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GOE 626 AIRFOIL (goe626-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 626 AIRFOIL (goe626-il)
Reynolds number: 200,000
Max Cl/Cd: 64.9 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe626-il-200000-n5.txt
Download as CSV file: xf-goe626-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 626 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -16.250  -0.6012   0.10868   0.10372  -0.0632   1.0000   0.0365
 -16.000  -0.6320   0.09976   0.09460  -0.0680   1.0000   0.0366
 -15.750  -0.6469   0.09407   0.08878  -0.0708   1.0000   0.0367
 -15.500  -0.6577   0.08929   0.08388  -0.0729   1.0000   0.0368
 -15.250  -0.6656   0.08513   0.07963  -0.0747   1.0000   0.0370
 -15.000  -0.6726   0.08128   0.07569  -0.0762   1.0000   0.0372
 -14.750  -0.6765   0.07807   0.07240  -0.0772   1.0000   0.0374
 -14.500  -0.6810   0.07491   0.06916  -0.0780   1.0000   0.0376
 -14.250  -0.6772   0.07327   0.06755  -0.0775   1.0000   0.0379
 -14.000  -0.6725   0.07186   0.06617  -0.0768   1.0000   0.0383
 -13.750  -0.6702   0.07018   0.06451  -0.0762   1.0000   0.0385
 -13.500  -0.6690   0.06855   0.06290  -0.0755   1.0000   0.0388
 -13.250  -0.6694   0.06684   0.06119  -0.0747   1.0000   0.0390
 -13.000  -0.6719   0.06508   0.05944  -0.0737   1.0000   0.0392
 -12.750  -0.6758   0.06343   0.05780  -0.0725   1.0000   0.0394
 -12.500  -0.6821   0.06178   0.05616  -0.0710   1.0000   0.0396
 -12.250  -0.6694   0.05966   0.05402  -0.0732   0.9977   0.0399
 -12.000  -0.6524   0.05733   0.05166  -0.0766   0.9939   0.0403
 -11.750  -0.6382   0.05506   0.04936  -0.0795   0.9897   0.0408
 -11.500  -0.6247   0.05273   0.04699  -0.0825   0.9848   0.0412
 -11.250  -0.6082   0.05032   0.04454  -0.0863   0.9807   0.0416
 -11.000  -0.6007   0.04785   0.04202  -0.0888   0.9727   0.0421
 -10.750  -0.5869   0.04511   0.03922  -0.0931   0.9673   0.0425
 -10.500  -0.5854   0.04201   0.03612  -0.0962   0.9568   0.0430
 -10.250  -0.5731   0.03825   0.03231  -0.1022   0.9493   0.0436
 -10.000  -0.5574   0.03425   0.02820  -0.1088   0.9414   0.0443
  -9.750  -0.5283   0.03017   0.02397  -0.1171   0.9378   0.0452
  -9.500  -0.5107   0.02701   0.02064  -0.1210   0.9293   0.0461
  -9.250  -0.4808   0.02496   0.01844  -0.1247   0.9253   0.0473
  -9.000  -0.4477   0.02326   0.01663  -0.1283   0.9225   0.0489
  -8.750  -0.4181   0.02192   0.01522  -0.1306   0.9186   0.0515
  -8.500  -0.3949   0.02088   0.01413  -0.1311   0.9117   0.0552
  -8.250  -0.3630   0.01980   0.01304  -0.1330   0.9077   0.0645
  -8.000  -0.3282   0.01886   0.01205  -0.1352   0.9046   0.0779
  -7.750  -0.3023   0.01810   0.01126  -0.1355   0.8982   0.0892
  -7.500  -0.2736   0.01731   0.01045  -0.1363   0.8919   0.1026
  -7.250  -0.2395   0.01648   0.00963  -0.1381   0.8874   0.1194
  -7.000  -0.2105   0.01585   0.00903  -0.1387   0.8804   0.1387
  -6.750  -0.1809   0.01539   0.00857  -0.1391   0.8723   0.1551
  -6.500  -0.1436   0.01499   0.00819  -0.1408   0.8665   0.1735
  -6.250  -0.1187   0.01485   0.00807  -0.1401   0.8558   0.1882
  -6.000  -0.0835   0.01470   0.00787  -0.1412   0.8486   0.2006
  -5.750  -0.0565   0.01461   0.00770  -0.1408   0.8381   0.2110
  -5.500  -0.0227   0.01456   0.00757  -0.1415   0.8294   0.2211
  -5.250   0.0044   0.01457   0.00753  -0.1411   0.8177   0.2282
  -5.000   0.0355   0.01454   0.00738  -0.1413   0.8067   0.2345
  -4.750   0.0644   0.01443   0.00712  -0.1412   0.7938   0.2401
  -4.500   0.0926   0.01449   0.00716  -0.1408   0.7796   0.2441
  -4.250   0.1213   0.01454   0.00710  -0.1406   0.7643   0.2494
  -4.000   0.1499   0.01454   0.00692  -0.1404   0.7475   0.2557
  -3.750   0.1779   0.01472   0.00709  -0.1400   0.7289   0.2601
  -3.500   0.2057   0.01485   0.00711  -0.1396   0.7096   0.2652
  -3.250   0.2333   0.01489   0.00692  -0.1392   0.6909   0.2702
  -3.000   0.2602   0.01491   0.00682  -0.1387   0.6739   0.2733
  -2.750   0.2869   0.01499   0.00681  -0.1381   0.6588   0.2760
  -2.500   0.3136   0.01504   0.00675  -0.1376   0.6455   0.2786
  -2.250   0.3403   0.01507   0.00668  -0.1372   0.6337   0.2815
  -2.000   0.3670   0.01509   0.00654  -0.1367   0.6227   0.2842
  -1.750   0.3938   0.01507   0.00640  -0.1363   0.6121   0.2866
  -1.500   0.4208   0.01510   0.00626  -0.1360   0.6029   0.2885
  -1.250   0.4472   0.01504   0.00619  -0.1355   0.5936   0.2904
  -1.000   0.4738   0.01507   0.00617  -0.1351   0.5849   0.2923
  -0.750   0.5002   0.01506   0.00615  -0.1346   0.5756   0.2941
  -0.500   0.5265   0.01509   0.00611  -0.1341   0.5666   0.2959
  -0.250   0.5529   0.01510   0.00609  -0.1336   0.5580   0.2979
   0.000   0.5791   0.01513   0.00607  -0.1331   0.5494   0.3003
   0.250   0.6054   0.01517   0.00605  -0.1326   0.5414   0.3027
   0.500   0.6314   0.01520   0.00602  -0.1321   0.5323   0.3047
   0.750   0.6571   0.01526   0.00599  -0.1315   0.5235   0.3063
   1.000   0.6824   0.01525   0.00598  -0.1308   0.5133   0.3080
   1.250   0.7074   0.01528   0.00599  -0.1301   0.5040   0.3097
   1.500   0.7324   0.01533   0.00604  -0.1294   0.4942   0.3117
   1.750   0.7572   0.01542   0.00609  -0.1286   0.4853   0.3140
   2.000   0.7821   0.01550   0.00616  -0.1279   0.4762   0.3164
   2.250   0.8068   0.01560   0.00622  -0.1272   0.4684   0.3186
   2.500   0.8318   0.01569   0.00631  -0.1265   0.4602   0.3207
   2.750   0.8560   0.01583   0.00638  -0.1256   0.4527   0.3228
   3.000   0.8809   0.01594   0.00648  -0.1249   0.4451   0.3248
   3.250   0.9052   0.01605   0.00660  -0.1241   0.4382   0.3269
   3.500   0.9292   0.01618   0.00674  -0.1233   0.4316   0.3291
   3.750   0.9534   0.01630   0.00690  -0.1225   0.4243   0.3319
   4.000   0.9767   0.01648   0.00706  -0.1215   0.4176   0.3348
   4.250   1.0008   0.01664   0.00724  -0.1207   0.4116   0.3380
   4.500   1.0246   0.01680   0.00743  -0.1199   0.4053   0.3409
   4.750   1.0475   0.01700   0.00761  -0.1189   0.3993   0.3437
   5.000   1.0705   0.01716   0.00782  -0.1179   0.3928   0.3466
   5.250   1.0919   0.01733   0.00803  -0.1167   0.3843   0.3497
   5.500   1.1126   0.01755   0.00826  -0.1153   0.3763   0.3531
   5.750   1.1336   0.01773   0.00850  -0.1140   0.3681   0.3570
   6.000   1.1527   0.01798   0.00872  -0.1123   0.3612   0.3610
   6.250   1.1735   0.01816   0.00899  -0.1110   0.3545   0.3656
   6.500   1.1923   0.01838   0.00927  -0.1093   0.3474   0.3708
   6.750   1.2103   0.01865   0.00957  -0.1076   0.3403   0.3771
   7.250   1.2450   0.01925   0.01025  -0.1039   0.3228   0.3911
   7.500   1.2628   0.01955   0.01063  -0.1022   0.3137   0.4004
   7.750   1.2788   0.01992   0.01104  -0.1003   0.3061   0.4116
   8.000   1.2967   0.02025   0.01148  -0.0987   0.2973   0.4277
   8.250   1.3121   0.02068   0.01196  -0.0968   0.2887   0.4502
   8.500   1.3288   0.02107   0.01248  -0.0951   0.2785   0.4874
   8.750   1.3436   0.02149   0.01308  -0.0933   0.2671   0.5603
   9.250   1.3678   0.02228   0.01438  -0.0890   0.2399   1.0000
   9.750   1.3861   0.02408   0.01607  -0.0844   0.2125   1.0000
  10.000   1.3943   0.02511   0.01706  -0.0822   0.2010   1.0000
  10.250   1.4014   0.02623   0.01815  -0.0800   0.1917   1.0000
  10.500   1.4080   0.02745   0.01933  -0.0778   0.1836   1.0000
  10.750   1.4149   0.02870   0.02058  -0.0758   0.1772   1.0000
  11.000   1.4219   0.03000   0.02189  -0.0740   0.1714   1.0000
  11.250   1.4267   0.03150   0.02340  -0.0721   0.1665   1.0000
  11.500   1.4346   0.03284   0.02479  -0.0706   0.1622   1.0000
  11.750   1.4413   0.03433   0.02632  -0.0691   0.1575   1.0000
  12.000   1.4443   0.03616   0.02816  -0.0675   0.1529   1.0000
  12.250   1.4495   0.03788   0.02995  -0.0663   0.1489   1.0000
  12.500   1.4568   0.03951   0.03165  -0.0652   0.1444   1.0000
  12.750   1.4597   0.04158   0.03377  -0.0641   0.1394   1.0000
  13.000   1.4622   0.04378   0.03602  -0.0632   0.1351   1.0000
  13.250   1.4687   0.04568   0.03801  -0.0625   0.1291   1.0000
  13.500   1.4693   0.04826   0.04063  -0.0619   0.1232   1.0000
  13.750   1.4730   0.05060   0.04305  -0.0614   0.1152   1.0000
  14.000   1.4720   0.05353   0.04601  -0.0611   0.1059   1.0000
  14.250   1.4673   0.05698   0.04946  -0.0610   0.0959   1.0000
  14.500   1.4612   0.06071   0.05318  -0.0611   0.0889   1.0000
  14.750   1.4552   0.06452   0.05701  -0.0613   0.0841   1.0000
  15.000   1.4495   0.06840   0.06093  -0.0617   0.0810   1.0000
  15.250   1.4448   0.07225   0.06484  -0.0621   0.0787   1.0000
  15.500   1.4415   0.07598   0.06865  -0.0627   0.0771   1.0000
  15.750   1.4375   0.07988   0.07263  -0.0634   0.0756   1.0000
  16.000   1.4330   0.08394   0.07676  -0.0642   0.0743   1.0000
  16.250   1.4280   0.08815   0.08105  -0.0652   0.0731   1.0000
  16.500   1.4230   0.09242   0.08539  -0.0663   0.0721   1.0000
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