Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

GOE 675 AIRFOIL (goe675-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 675 AIRFOIL (goe675-il)
Reynolds number: 1,000,000
Max Cl/Cd: 111.89 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe675-il-1000000-n5.txt
Download as CSV file: xf-goe675-il-1000000-n5.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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -15.500  -0.6257   0.08330   0.08041  -0.0898   0.9084   0.0247
 -15.250  -0.6502   0.07610   0.07310  -0.0946   0.9023   0.0248
 -15.000  -0.8899   0.03231   0.02859  -0.1368   0.8815   0.0245
 -14.750  -0.8862   0.02876   0.02482  -0.1396   0.8759   0.0245
 -14.500  -0.8738   0.02683   0.02273  -0.1405   0.8711   0.0246
 -14.250  -0.8578   0.02538   0.02113  -0.1408   0.8670   0.0247
 -14.000  -0.8392   0.02414   0.01980  -0.1410   0.8638   0.0248
 -13.750  -0.8191   0.02309   0.01864  -0.1411   0.8602   0.0249
 -13.500  -0.7979   0.02216   0.01761  -0.1411   0.8564   0.0250
 -13.250  -0.7775   0.02113   0.01648  -0.1411   0.8528   0.0252
 -13.000  -0.7564   0.02016   0.01540  -0.1410   0.8492   0.0254
 -12.750  -0.7336   0.01933   0.01450  -0.1410   0.8462   0.0257
 -12.500  -0.7098   0.01860   0.01370  -0.1409   0.8430   0.0259
 -12.250  -0.6854   0.01794   0.01297  -0.1408   0.8396   0.0260
 -12.000  -0.6606   0.01734   0.01230  -0.1408   0.8362   0.0262
 -11.750  -0.6353   0.01680   0.01168  -0.1407   0.8328   0.0264
 -11.500  -0.6098   0.01629   0.01109  -0.1406   0.8296   0.0266
 -11.250  -0.5835   0.01580   0.01055  -0.1406   0.8268   0.0268
 -11.000  -0.5571   0.01533   0.01003  -0.1405   0.8236   0.0270
 -10.750  -0.5305   0.01490   0.00953  -0.1405   0.8204   0.0273
 -10.500  -0.5037   0.01449   0.00906  -0.1405   0.8170   0.0275
 -10.250  -0.4768   0.01411   0.00861  -0.1404   0.8137   0.0277
 -10.000  -0.4496   0.01376   0.00819  -0.1404   0.8106   0.0280
  -9.750  -0.4220   0.01341   0.00779  -0.1404   0.8078   0.0282
  -9.500  -0.3943   0.01308   0.00742  -0.1405   0.8047   0.0284
  -9.250  -0.3665   0.01278   0.00707  -0.1405   0.8012   0.0286
  -9.000  -0.3391   0.01240   0.00663  -0.1405   0.7977   0.0290
  -8.750  -0.3116   0.01207   0.00625  -0.1404   0.7941   0.0294
  -8.500  -0.2835   0.01176   0.00591  -0.1405   0.7908   0.0298
  -8.250  -0.2554   0.01147   0.00559  -0.1406   0.7863   0.0302
  -8.000  -0.2273   0.01123   0.00530  -0.1406   0.7809   0.0308
  -7.750  -0.1993   0.01101   0.00502  -0.1405   0.7758   0.0313
  -7.500  -0.1707   0.01079   0.00477  -0.1406   0.7716   0.0319
  -7.250  -0.1420   0.01058   0.00453  -0.1407   0.7673   0.0323
  -7.000  -0.1137   0.01035   0.00427  -0.1407   0.7624   0.0331
  -6.750  -0.0855   0.01015   0.00402  -0.1407   0.7574   0.0341
  -6.500  -0.0568   0.00994   0.00381  -0.1408   0.7526   0.0352
  -6.250  -0.0281   0.00977   0.00361  -0.1409   0.7473   0.0364
  -6.000   0.0002   0.00958   0.00339  -0.1409   0.7417   0.0388
  -5.750   0.0287   0.00938   0.00320  -0.1410   0.7366   0.0427
  -5.500   0.0573   0.00919   0.00305  -0.1411   0.7307   0.0501
  -5.250   0.0859   0.00909   0.00295  -0.1411   0.7244   0.0567
  -5.000   0.1147   0.00902   0.00287  -0.1412   0.7179   0.0609
  -4.750   0.1434   0.00896   0.00279  -0.1412   0.7095   0.0635
  -4.500   0.1720   0.00892   0.00272  -0.1412   0.7022   0.0661
  -4.250   0.2009   0.00887   0.00265  -0.1413   0.6955   0.0680
  -4.000   0.2295   0.00883   0.00257  -0.1414   0.6887   0.0694
  -3.750   0.2582   0.00877   0.00250  -0.1414   0.6817   0.0710
  -3.500   0.2867   0.00874   0.00245  -0.1414   0.6732   0.0728
  -3.250   0.3151   0.00872   0.00239  -0.1414   0.6652   0.0743
  -3.000   0.3436   0.00871   0.00234  -0.1414   0.6567   0.0755
  -2.750   0.3719   0.00871   0.00230  -0.1414   0.6486   0.0763
  -2.500   0.4000   0.00866   0.00223  -0.1414   0.6386   0.0781
  -2.250   0.4278   0.00866   0.00220  -0.1413   0.6280   0.0800
  -2.000   0.4553   0.00868   0.00217  -0.1411   0.6162   0.0813
  -1.750   0.4834   0.00869   0.00215  -0.1411   0.6052   0.0825
  -1.500   0.5107   0.00873   0.00214  -0.1409   0.5929   0.0838
  -1.250   0.5377   0.00881   0.00215  -0.1407   0.5777   0.0850
  -1.000   0.5641   0.00888   0.00215  -0.1403   0.5597   0.0870
  -0.750   0.5902   0.00898   0.00218  -0.1399   0.5397   0.0887
  -0.500   0.6159   0.00911   0.00223  -0.1395   0.5181   0.0905
  -0.250   0.6409   0.00928   0.00230  -0.1389   0.4944   0.0924
   0.000   0.6656   0.00947   0.00239  -0.1383   0.4724   0.0944
   0.250   0.6908   0.00963   0.00247  -0.1378   0.4547   0.0983
   0.500   0.7168   0.00973   0.00255  -0.1374   0.4419   0.1034
   0.750   0.7430   0.00982   0.00263  -0.1371   0.4327   0.1105
   1.000   0.7693   0.00990   0.00271  -0.1367   0.4241   0.1203
   1.250   0.7953   0.01000   0.00280  -0.1364   0.4164   0.1320
   1.500   0.8218   0.01006   0.00288  -0.1361   0.4099   0.1447
   1.750   0.8478   0.01014   0.00298  -0.1358   0.4037   0.1578
   2.000   0.8738   0.01022   0.00307  -0.1355   0.3986   0.1744
   2.250   0.9004   0.01023   0.00317  -0.1353   0.3943   0.2068
   2.500   0.9264   0.01026   0.00330  -0.1350   0.3892   0.2526
   2.750   0.9517   0.01034   0.00344  -0.1346   0.3839   0.2849
   3.000   0.9774   0.01042   0.00356  -0.1342   0.3799   0.3115
   3.250   1.0035   0.01045   0.00369  -0.1339   0.3765   0.3439
   3.500   1.0292   0.01043   0.00384  -0.1336   0.3722   0.4193
   3.750   1.0536   0.01032   0.00406  -0.1333   0.3663   0.5786
   4.250   1.1002   0.00984   0.00447  -0.1315   0.3565   1.0000
   4.500   1.1234   0.01004   0.00463  -0.1306   0.3500   1.0000
   4.750   1.1449   0.01027   0.00481  -0.1294   0.3432   1.0000
   5.000   1.1676   0.01045   0.00497  -0.1285   0.3373   1.0000
   5.250   1.1893   0.01069   0.00518  -0.1274   0.3312   1.0000
   5.500   1.2112   0.01093   0.00539  -0.1264   0.3256   1.0000
   5.750   1.2340   0.01115   0.00559  -0.1256   0.3203   1.0000
   6.000   1.2552   0.01143   0.00584  -0.1245   0.3137   1.0000
   6.250   1.2769   0.01171   0.00609  -0.1235   0.3080   1.0000
   6.500   1.2986   0.01199   0.00635  -0.1226   0.3010   1.0000
   6.750   1.3184   0.01236   0.00668  -0.1214   0.2935   1.0000
   7.000   1.3397   0.01267   0.00697  -0.1204   0.2859   1.0000
   7.250   1.3587   0.01310   0.00735  -0.1191   0.2775   1.0000
   7.500   1.3785   0.01349   0.00772  -0.1180   0.2682   1.0000
   7.750   1.3971   0.01396   0.00814  -0.1167   0.2592   1.0000
   8.000   1.4146   0.01449   0.00862  -0.1153   0.2483   1.0000
   8.250   1.4315   0.01507   0.00913  -0.1139   0.2356   1.0000
   8.500   1.4467   0.01574   0.00973  -0.1122   0.2216   1.0000
   8.750   1.4605   0.01651   0.01042  -0.1104   0.2057   1.0000
   9.000   1.4720   0.01743   0.01123  -0.1083   0.1883   1.0000
   9.250   1.4837   0.01836   0.01206  -0.1064   0.1718   1.0000
   9.500   1.4952   0.01931   0.01294  -0.1044   0.1573   1.0000
   9.750   1.5047   0.02042   0.01394  -0.1023   0.1397   1.0000
  10.000   1.5116   0.02169   0.01510  -0.1000   0.1213   1.0000
  10.250   1.5139   0.02331   0.01657  -0.0972   0.0964   1.0000
  10.500   1.5172   0.02491   0.01805  -0.0946   0.0780   1.0000
  10.750   1.5225   0.02640   0.01949  -0.0924   0.0644   1.0000
  11.000   1.5177   0.02868   0.02162  -0.0893   0.0387   1.0000
  11.250   1.5266   0.03001   0.02295  -0.0876   0.0345   1.0000
  11.500   1.5371   0.03125   0.02421  -0.0862   0.0326   1.0000
  11.750   1.5475   0.03254   0.02552  -0.0849   0.0312   1.0000
  12.000   1.5587   0.03379   0.02680  -0.0837   0.0304   1.0000
  12.250   1.5693   0.03511   0.02816  -0.0826   0.0297   1.0000
  12.500   1.5788   0.03655   0.02963  -0.0814   0.0290   1.0000
  12.750   1.5877   0.03807   0.03119  -0.0802   0.0284   1.0000
  13.000   1.5960   0.03968   0.03284  -0.0790   0.0279   1.0000
  13.250   1.6032   0.04143   0.03463  -0.0779   0.0274   1.0000
  13.500   1.6113   0.04313   0.03638  -0.0769   0.0271   1.0000
  13.750   1.6189   0.04491   0.03822  -0.0760   0.0268   1.0000
  14.000   1.6262   0.04673   0.04009  -0.0750   0.0266   1.0000
  14.250   1.6324   0.04872   0.04213  -0.0742   0.0263   1.0000
  14.500   1.6380   0.05080   0.04427  -0.0733   0.0261   1.0000
  14.750   1.6431   0.05296   0.04649  -0.0726   0.0258   1.0000
  15.000   1.6466   0.05535   0.04894  -0.0719   0.0255   1.0000
  15.250   1.6494   0.05783   0.05148  -0.0712   0.0252   1.0000
  15.500   1.6515   0.06041   0.05412  -0.0706   0.0249   1.0000
  15.750   1.6520   0.06326   0.05704  -0.0700   0.0247   1.0000
  16.000   1.6516   0.06626   0.06011  -0.0696   0.0244   1.0000
  16.250   1.6502   0.06942   0.06335  -0.0692   0.0242   1.0000
  16.500   1.6475   0.07276   0.06676  -0.0689   0.0240   1.0000
  16.750   1.6431   0.07638   0.07047  -0.0687   0.0238   1.0000
  17.000   1.6371   0.08028   0.07445  -0.0687   0.0235   1.0000
  17.250   1.6329   0.08401   0.07826  -0.0688   0.0234   1.0000
  17.500   1.6297   0.08764   0.08198  -0.0690   0.0233   1.0000
  17.750   1.6256   0.09140   0.08582  -0.0692   0.0231   1.0000
  18.000   1.6209   0.09526   0.08978  -0.0696   0.0230   1.0000
  18.250   1.6160   0.09921   0.09381  -0.0701   0.0228   1.0000
  18.500   1.6107   0.10323   0.09792  -0.0707   0.0227   1.0000
  18.750   1.6046   0.10742   0.10219  -0.0714   0.0226   1.0000
<< Back to GOE 675 AIRFOIL (goe675-il)

Polar data table (+)

Polar graphs


<< Back to GOE 675 AIRFOIL (goe675-il)