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

GOE 679 AIRFOIL (goe679-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 679 AIRFOIL (goe679-il)
Reynolds number: 100,000
Max Cl/Cd: 41.6 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe679-il-100000-n5.txt
Download as CSV file: xf-goe679-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 679 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
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.6505   0.06614   0.05975  -0.0762   1.0000   0.0586
 -12.000  -0.7033   0.05869   0.05210  -0.0793   1.0000   0.0584
 -11.750  -0.7313   0.05310   0.04623  -0.0832   0.9957   0.0584
 -11.500  -0.7438   0.04896   0.04173  -0.0860   0.9870   0.0588
 -11.250  -0.7308   0.04717   0.03990  -0.0872   0.9812   0.0594
 -11.000  -0.7232   0.04554   0.03820  -0.0868   0.9731   0.0600
 -10.750  -0.7082   0.04373   0.03625  -0.0877   0.9674   0.0607
 -10.500  -0.6985   0.04203   0.03443  -0.0870   0.9588   0.0614
 -10.250  -0.6828   0.04031   0.03254  -0.0871   0.9523   0.0623
 -10.000  -0.6694   0.03873   0.03079  -0.0864   0.9442   0.0633
  -9.750  -0.6528   0.03715   0.02897  -0.0860   0.9378   0.0645
  -9.500  -0.6366   0.03602   0.02781  -0.0851   0.9299   0.0656
  -9.250  -0.6101   0.03489   0.02665  -0.0860   0.9256   0.0673
  -9.000  -0.5997   0.03395   0.02563  -0.0837   0.9156   0.0688
  -8.750  -0.5736   0.03272   0.02421  -0.0842   0.9110   0.0710
  -8.500  -0.5605   0.03193   0.02342  -0.0822   0.9017   0.0727
  -8.250  -0.5347   0.03095   0.02240  -0.0824   0.8963   0.0753
  -8.000  -0.5154   0.03004   0.02135  -0.0812   0.8885   0.0781
  -7.750  -0.4919   0.02920   0.02052  -0.0808   0.8814   0.0811
  -7.500  -0.4596   0.02816   0.01939  -0.0818   0.8774   0.0862
  -7.250  -0.4447   0.02760   0.01883  -0.0796   0.8666   0.0905
  -7.000  -0.4132   0.02674   0.01794  -0.0803   0.8617   0.0976
  -6.750  -0.3914   0.02615   0.01731  -0.0792   0.8534   0.1052
  -6.500  -0.3639   0.02552   0.01661  -0.0791   0.8467   0.1140
  -6.250  -0.3288   0.02487   0.01588  -0.0802   0.8427   0.1245
  -6.000  -0.3088   0.02460   0.01560  -0.0787   0.8335   0.1321
  -5.750  -0.2780   0.02415   0.01509  -0.0791   0.8275   0.1411
  -5.500  -0.2400   0.02361   0.01445  -0.0807   0.8235   0.1514
  -5.250  -0.2201   0.02344   0.01423  -0.0791   0.8138   0.1590
  -5.000  -0.1869   0.02306   0.01380  -0.0799   0.8077   0.1683
  -4.750  -0.1455   0.02261   0.01325  -0.0821   0.8034   0.1801
  -4.500  -0.1282   0.02255   0.01322  -0.0800   0.7925   0.1880
  -4.250  -0.0906   0.02214   0.01273  -0.0816   0.7863   0.1979
  -4.000  -0.0587   0.02182   0.01237  -0.0821   0.7785   0.2056
  -3.750  -0.0307   0.02151   0.01194  -0.0818   0.7689   0.2126
  -3.500   0.0149   0.02101   0.01145  -0.0850   0.7627   0.2203
  -3.250   0.0315   0.02087   0.01126  -0.0826   0.7507   0.2264
  -3.000   0.0742   0.02044   0.01077  -0.0851   0.7430   0.2344
  -2.750   0.0930   0.02029   0.01062  -0.0832   0.7309   0.2408
  -2.500   0.1335   0.01996   0.01017  -0.0853   0.7221   0.2504
  -2.250   0.1508   0.01981   0.01007  -0.0830   0.7093   0.2570
  -2.000   0.1863   0.01956   0.00972  -0.0842   0.6993   0.2675
  -1.750   0.2055   0.01941   0.00961  -0.0823   0.6864   0.2756
  -1.500   0.2316   0.01925   0.00941  -0.0817   0.6745   0.2864
  -1.250   0.2590   0.01905   0.00921  -0.0813   0.6625   0.2974
  -1.000   0.2785   0.01898   0.00910  -0.0794   0.6491   0.3094
  -0.750   0.3043   0.01881   0.00895  -0.0788   0.6370   0.3226
  -0.500   0.3275   0.01871   0.00882  -0.0776   0.6242   0.3375
  -0.250   0.3480   0.01863   0.00876  -0.0760   0.6113   0.3541
   0.000   0.3735   0.01852   0.00864  -0.0753   0.5995   0.3743
   0.250   0.3945   0.01844   0.00861  -0.0737   0.5870   0.3969
   0.500   0.4170   0.01836   0.00859  -0.0725   0.5755   0.4267
   0.750   0.4424   0.01824   0.00855  -0.0719   0.5645   0.4694
   1.000   0.4627   0.01812   0.00864  -0.0703   0.5533   0.5298
   1.250   0.4887   0.01788   0.00872  -0.0695   0.5438   0.6372
   1.500   0.5478   0.01788   0.00925  -0.0750   0.5305   0.8259
   1.750   0.6402   0.01840   0.00970  -0.0875   0.5161   0.9315
   2.000   0.6937   0.01880   0.00988  -0.0924   0.5049   0.9693
   2.250   0.7427   0.01922   0.01019  -0.0968   0.4933   0.9968
   2.500   0.7683   0.01947   0.01024  -0.0966   0.4851   1.0000
   2.750   0.7796   0.01967   0.01040  -0.0935   0.4770   1.0000
   3.000   0.7942   0.01989   0.01050  -0.0910   0.4693   1.0000
   3.250   0.8113   0.02013   0.01061  -0.0890   0.4626   1.0000
   3.500   0.8229   0.02037   0.01081  -0.0860   0.4549   1.0000
   3.750   0.8388   0.02061   0.01094  -0.0837   0.4482   1.0000
   4.000   0.8542   0.02087   0.01111  -0.0813   0.4417   1.0000
   4.250   0.8655   0.02113   0.01135  -0.0783   0.4347   1.0000
   4.500   0.8817   0.02140   0.01152  -0.0761   0.4284   1.0000
   4.750   0.8972   0.02170   0.01174  -0.0738   0.4222   1.0000
   5.000   0.9091   0.02200   0.01204  -0.0709   0.4155   1.0000
   5.250   0.9249   0.02230   0.01227  -0.0687   0.4093   1.0000
   5.500   0.9413   0.02263   0.01252  -0.0667   0.4034   1.0000
   5.750   0.9526   0.02299   0.01290  -0.0637   0.3967   1.0000
   6.000   0.9675   0.02333   0.01318  -0.0615   0.3906   1.0000
   6.250   0.9848   0.02369   0.01346  -0.0597   0.3851   1.0000
   6.500   0.9956   0.02411   0.01394  -0.0569   0.3785   1.0000
   6.750   1.0092   0.02450   0.01429  -0.0545   0.3724   1.0000
   7.000   1.0269   0.02489   0.01459  -0.0529   0.3670   1.0000
   7.250   1.0365   0.02540   0.01517  -0.0500   0.3604   1.0000
   7.500   1.0497   0.02586   0.01562  -0.0478   0.3545   1.0000
   7.750   1.0675   0.02627   0.01593  -0.0463   0.3496   1.0000
   8.000   1.0769   0.02688   0.01663  -0.0436   0.3435   1.0000
   8.250   1.0890   0.02743   0.01720  -0.0414   0.3377   1.0000
   8.500   1.1041   0.02792   0.01761  -0.0396   0.3327   1.0000
   8.750   1.1148   0.02859   0.01833  -0.0374   0.3271   1.0000
   9.000   1.1250   0.02927   0.01906  -0.0351   0.3213   1.0000
   9.250   1.1384   0.02987   0.01963  -0.0333   0.3165   1.0000
   9.500   1.1524   0.03053   0.02026  -0.0317   0.3120   1.0000
   9.750   1.1610   0.03140   0.02123  -0.0295   0.3068   1.0000
  10.000   1.1718   0.03219   0.02204  -0.0276   0.3020   1.0000
  10.250   1.1868   0.03283   0.02264  -0.0262   0.2981   1.0000
  10.500   1.1966   0.03377   0.02361  -0.0244   0.2936   1.0000
  10.750   1.2034   0.03484   0.02479  -0.0224   0.2889   1.0000
  11.000   1.2132   0.03578   0.02575  -0.0207   0.2845   1.0000
  11.250   1.2285   0.03649   0.02640  -0.0196   0.2810   1.0000
  11.500   1.2365   0.03766   0.02764  -0.0180   0.2772   1.0000
  11.750   1.2414   0.03905   0.02914  -0.0162   0.2732   1.0000
  12.000   1.2493   0.04026   0.03042  -0.0147   0.2696   1.0000
  12.250   1.2611   0.04125   0.03141  -0.0136   0.2663   1.0000
  12.500   1.2799   0.04186   0.03193  -0.0129   0.2633   1.0000
  12.750   1.2747   0.04402   0.03428  -0.0109   0.2595   1.0000
  13.000   1.2747   0.04591   0.03631  -0.0094   0.2558   1.0000
  13.250   1.2801   0.04744   0.03788  -0.0082   0.2522   1.0000
  13.500   1.2925   0.04846   0.03888  -0.0074   0.2491   1.0000
  13.750   1.3032   0.04969   0.04012  -0.0066   0.2461   1.0000
  14.000   1.2880   0.05303   0.04368  -0.0051   0.2423   1.0000
  14.250   1.2811   0.05582   0.04661  -0.0041   0.2385   1.0000
  14.500   1.2855   0.05762   0.04844  -0.0034   0.2350   1.0000
  14.750   1.3047   0.05804   0.04879  -0.0029   0.2319   1.0000
  15.000   1.2858   0.06228   0.05323  -0.0023   0.2285   1.0000
  15.250   1.2534   0.06829   0.05948  -0.0023   0.2243   1.0000
  15.500   1.2441   0.07198   0.06327  -0.0023   0.2206   1.0000
  15.750   1.2606   0.07262   0.06389  -0.0019   0.2177   1.0000
  16.000   1.2829   0.07265   0.06385  -0.0014   0.2154   1.0000
<< Back to GOE 679 AIRFOIL (goe679-il)

Polar data table (+)

Polar graphs


<< Back to GOE 679 AIRFOIL (goe679-il)