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GOE 155 (SSW D.1) AIRFOIL (goe155-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 155 (SSW D.1) AIRFOIL (goe155-il)
Reynolds number: 200,000
Max Cl/Cd: 78.57 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe155-il-200000-n5.txt
Download as CSV file: xf-goe155-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 155 (SSW D.1) AIRFOIL                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3266   0.10962   0.10629  -0.0204   1.0000   0.0200
  -8.750  -0.3209   0.10687   0.10358  -0.0235   1.0000   0.0201
  -8.500  -0.3154   0.10402   0.10077  -0.0265   1.0000   0.0202
  -8.000  -0.2950   0.09701   0.09380  -0.0340   0.9762   0.0203
  -7.750  -0.2789   0.09286   0.08965  -0.0389   0.9635   0.0203
  -7.500  -0.2634   0.08885   0.08561  -0.0432   0.9514   0.0203
  -7.250  -0.2541   0.08478   0.08155  -0.0431   0.9413   0.0205
  -7.000  -0.2442   0.08175   0.07850  -0.0420   0.9321   0.0211
  -6.750  -0.2320   0.07879   0.07551  -0.0439   0.9215   0.0217
  -6.500  -0.2177   0.07592   0.07261  -0.0465   0.9105   0.0232
  -6.250  -0.1877   0.07215   0.06876  -0.0573   0.8990   0.0261
  -6.000  -0.1642   0.06807   0.06459  -0.0628   0.8906   0.0262
  -5.750  -0.1404   0.06387   0.06030  -0.0676   0.8817   0.0263
  -5.500  -0.0905   0.04235   0.03885  -0.0686   0.8506   0.0264
  -5.250  -0.0865   0.03938   0.03593  -0.0653   0.8444   0.0278
  -5.000  -0.0679   0.03669   0.03317  -0.0670   0.8371   0.0311
  -4.750  -0.0257   0.03164   0.02778  -0.0770   0.8317   0.0342
  -4.500  -0.0039   0.02679   0.02279  -0.0799   0.8243   0.0346
  -4.250   0.0104   0.02424   0.02021  -0.0794   0.8167   0.0359
  -4.000   0.0315   0.02235   0.01824  -0.0801   0.8074   0.0397
  -3.750   0.0623   0.01879   0.01440  -0.0836   0.8007   0.0454
  -3.250   0.1207   0.03056   0.02534  -0.0919   0.8058   0.0390
  -3.000   0.1516   0.02780   0.02225  -0.0931   0.7983   0.0407
  -2.750   0.1858   0.02310   0.01688  -0.0943   0.7922   0.0360
  -2.500   0.2160   0.02056   0.01379  -0.0946   0.7868   0.0355
  -2.250   0.2434   0.01970   0.01284  -0.0950   0.7798   0.0372
  -2.000   0.2720   0.01836   0.01116  -0.0950   0.7741   0.0377
  -1.750   0.3014   0.01691   0.00932  -0.0951   0.7676   0.0370
  -1.500   0.3298   0.01591   0.00804  -0.0950   0.7612   0.0369
  -1.250   0.3580   0.01515   0.00707  -0.0949   0.7551   0.0371
  -1.000   0.3862   0.01452   0.00629  -0.0949   0.7480   0.0375
  -0.750   0.4139   0.01400   0.00564  -0.0947   0.7412   0.0380
  -0.500   0.4417   0.01359   0.00517  -0.0946   0.7323   0.0393
  -0.250   0.4693   0.01326   0.00476  -0.0944   0.7232   0.0410
   0.000   0.4966   0.01291   0.00434  -0.0941   0.7132   0.0413
   0.250   0.5242   0.01261   0.00401  -0.0940   0.7017   0.0414
   0.500   0.5518   0.01238   0.00374  -0.0938   0.6901   0.0417
   0.750   0.5793   0.01221   0.00351  -0.0937   0.6776   0.0421
   1.000   0.6068   0.01209   0.00332  -0.0935   0.6647   0.0427
   1.250   0.6343   0.01201   0.00318  -0.0934   0.6519   0.0436
   1.500   0.6619   0.01194   0.00309  -0.0932   0.6382   0.0458
   1.750   0.6893   0.01190   0.00304  -0.0931   0.6230   0.0500
   2.000   0.7167   0.01188   0.00304  -0.0930   0.6063   0.0683
   2.250   0.7439   0.01178   0.00310  -0.0929   0.5882   0.1603
   2.500   0.7704   0.01027   0.00318  -0.0928   0.5686   1.0000
   2.750   0.7969   0.01047   0.00323  -0.0925   0.5476   1.0000
   3.000   0.8233   0.01069   0.00331  -0.0922   0.5258   1.0000
   3.250   0.8494   0.01095   0.00343  -0.0919   0.5042   1.0000
   3.500   0.8754   0.01123   0.00358  -0.0917   0.4834   1.0000
   3.750   0.9012   0.01153   0.00378  -0.0914   0.4642   1.0000
   4.000   0.9270   0.01185   0.00400  -0.0911   0.4471   1.0000
   4.250   0.9528   0.01216   0.00424  -0.0909   0.4317   1.0000
   4.500   0.9785   0.01246   0.00452  -0.0906   0.4174   1.0000
   4.750   1.0041   0.01278   0.00481  -0.0903   0.4029   1.0000
   5.000   1.0291   0.01316   0.00512  -0.0900   0.3846   1.0000
   5.250   1.0540   0.01352   0.00546  -0.0897   0.3639   1.0000
   5.500   1.0788   0.01389   0.00580  -0.0893   0.3450   1.0000
   5.750   1.1036   0.01425   0.00616  -0.0890   0.3298   1.0000
   6.000   1.1280   0.01464   0.00655  -0.0886   0.3136   1.0000
   6.250   1.1512   0.01513   0.00699  -0.0880   0.2913   1.0000
   6.500   1.1731   0.01575   0.00747  -0.0874   0.2642   1.0000
   6.750   1.1949   0.01637   0.00801  -0.0867   0.2393   1.0000
   7.000   1.2162   0.01703   0.00859  -0.0860   0.2137   1.0000
   7.250   1.2351   0.01795   0.00928  -0.0850   0.1612   1.0000
   7.500   1.2390   0.02060   0.01113  -0.0824   0.0430   1.0000
   7.750   1.2568   0.02161   0.01218  -0.0811   0.0330   1.0000
   8.000   1.2723   0.02280   0.01350  -0.0795   0.0274   1.0000
   8.250   1.2904   0.02361   0.01445  -0.0783   0.0243   1.0000
   8.500   1.3057   0.02461   0.01559  -0.0767   0.0215   1.0000
   8.750   1.3168   0.02587   0.01700  -0.0747   0.0197   1.0000
   9.000   1.3172   0.02767   0.01893  -0.0713   0.0182   1.0000
   9.250   1.3262   0.02880   0.02020  -0.0691   0.0172   1.0000
   9.500   1.3336   0.03013   0.02165  -0.0669   0.0160   1.0000
   9.750   1.3389   0.03171   0.02335  -0.0647   0.0150   1.0000
  10.000   1.3428   0.03350   0.02526  -0.0627   0.0143   1.0000
  10.250   1.3462   0.03543   0.02729  -0.0608   0.0138   1.0000
  10.500   1.3490   0.03751   0.02946  -0.0591   0.0132   1.0000
  10.750   1.3505   0.03980   0.03185  -0.0574   0.0128   1.0000
  11.000   1.3498   0.04243   0.03459  -0.0557   0.0123   1.0000
  11.250   1.3507   0.04504   0.03730  -0.0540   0.0118   1.0000
  11.500   1.3569   0.04708   0.03950  -0.0529   0.0113   1.0000
  11.750   1.3618   0.04930   0.04187  -0.0517   0.0107   1.0000
  12.000   1.3658   0.05171   0.04443  -0.0505   0.0103   1.0000
  12.250   1.3695   0.05425   0.04712  -0.0493   0.0100   1.0000
  12.500   1.3724   0.05692   0.04994  -0.0482   0.0097   1.0000
  12.750   1.3742   0.05974   0.05293  -0.0473   0.0094   1.0000
  13.000   1.3749   0.06275   0.05612  -0.0465   0.0092   1.0000
  13.250   1.3740   0.06597   0.05951  -0.0460   0.0090   1.0000
  13.500   1.3715   0.06944   0.06318  -0.0456   0.0089   1.0000
  13.750   1.3675   0.07317   0.06709  -0.0455   0.0088   1.0000
  14.000   1.3618   0.07718   0.07129  -0.0457   0.0087   1.0000
  14.250   1.3548   0.08149   0.07578  -0.0462   0.0086   1.0000
  14.500   1.3468   0.08609   0.08056  -0.0471   0.0085   1.0000
  14.750   1.3376   0.09103   0.08568  -0.0483   0.0084   1.0000
  15.000   1.3268   0.09643   0.09126  -0.0500   0.0083   1.0000
  15.250   1.3143   0.10235   0.09736  -0.0521   0.0082   1.0000
  15.750   1.2866   0.11556   0.11097  -0.0582   0.0081   1.0000
  16.000   1.2726   0.12270   0.11831  -0.0621   0.0081   1.0000
  16.250   1.2587   0.13017   0.12597  -0.0664   0.0080   1.0000
  16.500   1.2447   0.13797   0.13396  -0.0711   0.0080   1.0000
  16.750   1.2312   0.14605   0.14219  -0.0761   0.0081   1.0000
  17.000   1.2176   0.15457   0.15087  -0.0816   0.0081   1.0000
  17.250   1.2046   0.16352   0.15999  -0.0875   0.0081   1.0000
  17.500   1.1822   0.17721   0.17390  -0.0965   0.0084   1.0000
  17.750   0.8735   0.16893   0.16593  -0.0699   0.0106   1.0000
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