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GOE 385 AIRFOIL (goe385-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 385 AIRFOIL (goe385-il)
Reynolds number: 100,000
Max Cl/Cd: 56.17 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe385-il-100000-n5.txt
Download as CSV file: xf-goe385-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 385 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3431   0.09655   0.09194  -0.0315   1.0000   0.0465
  -8.000  -0.3472   0.09387   0.08936  -0.0350   1.0000   0.0469
  -7.750  -0.3472   0.09067   0.08621  -0.0390   1.0000   0.0471
  -7.500  -0.3473   0.08753   0.08310  -0.0414   1.0000   0.0473
  -7.250  -0.3482   0.08448   0.08006  -0.0427   1.0000   0.0474
  -7.000  -0.3502   0.08162   0.07719  -0.0430   1.0000   0.0474
  -6.750  -0.3381   0.07556   0.07125  -0.0432   0.9953   0.0484
  -6.500  -0.3200   0.07229   0.06803  -0.0424   0.9893   0.0511
  -6.250  -0.2919   0.06790   0.06355  -0.0488   0.9803   0.0564
  -5.750  -0.2297   0.05682   0.05202  -0.0644   0.9601   0.0632
  -5.500  -0.2026   0.05305   0.04815  -0.0674   0.9512   0.0655
  -5.250  -0.1705   0.04923   0.04383  -0.0728   0.9382   0.0767
  -5.000  -0.1342   0.04270   0.03647  -0.0748   0.9264   0.0474
  -4.750  -0.1097   0.03844   0.03210  -0.0763   0.9148   0.0462
  -4.500  -0.0826   0.03518   0.02852  -0.0777   0.9032   0.0493
  -4.250  -0.0517   0.03230   0.02504  -0.0785   0.8921   0.0485
  -4.000  -0.0226   0.03014   0.02245  -0.0788   0.8796   0.0480
  -3.750   0.0043   0.02791   0.02004  -0.0793   0.8676   0.0498
  -3.500   0.0323   0.02644   0.01835  -0.0796   0.8557   0.0520
  -3.250   0.0615   0.02478   0.01629  -0.0795   0.8443   0.0519
  -3.000   0.0906   0.02337   0.01450  -0.0793   0.8334   0.0519
  -2.750   0.1190   0.02221   0.01303  -0.0790   0.8218   0.0522
  -2.500   0.1468   0.02131   0.01191  -0.0787   0.8097   0.0538
  -2.250   0.1745   0.02058   0.01098  -0.0784   0.7980   0.0562
  -2.000   0.2022   0.01981   0.01001  -0.0781   0.7869   0.0568
  -1.750   0.2297   0.01910   0.00916  -0.0776   0.7762   0.0572
  -1.500   0.2565   0.01850   0.00845  -0.0771   0.7630   0.0577
  -1.250   0.2828   0.01795   0.00782  -0.0765   0.7490   0.0585
  -1.000   0.3089   0.01748   0.00728  -0.0759   0.7350   0.0595
  -0.750   0.3350   0.01710   0.00681  -0.0753   0.7215   0.0605
  -0.500   0.3612   0.01668   0.00634  -0.0749   0.7095   0.0638
  -0.250   0.3880   0.01644   0.00602  -0.0745   0.6986   0.0688
   0.000   0.4153   0.01625   0.00570  -0.0742   0.6882   0.0725
   0.250   0.4425   0.01611   0.00545  -0.0738   0.6770   0.0768
   0.500   0.4697   0.01596   0.00524  -0.0735   0.6664   0.0873
   0.750   0.5001   0.01350   0.00516  -0.0737   0.6568   1.0000
   1.000   0.5269   0.01365   0.00507  -0.0733   0.6460   1.0000
   1.250   0.5536   0.01382   0.00504  -0.0729   0.6352   1.0000
   1.500   0.5802   0.01399   0.00504  -0.0726   0.6252   1.0000
   1.750   0.6068   0.01417   0.00508  -0.0723   0.6145   1.0000
   2.000   0.6334   0.01436   0.00517  -0.0720   0.6033   1.0000
   2.250   0.6599   0.01456   0.00527  -0.0717   0.5923   1.0000
   2.500   0.6863   0.01476   0.00537  -0.0714   0.5816   1.0000
   2.750   0.7127   0.01495   0.00551  -0.0711   0.5697   1.0000
   3.000   0.7389   0.01515   0.00569  -0.0709   0.5572   1.0000
   3.250   0.7651   0.01535   0.00586  -0.0706   0.5445   1.0000
   3.500   0.7911   0.01555   0.00603  -0.0702   0.5312   1.0000
   3.750   0.8170   0.01576   0.00623  -0.0699   0.5176   1.0000
   4.000   0.8428   0.01598   0.00643  -0.0696   0.5039   1.0000
   4.250   0.8684   0.01621   0.00664  -0.0692   0.4896   1.0000
   4.500   0.8938   0.01646   0.00686  -0.0688   0.4744   1.0000
   4.750   0.9188   0.01673   0.00712  -0.0684   0.4587   1.0000
   5.000   0.9437   0.01703   0.00739  -0.0679   0.4434   1.0000
   5.250   0.9684   0.01737   0.00769  -0.0674   0.4291   1.0000
   5.500   0.9929   0.01773   0.00806  -0.0670   0.4158   1.0000
   5.750   1.0173   0.01813   0.00843  -0.0665   0.4033   1.0000
   6.000   1.0414   0.01854   0.00884  -0.0660   0.3914   1.0000
   6.250   1.0656   0.01897   0.00933  -0.0656   0.3801   1.0000
   6.500   1.0897   0.01942   0.00982  -0.0651   0.3708   1.0000
   6.750   1.1136   0.01990   0.01033  -0.0646   0.3622   1.0000
   7.000   1.1373   0.02037   0.01089  -0.0641   0.3522   1.0000
   7.250   1.1603   0.02088   0.01146  -0.0635   0.3422   1.0000
   7.500   1.1830   0.02139   0.01203  -0.0629   0.3324   1.0000
   7.750   1.2054   0.02190   0.01267  -0.0622   0.3218   1.0000
   8.000   1.2271   0.02244   0.01330  -0.0615   0.3110   1.0000
   8.250   1.2473   0.02298   0.01395  -0.0605   0.2971   1.0000
   8.500   1.2662   0.02353   0.01459  -0.0595   0.2810   1.0000
   8.750   1.2844   0.02412   0.01527  -0.0583   0.2643   1.0000
   9.000   1.3010   0.02477   0.01599  -0.0570   0.2452   1.0000
   9.250   1.3169   0.02549   0.01678  -0.0556   0.2269   1.0000
   9.500   1.3324   0.02626   0.01769  -0.0542   0.2042   1.0000
   9.750   1.3446   0.02724   0.01867  -0.0524   0.1750   1.0000
  10.000   1.3456   0.02894   0.02006  -0.0496   0.1338   1.0000
  10.250   1.3430   0.03084   0.02179  -0.0463   0.1077   1.0000
  10.500   1.3367   0.03324   0.02397  -0.0432   0.0652   1.0000
  10.750   1.3294   0.03589   0.02650  -0.0406   0.0503   1.0000
  11.000   1.3253   0.03847   0.02917  -0.0387   0.0406   1.0000
  11.250   1.3213   0.04123   0.03204  -0.0372   0.0343   1.0000
  11.500   1.3176   0.04414   0.03509  -0.0363   0.0304   1.0000
  11.750   1.3114   0.04749   0.03853  -0.0357   0.0280   1.0000
  12.000   1.3060   0.05095   0.04216  -0.0355   0.0263   1.0000
  12.250   1.2992   0.05476   0.04617  -0.0356   0.0249   1.0000
  12.500   1.2908   0.05896   0.05052  -0.0362   0.0239   1.0000
  12.750   1.2805   0.06356   0.05526  -0.0370   0.0231   1.0000
  13.000   1.2685   0.06853   0.06038  -0.0381   0.0225   1.0000
  13.250   1.2554   0.07383   0.06583  -0.0394   0.0221   1.0000
  13.500   1.2438   0.07906   0.07121  -0.0408   0.0217   1.0000
  13.750   1.2331   0.08434   0.07666  -0.0424   0.0215   1.0000
  14.000   1.2231   0.08963   0.08211  -0.0440   0.0212   1.0000
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