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GOE 199 (L.F.G. 5406) AIRFOIL (goe199-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 199 (L.F.G. 5406) AIRFOIL (goe199-il)
Reynolds number: 500,000
Max Cl/Cd: 89.47 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe199-il-500000-n5.txt
Download as CSV file: xf-goe199-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 199 (L.F.G. 5406) 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3467   0.10658   0.10438  -0.0150   1.0000   0.0097
  -8.750  -0.3426   0.10263   0.10045  -0.0168   1.0000   0.0093
  -8.500  -0.3370   0.09934   0.09718  -0.0184   1.0000   0.0093
  -8.250  -0.3315   0.09625   0.09411  -0.0199   1.0000   0.0093
  -8.000  -0.3234   0.09294   0.09082  -0.0223   0.9879   0.0094
  -7.750  -0.3110   0.08928   0.08716  -0.0261   0.9648   0.0096
  -7.500  -0.2987   0.08575   0.08359  -0.0297   0.9439   0.0098
  -7.250  -0.2870   0.08242   0.08022  -0.0327   0.9237   0.0104
  -7.000  -0.2746   0.07842   0.07615  -0.0366   0.9055   0.0110
  -6.750  -0.2596   0.07383   0.07148  -0.0413   0.8901   0.0112
  -6.500  -0.2419   0.06966   0.06724  -0.0458   0.8770   0.0115
  -6.250  -0.2232   0.06710   0.06460  -0.0483   0.8651   0.0117
  -6.000  -0.2023   0.06401   0.06142  -0.0516   0.8539   0.0121
  -5.750  -0.1792   0.06057   0.05789  -0.0554   0.8435   0.0125
  -5.500  -0.1524   0.05646   0.05366  -0.0600   0.8347   0.0138
  -5.250  -0.1238   0.05205   0.04912  -0.0647   0.8271   0.0145
  -5.000  -0.0984   0.04960   0.04658  -0.0670   0.8196   0.0149
  -4.750  -0.0707   0.04665   0.04351  -0.0699   0.8128   0.0154
  -4.500  -0.0334   0.04177   0.03839  -0.0745   0.8068   0.0173
  -4.250  -0.0094   0.04016   0.03671  -0.0756   0.7996   0.0181
  -4.000   0.0191   0.03773   0.03415  -0.0774   0.7934   0.0186
  -3.750   0.0496   0.03497   0.03122  -0.0793   0.7869   0.0192
  -3.250   0.1105   0.03029   0.02619  -0.0820   0.7741   0.0226
  -3.000   0.1463   0.02822   0.02379  -0.0827   0.7660   0.0256
  -2.750   0.1759   0.02584   0.02115  -0.0833   0.7530   0.0256
  -2.500   0.2063   0.02392   0.01888  -0.0836   0.7350   0.0258
  -2.250   0.2336   0.02171   0.01644  -0.0842   0.7155   0.0255
  -2.000   0.2621   0.01999   0.01449  -0.0847   0.6988   0.0251
  -1.750   0.2917   0.01845   0.01266  -0.0849   0.6833   0.0251
  -1.500   0.3222   0.01703   0.01082  -0.0849   0.6677   0.0262
  -1.250   0.3510   0.01586   0.00941  -0.0851   0.6506   0.0263
  -1.000   0.3797   0.01525   0.00856  -0.0851   0.6300   0.0260
  -0.750   0.4080   0.01447   0.00752  -0.0852   0.6035   0.0261
  -0.500   0.4360   0.01366   0.00644  -0.0853   0.5726   0.0263
  -0.250   0.4638   0.01319   0.00575  -0.0853   0.5454   0.0266
   0.000   0.4917   0.01283   0.00522  -0.0854   0.5230   0.0268
   0.250   0.5196   0.01257   0.00484  -0.0855   0.5048   0.0273
   0.500   0.5475   0.01238   0.00458  -0.0856   0.4879   0.0281
   0.750   0.5754   0.01215   0.00424  -0.0856   0.4708   0.0283
   1.000   0.6033   0.01193   0.00392  -0.0857   0.4520   0.0282
   1.250   0.6310   0.01179   0.00368  -0.0857   0.4301   0.0282
   1.500   0.6585   0.01173   0.00351  -0.0857   0.4048   0.0284
   1.750   0.6858   0.01175   0.00340  -0.0857   0.3767   0.0288
   2.000   0.7130   0.01182   0.00334  -0.0858   0.3497   0.0293
   2.250   0.7402   0.01191   0.00332  -0.0858   0.3267   0.0300
   2.500   0.7675   0.01201   0.00334  -0.0859   0.3071   0.0306
   2.750   0.7948   0.01214   0.00340  -0.0859   0.2900   0.0313
   3.000   0.8220   0.01228   0.00347  -0.0859   0.2750   0.0323
   3.250   0.8493   0.01238   0.00351  -0.0860   0.2621   0.0333
   3.500   0.8765   0.01252   0.00361  -0.0860   0.2509   0.0339
   3.750   0.9036   0.01269   0.00372  -0.0860   0.2401   0.0350
   4.000   0.9306   0.01286   0.00385  -0.0860   0.2308   0.0366
   4.250   0.9577   0.01302   0.00400  -0.0860   0.2239   0.0391
   4.500   0.9848   0.01317   0.00417  -0.0860   0.2183   0.0492
   4.750   1.0095   0.01180   0.00448  -0.0859   0.2136   1.0000
   5.000   1.0365   0.01199   0.00468  -0.0859   0.2100   1.0000
   5.250   1.0633   0.01220   0.00488  -0.0858   0.2064   1.0000
   5.500   1.0898   0.01243   0.00510  -0.0857   0.2028   1.0000
   5.750   1.1160   0.01271   0.00536  -0.0856   0.1980   1.0000
   6.000   1.1425   0.01291   0.00558  -0.0856   0.1936   1.0000
   6.250   1.1687   0.01316   0.00583  -0.0855   0.1891   1.0000
   6.500   1.1946   0.01343   0.00610  -0.0853   0.1856   1.0000
   6.750   1.2205   0.01368   0.00638  -0.0852   0.1814   1.0000
   7.000   1.2463   0.01393   0.00664  -0.0850   0.1749   1.0000
   7.250   1.2713   0.01426   0.00696  -0.0848   0.1683   1.0000
   7.500   1.2969   0.01451   0.00725  -0.0846   0.1612   1.0000
   7.750   1.3215   0.01487   0.00758  -0.0843   0.1494   1.0000
   8.000   1.3418   0.01573   0.00813  -0.0835   0.0961   1.0000
   8.500   1.3766   0.01805   0.01012  -0.0810   0.0324   1.0000
   8.750   1.3981   0.01865   0.01075  -0.0802   0.0267   1.0000
   9.000   1.4184   0.01934   0.01147  -0.0793   0.0218   1.0000
   9.250   1.4393   0.01992   0.01210  -0.0785   0.0188   1.0000
   9.500   1.4584   0.02065   0.01284  -0.0774   0.0159   1.0000
   9.750   1.4776   0.02131   0.01359  -0.0763   0.0144   1.0000
  10.000   1.4958   0.02201   0.01435  -0.0750   0.0131   1.0000
  10.250   1.5118   0.02282   0.01522  -0.0735   0.0119   1.0000
  10.500   1.5259   0.02372   0.01619  -0.0717   0.0109   1.0000
  10.750   1.5401   0.02451   0.01709  -0.0699   0.0102   1.0000
  11.000   1.5513   0.02538   0.01805  -0.0676   0.0096   1.0000
  11.250   1.5588   0.02637   0.01913  -0.0648   0.0091   1.0000
  11.500   1.5650   0.02753   0.02038  -0.0622   0.0087   1.0000
  11.750   1.5688   0.02899   0.02193  -0.0595   0.0083   1.0000
  12.000   1.5706   0.03071   0.02377  -0.0569   0.0079   1.0000
  12.250   1.5755   0.03231   0.02551  -0.0550   0.0077   1.0000
  12.500   1.5790   0.03413   0.02745  -0.0533   0.0075   1.0000
  12.750   1.5816   0.03615   0.02959  -0.0518   0.0072   1.0000
  13.000   1.5832   0.03837   0.03193  -0.0505   0.0069   1.0000
  13.250   1.5837   0.04082   0.03451  -0.0494   0.0067   1.0000
  13.500   1.5834   0.04349   0.03729  -0.0486   0.0065   1.0000
  13.750   1.5814   0.04646   0.04038  -0.0481   0.0063   1.0000
  14.000   1.5771   0.04987   0.04390  -0.0478   0.0061   1.0000
  14.250   1.5704   0.05375   0.04792  -0.0478   0.0060   1.0000
  14.500   1.5604   0.05824   0.05255  -0.0483   0.0059   1.0000
  14.750   1.5479   0.06336   0.05782  -0.0492   0.0058   1.0000
  15.000   1.5337   0.06904   0.06364  -0.0506   0.0057   1.0000
  15.250   1.5177   0.07518   0.06993  -0.0523   0.0056   1.0000
  15.500   1.5040   0.08114   0.07602  -0.0541   0.0056   1.0000
  15.750   1.4908   0.08712   0.08214  -0.0559   0.0056   1.0000
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