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GOE 675 AIRFOIL (goe675-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 675 AIRFOIL (goe675-il)
Reynolds number: 100,000
Max Cl/Cd: 51.19 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe675-il-100000.txt
Download as CSV file: xf-goe675-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 675 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
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.2538   0.10862   0.10389  -0.0488   0.9580   0.1312
  -7.250  -0.2774   0.10762   0.10294  -0.0505   0.9506   0.1350
  -7.000  -0.3105   0.10465   0.10000  -0.0600   0.9409   0.1369
  -6.750  -0.2746   0.10104   0.09640  -0.0542   0.9398   0.1389
  -6.500  -0.2630   0.09896   0.09433  -0.0524   0.9345   0.1415
  -6.250  -0.2614   0.09687   0.09226  -0.0522   0.9279   0.1446
  -6.000  -0.2722   0.09178   0.08702  -0.0690   0.9182   0.1529
  -5.750  -0.2646   0.08914   0.08446  -0.0644   0.9121   0.1540
  -5.500  -0.2368   0.08636   0.08169  -0.0635   0.9067   0.1567
  -5.250  -0.2249   0.08222   0.07719  -0.0777   0.8940   0.1697
  -5.000  -0.1981   0.07816   0.07328  -0.0754   0.8885   0.1717
  -4.750  -0.1735   0.07610   0.07126  -0.0740   0.8818   0.1762
  -4.500  -0.1574   0.07210   0.06705  -0.0811   0.8722   0.1894
  -4.250  -0.1060   0.05635   0.05032  -0.0988   0.8691   0.1387
  -4.000  -0.0852   0.05513   0.04912  -0.0985   0.8619   0.1418
  -3.750  -0.0432   0.04681   0.03954  -0.1059   0.8565   0.1351
  -3.500  -0.0053   0.04527   0.03802  -0.1084   0.8514   0.1421
  -3.250   0.0473   0.04289   0.03489  -0.1132   0.8484   0.1519
  -3.000   0.0562   0.04212   0.03420  -0.1110   0.8374   0.1561
  -2.750   0.0984   0.04115   0.03307  -0.1135   0.8326   0.1654
  -2.500   0.1298   0.04005   0.03162  -0.1146   0.8256   0.1718
  -2.250   0.1579   0.03946   0.03108  -0.1148   0.8174   0.1776
  -2.000   0.2052   0.03821   0.02953  -0.1178   0.8135   0.1838
  -1.750   0.2249   0.03804   0.02908  -0.1166   0.8029   0.1870
  -1.500   0.2663   0.03675   0.02774  -0.1187   0.7977   0.1915
  -1.250   0.3148   0.03561   0.02653  -0.1214   0.7946   0.1984
  -1.000   0.3299   0.03564   0.02646  -0.1195   0.7820   0.2019
  -0.750   0.3760   0.03442   0.02515  -0.1217   0.7783   0.2083
  -0.500   0.4270   0.03316   0.02393  -0.1246   0.7762   0.2187
  -0.250   0.4395   0.03330   0.02400  -0.1220   0.7621   0.2248
   0.000   0.4893   0.03185   0.02269  -0.1246   0.7598   0.2392
   0.250   0.5050   0.03184   0.02277  -0.1225   0.7466   0.2515
   0.500   0.5532   0.03038   0.02145  -0.1247   0.7439   0.2852
   0.750   0.6030   0.02848   0.02003  -0.1271   0.7419   0.3737
   1.000   0.6188   0.02684   0.02009  -0.1238   0.7295   1.0000
   1.250   0.6665   0.02579   0.01870  -0.1258   0.7260   1.0000
   1.500   0.7169   0.02463   0.01731  -0.1283   0.7235   1.0000
   1.750   0.7350   0.02471   0.01729  -0.1262   0.7095   1.0000
   2.000   0.7858   0.02350   0.01590  -0.1288   0.7062   1.0000
   2.500   0.8382   0.02316   0.01537  -0.1272   0.6824   1.0000
   2.750   0.8781   0.02248   0.01455  -0.1283   0.6738   1.0000
   3.000   0.9049   0.02239   0.01438  -0.1277   0.6614   1.0000
   3.250   0.9504   0.02164   0.01346  -0.1299   0.6539   1.0000
   3.500   0.9717   0.02187   0.01363  -0.1285   0.6401   1.0000
   3.750   0.9997   0.02192   0.01359  -0.1282   0.6284   1.0000
   4.000   1.0383   0.02163   0.01313  -0.1296   0.6191   1.0000
   4.250   1.0576   0.02208   0.01355  -0.1281   0.6063   1.0000
   4.500   1.0878   0.02222   0.01359  -0.1283   0.5965   1.0000
   4.750   1.1154   0.02244   0.01373  -0.1281   0.5861   1.0000
   5.000   1.1379   0.02289   0.01415  -0.1272   0.5759   1.0000
   5.250   1.1701   0.02305   0.01418  -0.1278   0.5672   1.0000
   5.500   1.1888   0.02367   0.01484  -0.1263   0.5574   1.0000
   5.750   1.2215   0.02386   0.01491  -0.1270   0.5494   1.0000
   6.000   1.2387   0.02456   0.01566  -0.1254   0.5403   1.0000
   6.250   1.2693   0.02486   0.01588  -0.1259   0.5325   1.0000
   6.500   1.2882   0.02556   0.01662  -0.1246   0.5242   1.0000
   6.750   1.3145   0.02599   0.01702  -0.1243   0.5163   1.0000
   7.000   1.3386   0.02659   0.01762  -0.1238   0.5089   1.0000
   7.250   1.3578   0.02724   0.01831  -0.1226   0.5007   1.0000
   7.500   1.3914   0.02761   0.01857  -0.1236   0.4939   1.0000
   7.750   1.4011   0.02855   0.01968  -0.1209   0.4857   1.0000
   8.000   1.4354   0.02889   0.01991  -0.1220   0.4788   1.0000
   8.250   1.4465   0.02990   0.02107  -0.1196   0.4714   1.0000
   8.500   1.4687   0.03055   0.02175  -0.1189   0.4642   1.0000
   8.750   1.4978   0.03116   0.02233  -0.1192   0.4575   1.0000
   9.000   1.5047   0.03222   0.02356  -0.1162   0.4497   1.0000
   9.250   1.5476   0.03235   0.02351  -0.1185   0.4419   1.0000
   9.500   1.5425   0.03365   0.02508  -0.1138   0.4340   1.0000
   9.750   1.5777   0.03376   0.02505  -0.1148   0.4251   1.0000
  10.000   1.5783   0.03495   0.02644  -0.1109   0.4173   1.0000
  10.250   1.6022   0.03530   0.02677  -0.1103   0.4087   1.0000
  10.500   1.6124   0.03622   0.02778  -0.1079   0.4009   1.0000
  10.750   1.6209   0.03699   0.02864  -0.1051   0.3930   1.0000
  11.000   1.6468   0.03741   0.02903  -0.1050   0.3851   1.0000
  11.250   1.6356   0.03865   0.03048  -0.0994   0.3779   1.0000
  11.500   1.6713   0.03841   0.03009  -0.1004   0.3686   1.0000
  11.750   1.6485   0.04007   0.03202  -0.0936   0.3618   1.0000
  12.000   1.6880   0.03943   0.03116  -0.0949   0.3522   1.0000
  12.250   1.6584   0.04162   0.03368  -0.0879   0.3461   1.0000
  12.500   1.6687   0.04215   0.03426  -0.0858   0.3384   1.0000
  12.750   1.6697   0.04330   0.03549  -0.0828   0.3313   1.0000
  13.000   1.6612   0.04490   0.03725  -0.0791   0.3239   1.0000
  13.250   1.6750   0.04524   0.03757  -0.0775   0.3161   1.0000
  13.500   1.6556   0.04777   0.04032  -0.0734   0.3090   1.0000
  13.750   1.6708   0.04788   0.04037  -0.0720   0.3005   1.0000
  14.000   1.6473   0.05110   0.04384  -0.0683   0.2933   1.0000
  14.250   1.6623   0.05128   0.04395  -0.0670   0.2850   1.0000
  14.500   1.6358   0.05522   0.04818  -0.0639   0.2779   1.0000
  14.750   1.6469   0.05576   0.04866  -0.0626   0.2694   1.0000
  15.000   1.6197   0.06032   0.05349  -0.0602   0.2619   1.0000
  15.250   1.6222   0.06190   0.05506  -0.0590   0.2529   1.0000
  15.500   1.5989   0.06667   0.06006  -0.0577   0.2445   1.0000
  15.750   1.5889   0.07007   0.06353  -0.0568   0.2350   1.0000
  16.000   1.5818   0.07321   0.06666  -0.0562   0.2238   1.0000
  16.250   1.5531   0.07966   0.07333  -0.0563   0.2141   1.0000
  16.500   1.5335   0.08507   0.07882  -0.0566   0.2021   1.0000
  16.750   1.5126   0.09091   0.08468  -0.0573   0.1886   1.0000
  17.000   1.4897   0.09726   0.09102  -0.0584   0.1735   1.0000
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