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GOE 735 AIRFOIL (goe735-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 735 AIRFOIL (goe735-il)
Reynolds number: 100,000
Max Cl/Cd: 35.9 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe735-il-100000-n5.txt
Download as CSV file: xf-goe735-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 735 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
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.3650   0.09407   0.08838  -0.0521   0.8172   0.0791
 -12.750  -0.6178   0.05329   0.04702  -0.0787   0.8280   0.0827
 -12.500  -0.6560   0.04880   0.04218  -0.0780   0.8176   0.0837
 -12.250  -0.6852   0.04554   0.03857  -0.0753   0.8074   0.0849
 -12.000  -0.7132   0.04264   0.03524  -0.0711   0.7977   0.0863
 -11.750  -0.7035   0.04191   0.03448  -0.0691   0.7880   0.0875
 -11.500  -0.6932   0.04134   0.03390  -0.0671   0.7788   0.0889
 -11.250  -0.6897   0.04048   0.03292  -0.0643   0.7696   0.0904
 -11.000  -0.6895   0.03928   0.03149  -0.0611   0.7614   0.0924
 -10.750  -0.6926   0.03765   0.02947  -0.0576   0.7526   0.0947
 -10.500  -0.6799   0.03687   0.02858  -0.0556   0.7451   0.0965
 -10.250  -0.6626   0.03634   0.02805  -0.0542   0.7356   0.0982
 -10.000  -0.6489   0.03564   0.02722  -0.0523   0.7274   0.1005
  -9.750  -0.6379   0.03463   0.02593  -0.0501   0.7196   0.1033
  -9.500  -0.6248   0.03361   0.02466  -0.0481   0.7108   0.1058
  -9.250  -0.6044   0.03314   0.02418  -0.0469   0.7037   0.1078
  -9.000  -0.5852   0.03260   0.02359  -0.0457   0.6942   0.1103
  -8.750  -0.5682   0.03185   0.02262  -0.0440   0.6863   0.1132
  -8.500  -0.5522   0.03099   0.02142  -0.0422   0.6787   0.1162
  -8.250  -0.5288   0.03040   0.02091  -0.0415   0.6696   0.1184
  -8.000  -0.5074   0.02987   0.02029  -0.0403   0.6626   0.1209
  -7.750  -0.4859   0.02929   0.01960  -0.0394   0.6533   0.1238
  -7.500  -0.4650   0.02861   0.01867  -0.0381   0.6456   0.1269
  -7.250  -0.4419   0.02795   0.01791  -0.0373   0.6380   0.1295
  -7.000  -0.4179   0.02743   0.01741  -0.0366   0.6292   0.1321
  -6.750  -0.3944   0.02691   0.01676  -0.0357   0.6226   0.1349
  -6.500  -0.3704   0.02641   0.01616  -0.0350   0.6137   0.1381
  -6.250  -0.3465   0.02591   0.01543  -0.0342   0.6063   0.1413
  -6.000  -0.3213   0.02535   0.01488  -0.0337   0.5993   0.1442
  -5.750  -0.2964   0.02492   0.01445  -0.0331   0.5911   0.1472
  -5.500  -0.2716   0.02448   0.01391  -0.0324   0.5846   0.1508
  -5.250  -0.2464   0.02413   0.01343  -0.0318   0.5773   0.1547
  -5.000  -0.2212   0.02370   0.01298  -0.0313   0.5701   0.1582
  -4.750  -0.1964   0.02331   0.01255  -0.0306   0.5643   0.1620
  -4.500  -0.1715   0.02302   0.01224  -0.0300   0.5571   0.1665
  -4.250  -0.1463   0.02275   0.01186  -0.0294   0.5503   0.1715
  -4.000  -0.1220   0.02237   0.01149  -0.0287   0.5450   0.1763
  -3.750  -0.0977   0.02215   0.01127  -0.0280   0.5388   0.1820
  -3.500  -0.0729   0.02195   0.01101  -0.0273   0.5324   0.1886
  -3.250  -0.0495   0.02165   0.01075  -0.0265   0.5270   0.1956
  -3.000  -0.0251   0.02147   0.01051  -0.0257   0.5218   0.2045
  -2.750  -0.0020   0.02129   0.01042  -0.0249   0.5156   0.2139
  -2.500   0.0219   0.02112   0.01025  -0.0241   0.5103   0.2265
  -2.250   0.0457   0.02091   0.01005  -0.0232   0.5060   0.2426
  -2.000   0.0688   0.02077   0.01000  -0.0224   0.5010   0.2634
  -1.750   0.0912   0.02061   0.01000  -0.0215   0.4954   0.2912
  -1.500   0.1141   0.02040   0.00992  -0.0205   0.4904   0.3290
  -1.250   0.1371   0.02014   0.00979  -0.0196   0.4863   0.3772
  -1.000   0.1586   0.01990   0.00982  -0.0185   0.4819   0.4386
  -0.750   0.1794   0.01957   0.00998  -0.0171   0.4771   0.5372
  -0.500   0.2117   0.01929   0.01022  -0.0175   0.4723   0.6625
  -0.250   0.2820   0.01948   0.01064  -0.0242   0.4671   0.7827
   0.000   0.3288   0.01990   0.01105  -0.0272   0.4620   0.8297
   0.250   0.3653   0.02032   0.01145  -0.0284   0.4567   0.8595
   0.500   0.4014   0.02072   0.01175  -0.0295   0.4524   0.8821
   0.750   0.4387   0.02111   0.01200  -0.0308   0.4487   0.9015
   1.000   0.4830   0.02160   0.01236  -0.0333   0.4448   0.9220
   1.250   0.5286   0.02213   0.01288  -0.0366   0.4395   0.9404
   1.500   0.5714   0.02246   0.01314  -0.0394   0.4348   0.9537
   1.750   0.6127   0.02269   0.01324  -0.0420   0.4309   0.9655
   2.000   0.6612   0.02284   0.01322  -0.0460   0.4277   0.9760
   2.250   0.7070   0.02313   0.01353  -0.0501   0.4233   0.9857
   2.500   0.7479   0.02336   0.01375  -0.0532   0.4189   0.9938
   2.750   0.7853   0.02346   0.01380  -0.0556   0.4150   0.9993
   3.000   0.8071   0.02362   0.01387  -0.0549   0.4120   1.0000
   3.250   0.8270   0.02377   0.01391  -0.0538   0.4094   1.0000
   3.500   0.8434   0.02418   0.01434  -0.0524   0.4063   1.0000
   3.750   0.8583   0.02465   0.01487  -0.0509   0.4029   1.0000
   4.000   0.8740   0.02507   0.01531  -0.0493   0.3997   1.0000
   4.250   0.8908   0.02541   0.01563  -0.0479   0.3968   1.0000
   4.500   0.9088   0.02568   0.01585  -0.0465   0.3942   1.0000
   4.750   0.9283   0.02590   0.01598  -0.0453   0.3918   1.0000
   5.000   0.9444   0.02631   0.01637  -0.0437   0.3892   1.0000
   5.250   0.9521   0.02707   0.01725  -0.0412   0.3857   1.0000
   5.500   0.9618   0.02773   0.01797  -0.0389   0.3826   1.0000
   5.750   0.9735   0.02829   0.01855  -0.0368   0.3799   1.0000
   6.000   0.9875   0.02873   0.01897  -0.0349   0.3774   1.0000
   6.250   1.0047   0.02905   0.01924  -0.0334   0.3752   1.0000
   6.500   1.0257   0.02927   0.01937  -0.0323   0.3731   1.0000
   6.750   1.0265   0.03020   0.02040  -0.0289   0.3701   1.0000
   7.000   1.0166   0.03148   0.02181  -0.0243   0.3668   1.0000
   7.250   1.0096   0.03260   0.02301  -0.0200   0.3637   1.0000
   7.500   1.0039   0.03351   0.02394  -0.0158   0.3612   1.0000
   7.750   1.0094   0.03409   0.02450  -0.0130   0.3588   1.0000
   8.000   1.0296   0.03429   0.02464  -0.0119   0.3568   1.0000
   8.250   1.0612   0.03425   0.02452  -0.0121   0.3550   1.0000
   8.500   0.8557   0.04729   0.03809   0.0025   0.3428   1.0000
   8.750   0.8725   0.04779   0.03856   0.0034   0.3408   1.0000
   9.000   0.9008   0.04731   0.03804   0.0041   0.3395   1.0000
   9.250   0.9353   0.04639   0.03706   0.0046   0.3386   1.0000
   9.500   0.9727   0.04537   0.03597   0.0050   0.3377   1.0000
  12.500   0.7139   0.10839   0.09969   0.0036   0.2581   1.0000
  12.750   0.7334   0.10869   0.09999   0.0040   0.2571   1.0000
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