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GOE 604 AIRFOIL (goe604-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 604 AIRFOIL (goe604-il)
Reynolds number: 100,000
Max Cl/Cd: 42.32 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe604-il-100000-n5.txt
Download as CSV file: xf-goe604-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 604 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.4703   0.05117   0.04574  -0.0957   0.9582   0.0513
 -10.750  -0.4888   0.04578   0.03987  -0.0990   0.9367   0.0519
 -10.500  -0.4953   0.04189   0.03544  -0.0994   0.9155   0.0529
 -10.250  -0.4838   0.03935   0.03260  -0.0997   0.8981   0.0538
 -10.000  -0.4623   0.03769   0.03085  -0.1001   0.8813   0.0549
  -9.750  -0.4438   0.03602   0.02898  -0.0999   0.8632   0.0562
  -9.500  -0.4269   0.03435   0.02702  -0.0993   0.8441   0.0577
  -9.250  -0.4109   0.03265   0.02492  -0.0983   0.8249   0.0594
  -9.000  -0.3916   0.03115   0.02313  -0.0975   0.8063   0.0607
  -8.750  -0.3691   0.03004   0.02192  -0.0969   0.7884   0.0620
  -8.500  -0.3474   0.02903   0.02073  -0.0962   0.7714   0.0636
  -8.250  -0.3260   0.02805   0.01950  -0.0953   0.7557   0.0656
  -8.000  -0.3044   0.02708   0.01820  -0.0943   0.7409   0.0678
  -7.750  -0.2827   0.02623   0.01731  -0.0934   0.7268   0.0695
  -7.500  -0.2606   0.02550   0.01647  -0.0925   0.7143   0.0715
  -7.250  -0.2378   0.02480   0.01558  -0.0917   0.7033   0.0742
  -7.000  -0.2160   0.02414   0.01477  -0.0906   0.6917   0.0771
  -6.750  -0.1938   0.02355   0.01411  -0.0897   0.6819   0.0801
  -6.500  -0.1717   0.02300   0.01346  -0.0886   0.6718   0.0838
  -6.250  -0.1489   0.02247   0.01281  -0.0877   0.6634   0.0876
  -6.000  -0.1268   0.02202   0.01234  -0.0867   0.6540   0.0930
  -5.750  -0.1033   0.02160   0.01184  -0.0858   0.6465   0.0998
  -5.500  -0.0806   0.02124   0.01147  -0.0849   0.6376   0.1086
  -5.250  -0.0565   0.02095   0.01111  -0.0841   0.6300   0.1210
  -5.000  -0.0328   0.02071   0.01086  -0.0833   0.6221   0.1365
  -4.750  -0.0087   0.02051   0.01060  -0.0825   0.6143   0.1536
  -4.500   0.0161   0.02034   0.01032  -0.0818   0.6076   0.1702
  -4.250   0.0399   0.02019   0.01015  -0.0810   0.5997   0.1855
  -4.000   0.0649   0.02008   0.00993  -0.0803   0.5930   0.2005
  -3.750   0.0893   0.01996   0.00980  -0.0796   0.5863   0.2144
  -3.500   0.1135   0.01986   0.00969  -0.0788   0.5794   0.2281
  -3.250   0.1388   0.01977   0.00954  -0.0782   0.5734   0.2430
  -3.000   0.1630   0.01970   0.00949  -0.0775   0.5670   0.2609
  -2.750   0.1872   0.01963   0.00943  -0.0767   0.5604   0.2792
  -2.500   0.2126   0.01952   0.00927  -0.0761   0.5548   0.2961
  -2.250   0.2371   0.01944   0.00919  -0.0754   0.5487   0.3119
  -2.000   0.2615   0.01935   0.00911  -0.0746   0.5423   0.3293
  -1.750   0.2867   0.01924   0.00899  -0.0740   0.5370   0.3496
  -1.500   0.3110   0.01915   0.00895  -0.0732   0.5314   0.3741
  -1.250   0.3345   0.01907   0.00897  -0.0724   0.5249   0.4035
  -1.000   0.3592   0.01895   0.00890  -0.0716   0.5194   0.4387
  -0.750   0.3840   0.01884   0.00889  -0.0709   0.5143   0.4826
  -0.500   0.4069   0.01872   0.00901  -0.0699   0.5080   0.5407
  -0.250   0.4305   0.01853   0.00908  -0.0688   0.5027   0.6244
   0.000   0.4598   0.01833   0.00918  -0.0683   0.4983   0.7401
   0.250   0.5099   0.01844   0.00953  -0.0721   0.4909   0.8536
   0.500   0.5619   0.01863   0.00963  -0.0764   0.4843   0.9157
   0.750   0.6097   0.01884   0.00967  -0.0802   0.4788   0.9530
   1.000   0.6611   0.01911   0.00988  -0.0850   0.4716   0.9854
   1.250   0.7039   0.01930   0.00992  -0.0882   0.4662   1.0000
   1.500   0.7244   0.01948   0.00993  -0.0869   0.4625   1.0000
   1.750   0.7409   0.01977   0.01022  -0.0851   0.4572   1.0000
   2.000   0.7594   0.02001   0.01040  -0.0835   0.4524   1.0000
   2.250   0.7795   0.02022   0.01049  -0.0822   0.4482   1.0000
   2.500   0.8002   0.02045   0.01060  -0.0809   0.4445   1.0000
   2.750   0.8169   0.02079   0.01095  -0.0791   0.4392   1.0000
   3.000   0.8358   0.02107   0.01119  -0.0776   0.4348   1.0000
   3.250   0.8567   0.02132   0.01133  -0.0764   0.4311   1.0000
   3.500   0.8787   0.02158   0.01149  -0.0754   0.4280   1.0000
   3.750   0.8947   0.02201   0.01197  -0.0735   0.4236   1.0000
   4.000   0.9130   0.02239   0.01233  -0.0720   0.4196   1.0000
   4.250   0.9332   0.02271   0.01261  -0.0708   0.4163   1.0000
   4.500   0.9553   0.02301   0.01282  -0.0698   0.4134   1.0000
   4.750   0.9757   0.02338   0.01315  -0.0687   0.4103   1.0000
   5.000   0.9900   0.02388   0.01372  -0.0666   0.4061   1.0000
   5.250   1.0073   0.02428   0.01412  -0.0650   0.4020   1.0000
   5.500   1.0277   0.02459   0.01438  -0.0639   0.3986   1.0000
   5.750   1.0512   0.02484   0.01454  -0.0632   0.3955   1.0000
   6.000   1.0639   0.02540   0.01517  -0.0610   0.3916   1.0000
   6.250   1.0772   0.02593   0.01576  -0.0589   0.3875   1.0000
   6.500   1.0944   0.02634   0.01616  -0.0574   0.3839   1.0000
   6.750   1.1154   0.02662   0.01639  -0.0564   0.3806   1.0000
   7.000   1.1358   0.02698   0.01671  -0.0554   0.3776   1.0000
   7.250   1.1407   0.02774   0.01759  -0.0522   0.3734   1.0000
   7.500   1.1497   0.02832   0.01823  -0.0495   0.3696   1.0000
   7.750   1.1643   0.02878   0.01870  -0.0477   0.3665   1.0000
   8.000   1.1842   0.02915   0.01903  -0.0467   0.3638   1.0000
   8.250   1.2034   0.02958   0.01944  -0.0457   0.3611   1.0000
   8.500   1.1984   0.03071   0.02073  -0.0416   0.3574   1.0000
   8.750   1.2011   0.03166   0.02177  -0.0387   0.3535   1.0000
   9.000   1.2131   0.03227   0.02239  -0.0370   0.3497   1.0000
   9.250   1.2350   0.03251   0.02259  -0.0364   0.3465   1.0000
   9.500   1.2403   0.03352   0.02366  -0.0342   0.3431   1.0000
   9.750   1.2284   0.03543   0.02574  -0.0308   0.3390   1.0000
  10.000   1.2286   0.03689   0.02730  -0.0287   0.3352   1.0000
  10.250   1.2423   0.03764   0.02806  -0.0277   0.3319   1.0000
  10.500   1.2677   0.03773   0.02811  -0.0274   0.3292   1.0000
  10.750   1.2453   0.04085   0.03143  -0.0246   0.3250   1.0000
  11.000   1.2105   0.04546   0.03624  -0.0222   0.3197   1.0000
  11.250   1.2174   0.04694   0.03777  -0.0214   0.3159   1.0000
  11.500   1.2470   0.04649   0.03728  -0.0212   0.3133   1.0000
  11.750   1.1147   0.06240   0.05358  -0.0206   0.3002   1.0000
  12.000   1.1461   0.06132   0.05250  -0.0199   0.2983   1.0000
  12.250   1.1853   0.05943   0.05058  -0.0193   0.2968   1.0000
  12.750   1.1205   0.07242   0.06379  -0.0203   0.2804   1.0000
  13.250   1.0899   0.08211   0.07362  -0.0215   0.2647   1.0000
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