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GOE 561 AIRFOIL (goe561-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 561 AIRFOIL (goe561-il)
Reynolds number: 500,000
Max Cl/Cd: 43.22 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe561-il-500000.txt
Download as CSV file: xf-goe561-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 561 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500   0.5555   0.10314   0.09773  -0.1722   0.5380   0.0301
 -12.250   0.5506   0.10105   0.09566  -0.1740   0.5370   0.0304
 -12.000   0.5479   0.09885   0.09349  -0.1754   0.5353   0.0305
 -11.500   0.5741   0.09409   0.08874  -0.1755   0.5310   0.0308
 -11.250   0.5838   0.09216   0.08681  -0.1759   0.5289   0.0309
 -11.000   0.5945   0.09035   0.08500  -0.1762   0.5269   0.0311
 -10.750   0.6032   0.08850   0.08314  -0.1767   0.5250   0.0313
 -10.500   0.6113   0.08662   0.08124  -0.1774   0.5230   0.0315
 -10.250   0.6201   0.08473   0.07932  -0.1784   0.5204   0.0315
 -10.000   0.6309   0.08276   0.07732  -0.1798   0.5181   0.0319
  -9.750   0.6355   0.08090   0.07550  -0.1798   0.5170   0.0325
  -9.500   0.6392   0.07905   0.07369  -0.1797   0.5155   0.0329
  -9.250   0.6424   0.07698   0.07165  -0.1802   0.5144   0.0336
  -9.000   0.6212   0.07360   0.06832  -0.1827   0.5135   0.0344
  -8.750   0.6132   0.07081   0.06557  -0.1838   0.5123   0.0345
  -8.500   0.6152   0.06869   0.06348  -0.1830   0.5103   0.0346
  -8.250   0.6200   0.06700   0.06181  -0.1821   0.5086   0.0346
  -8.000   0.6277   0.06575   0.06057  -0.1804   0.5063   0.0348
  -7.750   0.6300   0.06406   0.05888  -0.1798   0.5047   0.0349
  -7.500   0.6299   0.06230   0.05713  -0.1794   0.5030   0.0350
  -7.250   0.6350   0.06086   0.05569  -0.1790   0.5009   0.0355
  -7.000   0.6322   0.05851   0.05333  -0.1806   0.4985   0.0356
  -6.750   0.6131   0.05652   0.05139  -0.1786   0.4976   0.0358
  -6.500   0.5885   0.05509   0.05001  -0.1735   0.4968   0.0358
  -6.250   0.5571   0.05401   0.04899  -0.1662   0.4957   0.0359
  -6.000   0.5317   0.05283   0.04784  -0.1596   0.4948   0.0360
  -5.750   0.5126   0.05146   0.04649  -0.1538   0.4932   0.0362
  -5.500   0.4972   0.05003   0.04505  -0.1485   0.4919   0.0365
  -5.250   0.4855   0.04859   0.04359  -0.1436   0.4906   0.0365
  -5.000   0.4734   0.04707   0.04204  -0.1384   0.4892   0.0370
  -4.750   0.4209   0.04370   0.03817  -0.1251   0.4887   0.0387
  -4.500   0.4194   0.04199   0.03645  -0.1210   0.4871   0.0388
  -4.250   0.4228   0.04057   0.03505  -0.1178   0.4854   0.0389
  -4.000   0.4270   0.03954   0.03404  -0.1147   0.4836   0.0391
  -3.750   0.4312   0.03839   0.03281  -0.1112   0.4818   0.0393
  -3.500   0.4451   0.03733   0.03166  -0.1098   0.4790   0.0396
  -3.250   0.4441   0.03641   0.03073  -0.1050   0.4777   0.0398
  -3.000   0.4435   0.03547   0.02976  -0.1003   0.4766   0.0402
  -2.750   0.4426   0.03450   0.02874  -0.0953   0.4752   0.0406
  -2.500   0.4246   0.03330   0.02692  -0.0847   0.4739   0.0432
  -2.250   0.4302   0.03179   0.02548  -0.0814   0.4721   0.0434
  -2.000   0.4368   0.03088   0.02463  -0.0782   0.4703   0.0437
  -1.750   0.4425   0.03019   0.02388  -0.0745   0.4684   0.0439
  -1.500   0.4478   0.02955   0.02319  -0.0706   0.4664   0.0442
  -1.250   0.4551   0.02899   0.02255  -0.0670   0.4646   0.0446
  -1.000   0.4664   0.02841   0.02186  -0.0641   0.4624   0.0454
  -0.750   0.4774   0.02757   0.02052  -0.0596   0.4600   0.0483
  -0.500   0.4800   0.02699   0.01997  -0.0552   0.4588   0.0485
  -0.250   0.4842   0.02656   0.01958  -0.0513   0.4571   0.0488
   0.000   0.4899   0.02621   0.01924  -0.0476   0.4552   0.0494
   0.250   0.4963   0.02588   0.01886  -0.0438   0.4531   0.0501
   0.500   0.4978   0.02579   0.01840  -0.0380   0.4511   0.0535
   0.750   0.5097   0.02508   0.01772  -0.0355   0.4490   0.0539
   1.000   0.5208   0.02465   0.01726  -0.0329   0.4469   0.0544
   1.250   0.5362   0.02431   0.01684  -0.0309   0.4445   0.0555
   1.500   0.5547   0.02400   0.01628  -0.0289   0.4417   0.0596
   1.750   0.5617   0.02380   0.01613  -0.0257   0.4400   0.0603
   2.000   0.5692   0.02373   0.01606  -0.0226   0.4377   0.0608
   2.250   0.5776   0.02373   0.01594  -0.0193   0.4353   0.0657
   2.500   0.5950   0.02348   0.01571  -0.0182   0.4328   0.0673
   2.750   0.6061   0.02350   0.01562  -0.0157   0.4300   0.0728
   3.000   0.6287   0.02334   0.01543  -0.0155   0.4273   0.0758
   3.250   0.6555   0.02319   0.01521  -0.0161   0.4245   0.0830
   3.500   0.7385   0.02200   0.01371  -0.0266   0.4215   0.0469
   3.750   0.7636   0.02217   0.01391  -0.0275   0.4185   0.0468
   4.000   0.7889   0.02237   0.01409  -0.0283   0.4156   0.0475
   4.250   0.8150   0.02258   0.01426  -0.0293   0.4127   0.0481
   4.500   0.8527   0.02264   0.01433  -0.0326   0.4094   0.0501
   4.750   0.8773   0.02307   0.01480  -0.0337   0.4064   0.0506
   5.000   0.8964   0.02363   0.01541  -0.0339   0.4028   0.0522
   5.250   0.9160   0.02417   0.01598  -0.0341   0.3995   0.0546
   5.500   0.9354   0.02467   0.01648  -0.0342   0.3962   0.0571
   5.750   0.9553   0.02515   0.01689  -0.0342   0.3928   0.0591
   6.000   0.9708   0.02588   0.01769  -0.0339   0.3898   0.0615
   6.250   0.9842   0.02673   0.01858  -0.0334   0.3864   0.0661
   6.500   0.9977   0.02756   0.01943  -0.0328   0.3831   0.0704
   6.750   1.0142   0.02826   0.02015  -0.0326   0.3799   0.0890
   7.000   1.3026   0.03014   0.02401  -0.0888   0.3732   1.0000
   7.250   1.3099   0.03136   0.02525  -0.0874   0.3700   1.0000
   7.500   1.3190   0.03249   0.02635  -0.0862   0.3669   1.0000
   7.750   1.3266   0.03371   0.02753  -0.0850   0.3637   1.0000
   8.000   1.3376   0.03470   0.02846  -0.0840   0.3604   1.0000
   8.250   1.3443   0.03610   0.02991  -0.0828   0.3581   1.0000
   8.500   1.3498   0.03760   0.03144  -0.0816   0.3550   1.0000
   8.750   1.3581   0.03890   0.03274  -0.0806   0.3524   1.0000
   9.000   1.3638   0.04039   0.03419  -0.0795   0.3491   1.0000
   9.250   1.3771   0.04125   0.03498  -0.0788   0.3463   1.0000
   9.500   1.3815   0.04293   0.03672  -0.0778   0.3437   1.0000
   9.750   1.3819   0.04500   0.03884  -0.0765   0.3406   1.0000
  10.000   1.3887   0.04652   0.04038  -0.0757   0.3382   1.0000
  10.250   1.3938   0.04818   0.04203  -0.0748   0.3354   1.0000
  10.500   1.4042   0.04936   0.04316  -0.0742   0.3328   1.0000
  10.750   1.4211   0.04996   0.04370  -0.0740   0.3306   1.0000
  11.000   1.4196   0.05234   0.04618  -0.0729   0.3286   1.0000
  11.250   1.4191   0.05464   0.04854  -0.0720   0.3260   1.0000
  11.500   1.4249   0.05636   0.05029  -0.0714   0.3239   1.0000
  11.750   1.4288   0.05826   0.05220  -0.0707   0.3216   1.0000
  12.000   1.4389   0.05955   0.05346  -0.0703   0.3194   1.0000
  12.250   1.4553   0.06019   0.05405  -0.0702   0.3175   1.0000
  12.500   1.4666   0.06135   0.05521  -0.0700   0.3155   1.0000
  12.750   1.4618   0.06421   0.05817  -0.0691   0.3137   1.0000
  13.000   1.4601   0.06675   0.06078  -0.0684   0.3113   1.0000
  13.250   1.4619   0.06895   0.06303  -0.0679   0.3093   1.0000
  13.500   1.4676   0.07075   0.06485  -0.0675   0.3075   1.0000
  13.750   1.4770   0.07215   0.06624  -0.0674   0.3056   1.0000
  14.000   1.4917   0.07297   0.06702  -0.0674   0.3039   1.0000
  14.250   1.5129   0.07307   0.06707  -0.0676   0.3023   1.0000
  14.500   1.5040   0.07644   0.07055  -0.0669   0.3002   1.0000
  14.750   1.4976   0.07956   0.07377  -0.0662   0.2985   1.0000
  15.000   1.4928   0.08252   0.07681  -0.0657   0.2963   1.0000
  15.250   1.4936   0.08490   0.07922  -0.0655   0.2942   1.0000
  15.500   1.5007   0.08657   0.08091  -0.0654   0.2925   1.0000
  15.750   1.5106   0.08793   0.08229  -0.0654   0.2914   1.0000
  16.000   1.5266   0.08857   0.08289  -0.0657   0.2899   1.0000
  16.250   1.5491   0.08842   0.08271  -0.0661   0.2884   1.0000
  16.500   1.5546   0.09022   0.08456  -0.0660   0.2872   1.0000
  16.750   1.5121   0.09752   0.09208  -0.0646   0.2844   1.0000
  17.000   1.4913   0.10244   0.09710  -0.0640   0.2813   1.0000
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