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GOE 682 AIRFOIL (goe682-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 682 AIRFOIL (goe682-il)
Reynolds number: 500,000
Max Cl/Cd: 97.4 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe682-il-500000-n5.txt
Download as CSV file: xf-goe682-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 682 AIRFOIL                                 
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.3838   0.12228   0.11975  -0.0342   1.0000   0.0146
 -12.250  -0.3783   0.11966   0.11715  -0.0349   1.0000   0.0150
 -11.250  -0.7205   0.03092   0.02768  -0.0958   0.9850   0.0215
 -11.000  -0.7031   0.02787   0.02430  -0.0979   0.9790   0.0220
 -10.750  -0.6741   0.02703   0.02342  -0.0994   0.9762   0.0225
 -10.500  -0.6442   0.02666   0.02302  -0.1005   0.9733   0.0229
 -10.250  -0.6166   0.02604   0.02234  -0.1013   0.9688   0.0234
 -10.000  -0.5871   0.02502   0.02119  -0.1029   0.9657   0.0240
  -9.750  -0.5607   0.02382   0.01981  -0.1039   0.9611   0.0247
  -9.500  -0.5343   0.02251   0.01827  -0.1049   0.9558   0.0255
  -9.250  -0.5063   0.02120   0.01670  -0.1060   0.9512   0.0261
  -9.000  -0.4799   0.02027   0.01556  -0.1064   0.9445   0.0266
  -8.750  -0.4529   0.01891   0.01400  -0.1072   0.9391   0.0272
  -8.500  -0.4273   0.01808   0.01307  -0.1072   0.9316   0.0278
  -8.250  -0.3988   0.01748   0.01237  -0.1077   0.9251   0.0282
  -8.000  -0.3722   0.01697   0.01177  -0.1077   0.9166   0.0288
  -7.750  -0.3451   0.01645   0.01114  -0.1077   0.9087   0.0294
  -7.500  -0.3189   0.01583   0.01039  -0.1076   0.9000   0.0299
  -7.250  -0.2931   0.01522   0.00964  -0.1073   0.8914   0.0304
  -7.000  -0.2670   0.01464   0.00891  -0.1070   0.8822   0.0309
  -6.750  -0.2415   0.01412   0.00826  -0.1066   0.8724   0.0315
  -6.500  -0.2151   0.01371   0.00771  -0.1063   0.8632   0.0320
  -6.250  -0.1891   0.01332   0.00722  -0.1059   0.8534   0.0325
  -6.000  -0.1631   0.01293   0.00670  -0.1055   0.8439   0.0328
  -5.750  -0.1382   0.01231   0.00597  -0.1049   0.8331   0.0335
  -5.500  -0.1128   0.01191   0.00549  -0.1044   0.8208   0.0341
  -5.250  -0.0871   0.01161   0.00512  -0.1038   0.8076   0.0347
  -5.000  -0.0614   0.01136   0.00477  -0.1033   0.7934   0.0354
  -4.750  -0.0355   0.01113   0.00446  -0.1028   0.7804   0.0361
  -4.500  -0.0095   0.01092   0.00415  -0.1023   0.7689   0.0369
  -4.250   0.0168   0.01071   0.00387  -0.1019   0.7584   0.0378
  -4.000   0.0433   0.01054   0.00363  -0.1014   0.7484   0.0388
  -3.500   0.0960   0.01016   0.00311  -0.1006   0.7288   0.0409
  -3.250   0.1222   0.00997   0.00288  -0.1002   0.7195   0.0425
  -3.000   0.1488   0.00984   0.00271  -0.0998   0.7096   0.0442
  -2.750   0.1755   0.00973   0.00255  -0.0994   0.7004   0.0463
  -2.500   0.2021   0.00964   0.00241  -0.0990   0.6918   0.0483
  -2.250   0.2289   0.00951   0.00226  -0.0987   0.6835   0.0516
  -1.750   0.2824   0.00937   0.00206  -0.0980   0.6662   0.0600
  -1.500   0.3089   0.00928   0.00196  -0.0976   0.6583   0.0674
  -1.250   0.3357   0.00922   0.00188  -0.0973   0.6489   0.0747
  -1.000   0.3620   0.00916   0.00181  -0.0969   0.6386   0.0862
  -0.750   0.3878   0.00903   0.00177  -0.0964   0.6279   0.1192
  -0.500   0.4140   0.00893   0.00176  -0.0960   0.6177   0.1619
  -0.250   0.4401   0.00890   0.00177  -0.0956   0.6068   0.1904
   0.000   0.4663   0.00887   0.00177  -0.0952   0.5960   0.2141
   0.250   0.4927   0.00885   0.00178  -0.0948   0.5852   0.2363
   0.500   0.5187   0.00882   0.00180  -0.0944   0.5730   0.2645
   0.750   0.5442   0.00879   0.00182  -0.0939   0.5590   0.3012
   1.000   0.5691   0.00872   0.00185  -0.0933   0.5427   0.3614
   1.250   0.5911   0.00830   0.00194  -0.0923   0.5286   0.5608
   1.500   0.6057   0.00756   0.00208  -0.0892   0.5163   0.8632
   2.000   0.6987   0.00779   0.00223  -0.0973   0.4816   1.0000
   2.250   0.7224   0.00797   0.00231  -0.0964   0.4658   1.0000
   2.500   0.7462   0.00815   0.00240  -0.0955   0.4519   1.0000
   2.750   0.7704   0.00832   0.00250  -0.0947   0.4397   1.0000
   3.000   0.7948   0.00849   0.00260  -0.0940   0.4286   1.0000
   3.250   0.8191   0.00867   0.00273  -0.0932   0.4181   1.0000
   3.500   0.8433   0.00885   0.00285  -0.0924   0.4071   1.0000
   3.750   0.8678   0.00903   0.00298  -0.0917   0.3957   1.0000
   4.000   0.8920   0.00923   0.00313  -0.0910   0.3836   1.0000
   4.250   0.9159   0.00944   0.00329  -0.0902   0.3703   1.0000
   4.500   0.9397   0.00966   0.00345  -0.0894   0.3571   1.0000
   4.750   0.9633   0.00989   0.00363  -0.0886   0.3422   1.0000
   5.000   0.9866   0.01014   0.00382  -0.0877   0.3257   1.0000
   5.250   1.0094   0.01042   0.00403  -0.0868   0.3073   1.0000
   5.500   1.0311   0.01077   0.00427  -0.0857   0.2864   1.0000
   6.000   1.0743   0.01148   0.00482  -0.0835   0.2541   1.0000
   6.250   1.0966   0.01178   0.00509  -0.0826   0.2441   1.0000
   6.500   1.1184   0.01210   0.00539  -0.0815   0.2357   1.0000
   6.750   1.1406   0.01239   0.00567  -0.0805   0.2272   1.0000
   7.000   1.1617   0.01274   0.00598  -0.0794   0.2187   1.0000
   7.250   1.1832   0.01305   0.00628  -0.0783   0.2100   1.0000
   7.500   1.2039   0.01339   0.00661  -0.0771   0.2029   1.0000
   7.750   1.2254   0.01367   0.00691  -0.0761   0.1961   1.0000
   8.000   1.2451   0.01405   0.00726  -0.0747   0.1883   1.0000
   8.250   1.2656   0.01436   0.00758  -0.0735   0.1795   1.0000
   8.500   1.2840   0.01473   0.00794  -0.0720   0.1701   1.0000
   8.750   1.3007   0.01513   0.00832  -0.0701   0.1593   1.0000
   9.000   1.3160   0.01561   0.00873  -0.0681   0.1434   1.0000
   9.250   1.3257   0.01637   0.00932  -0.0652   0.1145   1.0000
   9.500   1.3315   0.01738   0.01014  -0.0619   0.0868   1.0000
   9.750   1.3408   0.01823   0.01092  -0.0593   0.0724   1.0000
  10.000   1.3504   0.01908   0.01173  -0.0567   0.0584   1.0000
  10.250   1.3549   0.02026   0.01278  -0.0537   0.0384   1.0000
  10.500   1.3595   0.02147   0.01392  -0.0508   0.0248   1.0000
  10.750   1.3678   0.02250   0.01495  -0.0485   0.0198   1.0000
  11.000   1.3768   0.02352   0.01600  -0.0465   0.0172   1.0000
  11.250   1.3874   0.02447   0.01702  -0.0447   0.0160   1.0000
  11.500   1.3968   0.02554   0.01815  -0.0429   0.0150   1.0000
  11.750   1.4045   0.02677   0.01944  -0.0411   0.0140   1.0000
  12.000   1.4122   0.02805   0.02079  -0.0394   0.0133   1.0000
  12.250   1.4207   0.02931   0.02214  -0.0379   0.0128   1.0000
  12.500   1.4283   0.03070   0.02360  -0.0365   0.0122   1.0000
  12.750   1.4344   0.03226   0.02525  -0.0352   0.0117   1.0000
  13.000   1.4391   0.03400   0.02707  -0.0339   0.0112   1.0000
  13.250   1.4416   0.03601   0.02916  -0.0328   0.0107   1.0000
  13.500   1.4424   0.03828   0.03152  -0.0317   0.0104   1.0000
  13.750   1.4446   0.04049   0.03382  -0.0309   0.0102   1.0000
  14.000   1.4463   0.04283   0.03628  -0.0302   0.0100   1.0000
  14.250   1.4477   0.04530   0.03884  -0.0297   0.0097   1.0000
  14.500   1.4479   0.04799   0.04164  -0.0294   0.0095   1.0000
  14.750   1.4469   0.05091   0.04466  -0.0292   0.0092   1.0000
  15.000   1.4445   0.05410   0.04796  -0.0293   0.0091   1.0000
  15.250   1.4423   0.05738   0.05134  -0.0295   0.0088   1.0000
  15.500   1.4376   0.06111   0.05519  -0.0300   0.0087   1.0000
  15.750   1.4327   0.06499   0.05918  -0.0306   0.0085   1.0000
  16.000   1.4273   0.06906   0.06336  -0.0315   0.0084   1.0000
  16.250   1.4202   0.07352   0.06793  -0.0326   0.0083   1.0000
  16.500   1.4122   0.07822   0.07274  -0.0340   0.0081   1.0000
  16.750   1.4027   0.08331   0.07793  -0.0356   0.0080   1.0000
  17.000   1.3901   0.08904   0.08379  -0.0376   0.0079   1.0000
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