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GOE 400 AIRFOIL (goe400-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 400 AIRFOIL (goe400-il)
Reynolds number: 100,000
Max Cl/Cd: 61.36 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe400-il-100000-n5.txt
Download as CSV file: xf-goe400-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 400 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3982   0.11302   0.10815  -0.0044   1.0000   0.0478
  -8.500  -0.3968   0.11120   0.10640  -0.0081   1.0000   0.0481
  -8.250  -0.3936   0.10885   0.10410  -0.0119   1.0000   0.0483
  -8.000  -0.3800   0.10229   0.09756  -0.0093   1.0000   0.0491
  -7.750  -0.3686   0.09827   0.09355  -0.0086   1.0000   0.0503
  -7.500  -0.3602   0.09518   0.09049  -0.0093   1.0000   0.0516
  -7.250  -0.3523   0.09227   0.08762  -0.0107   1.0000   0.0531
  -7.000  -0.3423   0.08942   0.08481  -0.0134   1.0000   0.0568
  -6.750  -0.3252   0.08729   0.08270  -0.0259   1.0000   0.0600
  -6.500  -0.3089   0.08340   0.07883  -0.0315   1.0000   0.0604
  -6.250  -0.3030   0.07918   0.07467  -0.0273   1.0000   0.0613
  -6.000  -0.2916   0.07599   0.07148  -0.0272   1.0000   0.0625
  -5.750  -0.2784   0.07299   0.06851  -0.0288   1.0000   0.0640
  -5.500  -0.2559   0.07052   0.06602  -0.0360   1.0000   0.0709
  -5.000  -0.1950   0.05995   0.05521  -0.0500   0.9854   0.0599
  -4.750  -0.1712   0.05624   0.05151  -0.0512   0.9710   0.0565
  -4.500  -0.1277   0.05156   0.04663  -0.0595   0.9545   0.0579
  -4.250  -0.0886   0.04732   0.04218  -0.0656   0.9378   0.0567
  -4.000  -0.0492   0.04308   0.03771  -0.0712   0.9206   0.0550
  -3.750  -0.0108   0.03903   0.03337  -0.0761   0.9029   0.0541
  -3.500   0.0245   0.03570   0.02973  -0.0794   0.8842   0.0554
  -3.250   0.0589   0.03238   0.02604  -0.0822   0.8664   0.0571
  -3.000   0.0911   0.02919   0.02243  -0.0840   0.8495   0.0567
  -2.750   0.1223   0.02620   0.01897  -0.0852   0.8335   0.0567
  -2.500   0.1528   0.02337   0.01560  -0.0860   0.8185   0.0572
  -2.250   0.1825   0.02089   0.01253  -0.0863   0.8042   0.0584
  -2.000   0.2113   0.01901   0.01007  -0.0863   0.7905   0.0600
  -1.750   0.2381   0.01878   0.00979  -0.0859   0.7767   0.0628
  -1.500   0.2652   0.01847   0.00933  -0.0855   0.7638   0.0669
  -1.250   0.2932   0.01752   0.00806  -0.0851   0.7521   0.0705
  -1.000   0.3205   0.01706   0.00748  -0.0847   0.7402   0.0737
  -0.750   0.3478   0.01671   0.00702  -0.0843   0.7283   0.0796
  -0.500   0.3751   0.01639   0.00658  -0.0838   0.7171   0.0890
  -0.250   0.4023   0.01617   0.00619  -0.0833   0.7066   0.1034
   0.000   0.4294   0.01610   0.00603  -0.0829   0.6956   0.1189
   0.250   0.4564   0.01608   0.00596  -0.0827   0.6846   0.1350
   0.500   0.4829   0.01606   0.00597  -0.0823   0.6744   0.1531
   0.750   0.5096   0.01596   0.00584  -0.0819   0.6643   0.1629
   1.000   0.5362   0.01584   0.00567  -0.0814   0.6536   0.1667
   1.250   0.5632   0.01575   0.00557  -0.0810   0.6439   0.1722
   1.500   0.5902   0.01571   0.00548  -0.0805   0.6339   0.1770
   1.750   0.6172   0.01570   0.00544  -0.0802   0.6232   0.1808
   2.000   0.6441   0.01568   0.00543  -0.0798   0.6134   0.1853
   2.250   0.6709   0.01571   0.00544  -0.0793   0.6034   0.1917
   2.500   0.6978   0.01574   0.00553  -0.0790   0.5925   0.2003
   2.750   0.7246   0.01577   0.00562  -0.0786   0.5821   0.2161
   3.000   0.7512   0.01569   0.00573  -0.0783   0.5723   0.2763
   3.500   0.8049   0.01478   0.00600  -0.0775   0.5494   1.0000
   3.750   0.8311   0.01499   0.00614  -0.0770   0.5372   1.0000
   4.000   0.8571   0.01519   0.00629  -0.0765   0.5237   1.0000
   4.250   0.8830   0.01539   0.00648  -0.0759   0.5092   1.0000
   4.500   0.9087   0.01560   0.00667  -0.0753   0.4940   1.0000
   4.750   0.9344   0.01584   0.00690  -0.0748   0.4789   1.0000
   5.000   0.9599   0.01609   0.00718  -0.0742   0.4644   1.0000
   5.250   0.9853   0.01637   0.00747  -0.0737   0.4491   1.0000
   5.500   1.0105   0.01665   0.00778  -0.0731   0.4326   1.0000
   5.750   1.0355   0.01697   0.00813  -0.0725   0.4159   1.0000
   6.000   1.0603   0.01731   0.00854  -0.0720   0.4001   1.0000
   6.250   1.0848   0.01768   0.00895  -0.0713   0.3830   1.0000
   6.500   1.1090   0.01808   0.00939  -0.0707   0.3654   1.0000
   6.750   1.1331   0.01852   0.00989  -0.0700   0.3492   1.0000
   7.000   1.1569   0.01898   0.01048  -0.0694   0.3319   1.0000
   7.250   1.1803   0.01949   0.01108  -0.0687   0.3123   1.0000
   7.500   1.2021   0.02010   0.01170  -0.0679   0.2838   1.0000
   7.750   1.2213   0.02095   0.01239  -0.0669   0.2385   1.0000
   8.000   1.2379   0.02216   0.01330  -0.0658   0.1855   1.0000
   8.250   1.2541   0.02351   0.01446  -0.0647   0.1423   1.0000
   8.750   1.2822   0.02666   0.01724  -0.0622   0.0818   1.0000
   9.000   1.2966   0.02815   0.01877  -0.0608   0.0553   1.0000
   9.250   1.3074   0.02992   0.02040  -0.0592   0.0402   1.0000
   9.500   1.3159   0.03180   0.02226  -0.0574   0.0343   1.0000
   9.750   1.3242   0.03354   0.02423  -0.0556   0.0314   1.0000
  10.000   1.3291   0.03544   0.02627  -0.0535   0.0294   1.0000
  10.250   1.3282   0.03762   0.02856  -0.0512   0.0278   1.0000
  10.500   1.3280   0.03990   0.03097  -0.0494   0.0265   1.0000
  10.750   1.3297   0.04216   0.03343  -0.0480   0.0252   1.0000
  11.000   1.3305   0.04467   0.03611  -0.0469   0.0240   1.0000
  11.250   1.3307   0.04739   0.03898  -0.0461   0.0232   1.0000
  11.500   1.3307   0.05025   0.04198  -0.0454   0.0225   1.0000
  11.750   1.3307   0.05319   0.04505  -0.0449   0.0219   1.0000
  12.000   1.3306   0.05622   0.04820  -0.0443   0.0213   1.0000
  12.250   1.3302   0.05936   0.05145  -0.0438   0.0208   1.0000
  12.500   1.3292   0.06265   0.05485  -0.0433   0.0202   1.0000
  12.750   1.3280   0.06614   0.05845  -0.0425   0.0196   1.0000
  13.000   1.3258   0.06976   0.06236  -0.0428   0.0192   1.0000
  13.250   1.3219   0.07372   0.06657  -0.0433   0.0188   1.0000
  13.500   1.3161   0.07801   0.07110  -0.0441   0.0184   1.0000
  13.750   1.3085   0.08268   0.07600  -0.0453   0.0181   1.0000
  14.000   1.2991   0.08776   0.08131  -0.0468   0.0179   1.0000
  14.250   1.2880   0.09325   0.08703  -0.0487   0.0178   1.0000
  14.500   1.2752   0.09927   0.09327  -0.0512   0.0177   1.0000
  14.750   1.2612   0.10584   0.10007  -0.0544   0.0177   1.0000
  15.000   1.2460   0.11301   0.10744  -0.0581   0.0177   1.0000
  15.250   1.2297   0.12084   0.11548  -0.0625   0.0178   1.0000
  15.500   1.2122   0.12949   0.12432  -0.0677   0.0179   1.0000
  15.750   1.1937   0.13899   0.13400  -0.0737   0.0180   1.0000
  16.000   1.1738   0.14962   0.14479  -0.0804   0.0183   1.0000
  16.250   1.1532   0.16148   0.15672  -0.0879   0.0186   1.0000
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