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AG10 (ag10-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: AG10 (ag10-il)
Reynolds number: 500,000
Max Cl/Cd: 67.47 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ag10-il-500000-n5.txt
Download as CSV file: xf-ag10-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AG10                                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.6490   0.12693   0.12459   0.0414   1.0000   0.0093
  -9.750  -0.6444   0.12327   0.12094   0.0400   1.0000   0.0094
  -9.500  -0.6446   0.11734   0.11502   0.0369   1.0000   0.0086
  -9.250  -0.6393   0.11415   0.11183   0.0361   1.0000   0.0085
  -9.000  -0.6353   0.11049   0.10818   0.0346   1.0000   0.0084
  -8.750  -0.6316   0.10667   0.10438   0.0329   1.0000   0.0083
  -8.500  -0.6284   0.10265   0.10037   0.0309   1.0000   0.0083
  -7.500  -0.6145   0.08357   0.08136   0.0163   1.0000   0.0087
  -7.250  -0.6035   0.07929   0.07707   0.0118   1.0000   0.0085
  -7.000  -0.5898   0.07441   0.07217   0.0065   1.0000   0.0084
  -6.000  -0.5061   0.01863   0.01387  -0.0308   1.0000   0.0085
  -5.750  -0.4793   0.01652   0.01128  -0.0310   1.0000   0.0087
  -5.500  -0.4524   0.01502   0.00953  -0.0311   1.0000   0.0091
  -5.250  -0.4252   0.01439   0.00881  -0.0311   1.0000   0.0096
  -5.000  -0.3977   0.01374   0.00804  -0.0311   1.0000   0.0102
  -4.750  -0.3701   0.01288   0.00700  -0.0310   1.0000   0.0109
  -4.500  -0.3424   0.01206   0.00600  -0.0309   1.0000   0.0113
  -4.250  -0.3147   0.01128   0.00513  -0.0308   1.0000   0.0120
  -4.000  -0.2870   0.01079   0.00460  -0.0307   1.0000   0.0128
  -3.750  -0.2592   0.01035   0.00410  -0.0306   1.0000   0.0139
  -3.500  -0.2313   0.00994   0.00362  -0.0305   1.0000   0.0149
  -3.250  -0.2036   0.00956   0.00324  -0.0304   1.0000   0.0167
  -3.000  -0.1757   0.00928   0.00294  -0.0303   1.0000   0.0188
  -2.750  -0.1479   0.00892   0.00258  -0.0302   1.0000   0.0211
  -2.500  -0.1201   0.00869   0.00234  -0.0301   1.0000   0.0241
  -2.250  -0.0924   0.00841   0.00209  -0.0299   1.0000   0.0284
  -2.000  -0.0646   0.00819   0.00188  -0.0298   1.0000   0.0333
  -1.750  -0.0370   0.00799   0.00172  -0.0296   1.0000   0.0404
  -1.500  -0.0053   0.00780   0.00158  -0.0304   0.9864   0.0513
  -1.250   0.0304   0.00762   0.00146  -0.0320   0.9531   0.0679
  -1.000   0.0594   0.00754   0.00138  -0.0318   0.9041   0.0865
  -0.750   0.0830   0.00758   0.00130  -0.0304   0.8444   0.1069
  -0.500   0.1077   0.00766   0.00123  -0.0294   0.7795   0.1348
  -0.250   0.1338   0.00774   0.00118  -0.0289   0.7114   0.1770
   0.000   0.1606   0.00778   0.00115  -0.0287   0.6426   0.2429
   0.250   0.1878   0.00772   0.00115  -0.0287   0.5751   0.3525
   0.500   0.2085   0.00609   0.00112  -0.0271   0.5219   1.0000
   0.750   0.2361   0.00633   0.00112  -0.0270   0.4720   1.0000
   1.000   0.2639   0.00656   0.00114  -0.0269   0.4309   1.0000
   1.250   0.2918   0.00677   0.00118  -0.0268   0.3948   1.0000
   1.500   0.3197   0.00697   0.00123  -0.0268   0.3643   1.0000
   1.750   0.3476   0.00715   0.00129  -0.0267   0.3373   1.0000
   2.000   0.3755   0.00734   0.00136  -0.0267   0.3118   1.0000
   2.250   0.4033   0.00754   0.00144  -0.0266   0.2872   1.0000
   2.500   0.4312   0.00773   0.00155  -0.0266   0.2642   1.0000
   2.750   0.4590   0.00794   0.00166  -0.0265   0.2410   1.0000
   3.000   0.4868   0.00815   0.00178  -0.0264   0.2181   1.0000
   3.250   0.5145   0.00839   0.00193  -0.0264   0.1961   1.0000
   3.500   0.5421   0.00863   0.00209  -0.0263   0.1741   1.0000
   3.750   0.5697   0.00889   0.00227  -0.0263   0.1534   1.0000
   4.000   0.5972   0.00916   0.00247  -0.0262   0.1326   1.0000
   4.250   0.6247   0.00947   0.00270  -0.0261   0.1131   1.0000
   4.500   0.6520   0.00977   0.00294  -0.0260   0.0946   1.0000
   4.750   0.6792   0.01013   0.00321  -0.0260   0.0764   1.0000
   5.000   0.7064   0.01048   0.00351  -0.0259   0.0605   1.0000
   5.250   0.7334   0.01087   0.00385  -0.0258   0.0462   1.0000
   5.500   0.7603   0.01129   0.00422  -0.0257   0.0345   1.0000
   5.750   0.7872   0.01172   0.00462  -0.0255   0.0265   1.0000
   6.000   0.8139   0.01217   0.00507  -0.0254   0.0207   1.0000
   6.250   0.8406   0.01262   0.00554  -0.0252   0.0166   1.0000
   6.500   0.8671   0.01310   0.00607  -0.0250   0.0140   1.0000
   6.750   0.8934   0.01364   0.00665  -0.0248   0.0123   1.0000
   7.000   0.9196   0.01421   0.00732  -0.0246   0.0111   1.0000
   7.250   0.9456   0.01480   0.00799  -0.0243   0.0102   1.0000
   7.500   0.9712   0.01545   0.00872  -0.0241   0.0094   1.0000
   7.750   0.9960   0.01632   0.00969  -0.0238   0.0088   1.0000
   8.000   1.0213   0.01700   0.01048  -0.0234   0.0083   1.0000
   8.250   1.0462   0.01772   0.01131  -0.0231   0.0077   1.0000
   8.500   1.0706   0.01853   0.01223  -0.0228   0.0073   1.0000
   8.750   1.0944   0.01943   0.01325  -0.0224   0.0070   1.0000
   9.000   1.1174   0.02049   0.01443  -0.0220   0.0067   1.0000
   9.250   1.1383   0.02202   0.01611  -0.0214   0.0065   1.0000
   9.500   1.1602   0.02321   0.01750  -0.0209   0.0063   1.0000
   9.750   1.1810   0.02459   0.01908  -0.0203   0.0062   1.0000
  10.000   1.2006   0.02615   0.02088  -0.0196   0.0060   1.0000
  10.250   1.2187   0.02792   0.02291  -0.0189   0.0059   1.0000
  10.500   1.2349   0.02993   0.02519  -0.0182   0.0057   1.0000
  10.750   1.2488   0.03221   0.02775  -0.0174   0.0056   1.0000
  11.000   1.2596   0.03480   0.03064  -0.0166   0.0055   1.0000
  11.250   1.2665   0.03775   0.03390  -0.0158   0.0054   1.0000
  11.500   1.2680   0.04114   0.03760  -0.0151   0.0053   1.0000
  11.750   1.2622   0.04504   0.04180  -0.0148   0.0053   1.0000
  12.000   1.2445   0.04976   0.04677  -0.0156   0.0053   1.0000
  12.250   1.2232   0.05984   0.05711  -0.0263   0.0053   1.0000
  12.500   1.1929   0.07427   0.07176  -0.0387   0.0054   1.0000
  12.750   1.1577   0.08724   0.08485  -0.0468   0.0055   1.0000
  13.000   1.1184   0.10060   0.09830  -0.0541   0.0057   1.0000
  13.250   1.0723   0.11593   0.11370  -0.0619   0.0058   1.0000
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