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GOE 376 AIRFOIL (goe376-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 376 AIRFOIL (goe376-il)
Reynolds number: 100,000
Max Cl/Cd: 56.41 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe376-il-100000.txt
Download as CSV file: xf-goe376-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 376 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3108   0.09694   0.09214  -0.0219   1.0000   0.0447
  -7.500  -0.3123   0.09508   0.09036  -0.0218   1.0000   0.0456
  -7.250  -0.3156   0.09379   0.08917  -0.0226   1.0000   0.0467
  -7.000  -0.3149   0.09350   0.08895  -0.0279   1.0000   0.0475
  -6.750  -0.3078   0.09260   0.08806  -0.0331   1.0000   0.0479
  -6.500  -0.3078   0.08660   0.08218  -0.0284   1.0000   0.0487
  -6.250  -0.3055   0.08282   0.07847  -0.0247   1.0000   0.0499
  -6.000  -0.3030   0.08016   0.07587  -0.0234   1.0000   0.0513
  -5.750  -0.3007   0.07780   0.07355  -0.0229   1.0000   0.0529
  -5.500  -0.2979   0.07558   0.07137  -0.0229   1.0000   0.0546
  -5.250  -0.2931   0.07344   0.06924  -0.0236   1.0000   0.0568
  -5.000  -0.2687   0.07342   0.06902  -0.0317   1.0000   0.0600
  -4.750  -0.2632   0.06996   0.06556  -0.0318   1.0000   0.0608
  -4.500  -0.2690   0.06618   0.06194  -0.0274   1.0000   0.0622
  -4.250  -0.2665   0.06377   0.05956  -0.0256   1.0000   0.0646
  -4.000  -0.2569   0.06160   0.05736  -0.0258   1.0000   0.0684
  -3.750  -0.2058   0.05890   0.05429  -0.0360   0.9958   0.0748
  -3.500  -0.1808   0.05428   0.04977  -0.0381   0.9889   0.0788
  -3.250  -0.1228   0.05132   0.04639  -0.0475   0.9807   0.0893
  -2.750  -0.0511   0.04437   0.03931  -0.0554   0.9640   0.1094
  -2.500  -0.0064   0.04142   0.03617  -0.0606   0.9567   0.1238
  -2.250   0.0380   0.03951   0.03388  -0.0652   0.9466   0.1472
  -2.000   0.0702   0.03646   0.03086  -0.0676   0.9371   0.1655
  -1.750   0.1121   0.03398   0.02828  -0.0716   0.9302   0.2087
  -1.250   0.2038   0.01097   0.00599  -0.0761   0.8877   0.3941
  -1.000   0.2312   0.00913   0.00417  -0.0758   0.8760   0.4497
  -0.750   0.2704   0.00772   0.00259  -0.0778   0.8653   0.4744
  -0.500   0.3288   0.00687   0.00117  -0.0837   0.8562   0.4115
  -0.250   0.3964   0.00742   0.00018  -0.0874   0.8441   0.1732
   0.000   0.4269   0.02204   0.01406  -0.0886   0.8598   0.1438
   0.250   0.4664   0.02110   0.01267  -0.0888   0.8458   0.1175
   0.500   0.5015   0.01981   0.01131  -0.0891   0.8303   0.1090
   0.750   0.5358   0.01919   0.01042  -0.0888   0.8132   0.1017
   1.000   0.5667   0.01825   0.00943  -0.0882   0.7943   0.0990
   1.250   0.5942   0.01769   0.00879  -0.0872   0.7724   0.0998
   1.500   0.6231   0.01722   0.00820  -0.0863   0.7525   0.1021
   1.750   0.6497   0.01686   0.00776  -0.0853   0.7313   0.1026
   2.000   0.6769   0.01660   0.00737  -0.0845   0.7110   0.1045
   2.250   0.7044   0.01649   0.00712  -0.0837   0.6920   0.1090
   2.500   0.7300   0.01652   0.00702  -0.0828   0.6721   0.1167
   2.750   0.7560   0.01643   0.00702  -0.0820   0.6530   0.1594
   3.000   0.8076   0.01509   0.00692  -0.0868   0.6323   1.0000
   3.250   0.8319   0.01536   0.00700  -0.0856   0.6146   1.0000
   3.500   0.8554   0.01564   0.00715  -0.0845   0.5963   1.0000
   3.750   0.8791   0.01592   0.00731  -0.0834   0.5784   1.0000
   4.000   0.9029   0.01622   0.00748  -0.0823   0.5609   1.0000
   4.250   0.9268   0.01653   0.00768  -0.0812   0.5433   1.0000
   4.500   0.9502   0.01687   0.00791  -0.0801   0.5254   1.0000
   4.750   0.9727   0.01725   0.00823  -0.0789   0.5062   1.0000
   5.000   0.9956   0.01765   0.00855  -0.0778   0.4874   1.0000
   5.250   1.0188   0.01810   0.00892  -0.0767   0.4691   1.0000
   5.500   1.0416   0.01862   0.00935  -0.0756   0.4511   1.0000
   5.750   1.0636   0.01915   0.00988  -0.0745   0.4326   1.0000
   6.000   1.0860   0.01973   0.01045  -0.0734   0.4154   1.0000
   6.250   1.1084   0.02033   0.01107  -0.0723   0.3991   1.0000
   6.500   1.1306   0.02092   0.01168  -0.0713   0.3835   1.0000
   6.750   1.1526   0.02152   0.01230  -0.0702   0.3688   1.0000
   7.000   1.1747   0.02215   0.01298  -0.0692   0.3551   1.0000
   7.250   1.1961   0.02269   0.01360  -0.0680   0.3411   1.0000
   7.500   1.2154   0.02300   0.01394  -0.0664   0.3245   1.0000
   7.750   1.2345   0.02334   0.01432  -0.0649   0.3088   1.0000
   8.000   1.2540   0.02381   0.01486  -0.0635   0.2949   1.0000
   8.250   1.2713   0.02413   0.01522  -0.0617   0.2787   1.0000
   8.500   1.2881   0.02453   0.01569  -0.0599   0.2631   1.0000
   8.750   1.3052   0.02504   0.01633  -0.0583   0.2492   1.0000
   9.000   1.3200   0.02549   0.01687  -0.0563   0.2336   1.0000
   9.250   1.3321   0.02591   0.01741  -0.0539   0.2151   1.0000
   9.500   1.3413   0.02633   0.01797  -0.0512   0.1896   1.0000
   9.750   1.3502   0.02704   0.01879  -0.0485   0.1491   1.0000
  10.000   1.3459   0.02925   0.02048  -0.0445   0.0818   1.0000
  10.250   1.3392   0.03155   0.02253  -0.0402   0.0635   1.0000
  10.500   1.3340   0.03364   0.02462  -0.0362   0.0575   1.0000
  10.750   1.3306   0.03567   0.02679  -0.0329   0.0535   1.0000
  11.000   1.3231   0.03813   0.02933  -0.0299   0.0503   1.0000
  11.250   1.3146   0.04086   0.03212  -0.0274   0.0485   1.0000
  11.500   1.3136   0.04321   0.03468  -0.0257   0.0459   1.0000
  11.750   1.3114   0.04581   0.03742  -0.0243   0.0443   1.0000
  12.000   1.3095   0.04855   0.04028  -0.0231   0.0429   1.0000
  12.250   1.3091   0.05130   0.04312  -0.0221   0.0418   1.0000
  12.500   1.3112   0.05397   0.04587  -0.0209   0.0406   1.0000
  12.750   1.3191   0.05639   0.04831  -0.0194   0.0396   1.0000
  13.000   1.3404   0.05894   0.05087  -0.0172   0.0385   1.0000
  13.250   1.3488   0.06191   0.05407  -0.0161   0.0382   1.0000
  13.500   1.3486   0.06536   0.05779  -0.0155   0.0379   1.0000
  13.750   1.3433   0.06917   0.06188  -0.0153   0.0376   1.0000
  14.000   1.3366   0.07332   0.06630  -0.0155   0.0374   1.0000
  14.250   1.3253   0.07792   0.07116  -0.0163   0.0372   1.0000
  14.500   1.3115   0.08301   0.07651  -0.0177   0.0371   1.0000
  14.750   1.2959   0.08857   0.08231  -0.0197   0.0371   1.0000
  15.000   1.2792   0.09459   0.08856  -0.0222   0.0372   1.0000
  15.250   1.2607   0.10122   0.09541  -0.0254   0.0374   1.0000
  15.500   1.2418   0.10828   0.10266  -0.0292   0.0377   1.0000
  15.750   1.2225   0.11590   0.11045  -0.0334   0.0380   1.0000
  16.000   1.2020   0.12415   0.11887  -0.0384   0.0382   1.0000
  16.250   1.1840   0.13243   0.12731  -0.0435   0.0387   1.0000
  16.500   1.0657   0.17400   0.16907  -0.0726   0.0464   1.0000
  16.750   1.0610   0.18149   0.17652  -0.0760   0.0475   1.0000
  17.000   1.0619   0.18702   0.18204  -0.0781   0.0484   1.0000
  17.250   1.0357   0.20756   0.20240  -0.0897   0.0632   1.0000
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