000
  10.750   1.1870   0.03067   0.02283  -0.0176   0.0187   1.0000
  11.000   1.1967   0.03195   0.02427  -0.0158   0.0179   1.0000
  11.250   1.2048   0.03339   0.02585  -0.0140   0.0169   1.0000
  11.500   1.2118   0.03495   0.02755  -0.0122   0.0164   1.0000
  11.750   1.2179   0.03659   0.02931  -0.0106   0.0158   1.0000
  12.000   1.2224   0.03839   0.03120  -0.0090   0.0153   1.0000
  12.250   1.2257   0.04037   0.03327  -0.0076   0.0149   1.0000
  12.500   1.2281   0.04264   0.03567  -0.0063   0.0145   1.0000
  12.750   1.2311   0.04485   0.03811  -0.0052   0.0140   1.0000
  13.000   1.2314   0.04746   0.04093  -0.0041   0.0136   1.0000
  13.250   1.2308   0.05015   0.04381  -0.0034   0.0133   1.0000
  13.500   1.2291   0.05300   0.04683  -0.0030   0.0129   1.0000
  13.750   1.2256   0.05621   0.05022  -0.0029   0.0127   1.0000
  14.000   1.2212   0.05960   0.05376  -0.0032   0.0124   1.0000
  14.250   1.2150   0.06344   0.05777  -0.0038   0.0122   1.0000
  14.500   1.2072   0.06769   0.06219  -0.0048   0.0121   1.0000
  14.750   1.1987   0.07223   0.06688  -0.0064   0.0120   1.0000
  15.000   1.1888   0.07723   0.07205  -0.0083   0.0119   1.0000
  15.250   1.1767   0.08295   0.07795  -0.0109   0.0118   1.0000
  15.500   1.1626   0.08933   0.08452  -0.0141   0.0118   1.0000
  15.750   1.1488   0.09591   0.09126  -0.0176   0.0117   1.0000
  16.000   1.1292   0.10421   0.09978  -0.0223   0.0118   1.0000
  16.250   1.1079   0.11334   0.10911  -0.0278   0.0118   1.0000
  16.500   1.0445   0.13488   0.13114  -0.0413   0.0124   1.0000
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