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GOE 675 AIRFOIL (goe675-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 675 AIRFOIL (goe675-il)
Reynolds number: 200,000
Max Cl/Cd: 75.32 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe675-il-200000.txt
Download as CSV file: xf-goe675-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.0472   0.09449   0.09054  -0.1015   0.9560   0.0830
  -9.000  -0.0386   0.09111   0.08715  -0.1057   0.9519   0.0860
  -8.750  -0.0684   0.08531   0.08139  -0.1163   0.9405   0.0880
  -8.500  -0.0394   0.08252   0.07859  -0.1152   0.9398   0.0887
  -8.250  -0.0145   0.08001   0.07606  -0.1159   0.9382   0.0896
  -8.000  -0.0124   0.07856   0.07464  -0.1141   0.9295   0.0905
  -7.750  -0.1162   0.05363   0.04936  -0.1370   0.9073   0.0707
  -7.500  -0.1117   0.04594   0.04135  -0.1424   0.9036   0.0701
  -7.250  -0.1373   0.03954   0.03442  -0.1403   0.8910   0.0699
  -7.000  -0.1270   0.03255   0.02648  -0.1426   0.8873   0.0713
  -6.750  -0.0932   0.03212   0.02614  -0.1439   0.8857   0.0728
  -6.500  -0.0907   0.03198   0.02597  -0.1399   0.8760   0.0738
  -6.250  -0.0645   0.02986   0.02342  -0.1406   0.8724   0.0770
  -6.000  -0.0324   0.02813   0.02141  -0.1420   0.8699   0.0806
  -5.750   0.0040   0.02746   0.02072  -0.1434   0.8678   0.0843
  -5.500   0.0157   0.02646   0.01932  -0.1409   0.8592   0.0885
  -5.250   0.0470   0.02592   0.01889  -0.1415   0.8549   0.0921
  -5.000   0.0806   0.02490   0.01755  -0.1423   0.8519   0.0987
  -4.750   0.1156   0.02437   0.01713  -0.1434   0.8496   0.1034
  -4.500   0.1357   0.02419   0.01676  -0.1419   0.8422   0.1084
  -4.250   0.1637   0.02337   0.01592  -0.1419   0.8369   0.1127
  -4.000   0.1970   0.02285   0.01537  -0.1426   0.8336   0.1177
  -3.750   0.2314   0.02227   0.01453  -0.1433   0.8311   0.1226
  -3.500   0.2523   0.02189   0.01426  -0.1423   0.8245   0.1267
  -3.250   0.2788   0.02167   0.01403  -0.1419   0.8191   0.1317
  -3.000   0.3112   0.02128   0.01346  -0.1423   0.8157   0.1360
  -2.750   0.3447   0.02020   0.01232  -0.1431   0.8130   0.1392
  -2.500   0.3670   0.01995   0.01210  -0.1421   0.8061   0.1421
  -2.250   0.3947   0.01953   0.01165  -0.1418   0.8007   0.1451
  -2.000   0.4274   0.01894   0.01098  -0.1423   0.7971   0.1482
  -1.750   0.4618   0.01840   0.01032  -0.1429   0.7942   0.1517
  -1.500   0.4819   0.01809   0.01008  -0.1415   0.7854   0.1550
  -1.250   0.5126   0.01753   0.00956  -0.1417   0.7806   0.1593
  -1.000   0.5461   0.01699   0.00898  -0.1423   0.7770   0.1648
  -0.750   0.5690   0.01686   0.00886  -0.1412   0.7687   0.1701
  -0.500   0.5985   0.01631   0.00841  -0.1412   0.7628   0.1793
  -0.250   0.6325   0.01573   0.00784  -0.1419   0.7584   0.1923
   0.000   0.6540   0.01557   0.00781  -0.1406   0.7487   0.2097
   0.250   0.6854   0.01502   0.00744  -0.1410   0.7428   0.2528
   0.500   0.7097   0.01462   0.00738  -0.1403   0.7339   0.3407
   0.750   0.7359   0.01377   0.00718  -0.1398   0.7261   0.5341
   1.000   0.7714   0.01276   0.00711  -0.1403   0.7168   1.0000
   1.250   0.8003   0.01264   0.00683  -0.1401   0.7076   1.0000
   1.500   0.8245   0.01267   0.00677  -0.1391   0.6958   1.0000
   1.750   0.8521   0.01262   0.00658  -0.1387   0.6845   1.0000
   2.000   0.8789   0.01260   0.00642  -0.1382   0.6717   1.0000
   2.250   0.9027   0.01266   0.00640  -0.1372   0.6565   1.0000
   2.500   0.9270   0.01275   0.00638  -0.1363   0.6406   1.0000
   2.750   0.9511   0.01288   0.00637  -0.1354   0.6235   1.0000
   3.000   0.9747   0.01306   0.00641  -0.1344   0.6058   1.0000
   3.250   0.9977   0.01328   0.00649  -0.1334   0.5883   1.0000
   3.500   1.0206   0.01355   0.00663  -0.1324   0.5718   1.0000
   3.750   1.0432   0.01385   0.00680  -0.1313   0.5564   1.0000
   4.000   1.0660   0.01417   0.00699  -0.1304   0.5426   1.0000
   4.500   1.1116   0.01486   0.00747  -0.1286   0.5185   1.0000
   4.750   1.1352   0.01523   0.00774  -0.1278   0.5086   1.0000
   5.000   1.1582   0.01559   0.00802  -0.1270   0.4988   1.0000
   5.250   1.1820   0.01598   0.00835  -0.1264   0.4903   1.0000
   5.500   1.2052   0.01635   0.00867  -0.1256   0.4820   1.0000
   5.750   1.2303   0.01677   0.00901  -0.1253   0.4746   1.0000
   6.000   1.2521   0.01715   0.00940  -0.1243   0.4668   1.0000
   6.250   1.2796   0.01761   0.00971  -0.1244   0.4599   1.0000
   6.500   1.2996   0.01799   0.01016  -0.1231   0.4527   1.0000
   6.750   1.3227   0.01840   0.01054  -0.1225   0.4458   1.0000
   7.000   1.3478   0.01887   0.01096  -0.1222   0.4392   1.0000
   7.250   1.3666   0.01927   0.01141  -0.1207   0.4319   1.0000
   7.500   1.3919   0.01973   0.01176  -0.1205   0.4249   1.0000
   7.750   1.4091   0.02016   0.01228  -0.1188   0.4180   1.0000
   8.000   1.4277   0.02057   0.01269  -0.1173   0.4109   1.0000
   8.250   1.4526   0.02107   0.01312  -0.1171   0.4043   1.0000
   8.500   1.4642   0.02147   0.01365  -0.1144   0.3979   1.0000
   8.750   1.4821   0.02190   0.01407  -0.1129   0.3916   1.0000
   9.000   1.5033   0.02241   0.01456  -0.1120   0.3855   1.0000
   9.250   1.5141   0.02289   0.01515  -0.1094   0.3792   1.0000
   9.500   1.5306   0.02335   0.01562  -0.1077   0.3730   1.0000
   9.750   1.5470   0.02389   0.01619  -0.1061   0.3669   1.0000
  10.000   1.5565   0.02446   0.01687  -0.1035   0.3604   1.0000
  10.250   1.5722   0.02497   0.01735  -0.1019   0.3541   1.0000
  10.500   1.5815   0.02565   0.01814  -0.0994   0.3475   1.0000
  10.750   1.5890   0.02634   0.01890  -0.0968   0.3402   1.0000
  11.000   1.5996   0.02705   0.01960  -0.0947   0.3329   1.0000
  11.250   1.6047   0.02794   0.02062  -0.0920   0.3251   1.0000
  11.500   1.6167   0.02869   0.02132  -0.0902   0.3184   1.0000
  11.750   1.6228   0.02972   0.02254  -0.0879   0.3112   1.0000
  12.000   1.6314   0.03069   0.02353  -0.0859   0.3043   1.0000
  12.250   1.6380   0.03181   0.02475  -0.0839   0.2967   1.0000
  12.500   1.6435   0.03303   0.02601  -0.0818   0.2885   1.0000
  12.750   1.6494   0.03432   0.02739  -0.0799   0.2803   1.0000
  13.000   1.6530   0.03577   0.02887  -0.0779   0.2717   1.0000
  13.250   1.6563   0.03736   0.03055  -0.0760   0.2619   1.0000
  13.500   1.6581   0.03913   0.03233  -0.0741   0.2526   1.0000
  13.750   1.6599   0.04103   0.03430  -0.0724   0.2422   1.0000
  14.000   1.6609   0.04309   0.03642  -0.0708   0.2314   1.0000
  14.250   1.6594   0.04545   0.03881  -0.0692   0.2201   1.0000
  14.500   1.6555   0.04816   0.04153  -0.0677   0.2077   1.0000
  14.750   1.6492   0.05125   0.04462  -0.0663   0.1939   1.0000
  15.000   1.6400   0.05475   0.04813  -0.0650   0.1785   1.0000
  15.250   1.6269   0.05886   0.05222  -0.0639   0.1612   1.0000
  15.500   1.6089   0.06371   0.05703  -0.0630   0.1430   1.0000
  15.750   1.5877   0.06914   0.06241  -0.0624   0.1233   1.0000
  16.000   1.5632   0.07523   0.06843  -0.0622   0.1060   1.0000
  16.250   1.5395   0.08146   0.07463  -0.0623   0.0934   1.0000
  16.500   1.5168   0.08773   0.08090  -0.0628   0.0851   1.0000
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