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GOE 673 AIRFOIL (goe673-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 673 AIRFOIL (goe673-il)
Reynolds number: 100,000
Max Cl/Cd: 55.53 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe673-il-100000-n5.txt
Download as CSV file: xf-goe673-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 673 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4214   0.09348   0.08866  -0.0416   1.0000   0.0247
  -9.000  -0.4252   0.08923   0.08449  -0.0432   1.0000   0.0243
  -8.750  -0.4318   0.08495   0.08030  -0.0446   1.0000   0.0237
  -8.500  -0.4423   0.08073   0.07619  -0.0456   1.0000   0.0231
  -8.250  -0.4778   0.07018   0.06577  -0.0520   1.0000   0.0195
  -8.000  -0.4925   0.06627   0.06177  -0.0526   1.0000   0.0190
  -7.750  -0.5040   0.06324   0.05863  -0.0518   1.0000   0.0188
  -7.500  -0.5127   0.06010   0.05535  -0.0506   1.0000   0.0187
  -7.250  -0.5191   0.05656   0.05163  -0.0496   1.0000   0.0188
  -7.000  -0.5219   0.05280   0.04764  -0.0486   1.0000   0.0188
  -6.750  -0.5071   0.04716   0.04155  -0.0517   0.9961   0.0191
  -6.500  -0.4842   0.04212   0.03599  -0.0548   0.9913   0.0194
  -6.250  -0.4558   0.03804   0.03131  -0.0573   0.9872   0.0193
  -6.000  -0.4278   0.03453   0.02724  -0.0589   0.9826   0.0193
  -5.750  -0.3970   0.03130   0.02348  -0.0607   0.9789   0.0195
  -5.500  -0.3660   0.02858   0.02034  -0.0620   0.9751   0.0200
  -5.250  -0.3352   0.02647   0.01793  -0.0632   0.9708   0.0213
  -5.000  -0.3011   0.02485   0.01607  -0.0648   0.9674   0.0240
  -4.750  -0.2697   0.02333   0.01429  -0.0656   0.9630   0.0257
  -4.500  -0.2379   0.02201   0.01280  -0.0665   0.9583   0.0273
  -4.250  -0.2029   0.02085   0.01146  -0.0683   0.9548   0.0309
  -4.000  -0.1718   0.01987   0.01034  -0.0693   0.9495   0.0362
  -3.750  -0.1386   0.01895   0.00928  -0.0706   0.9445   0.0458
  -3.500  -0.1033   0.01735   0.00834  -0.0729   0.9412   0.1773
  -3.250  -0.0740   0.01622   0.00817  -0.0742   0.9360   0.3849
  -3.000  -0.0440   0.01567   0.00806  -0.0748   0.9303   0.5136
  -2.750  -0.0089   0.01537   0.00774  -0.0761   0.9263   0.5648
  -2.500   0.0175   0.01519   0.00760  -0.0756   0.9182   0.6133
  -2.250   0.0510   0.01498   0.00737  -0.0765   0.9134   0.6662
  -2.000   0.0773   0.01484   0.00722  -0.0759   0.9052   0.7122
  -1.750   0.1086   0.01463   0.00701  -0.0761   0.8996   0.7580
  -1.500   0.1330   0.01447   0.00691  -0.0748   0.8911   0.8092
  -1.250   0.1646   0.01425   0.00673  -0.0746   0.8855   0.8732
  -1.000   0.2019   0.01414   0.00659  -0.0762   0.8777   0.9392
  -0.750   0.2498   0.01396   0.00629  -0.0803   0.8721   0.9875
  -0.500   0.2802   0.01391   0.00610  -0.0811   0.8623   1.0000
  -0.250   0.3094   0.01385   0.00592  -0.0815   0.8536   1.0000
   0.000   0.3386   0.01379   0.00576  -0.0818   0.8446   1.0000
   0.250   0.3651   0.01380   0.00569  -0.0816   0.8339   1.0000
   0.500   0.3929   0.01379   0.00561  -0.0817   0.8238   1.0000
   0.750   0.4224   0.01374   0.00550  -0.0819   0.8147   1.0000
   1.000   0.4495   0.01376   0.00547  -0.0818   0.8034   1.0000
   1.250   0.4764   0.01379   0.00547  -0.0816   0.7917   1.0000
   1.500   0.5039   0.01382   0.00549  -0.0815   0.7801   1.0000
   1.750   0.5317   0.01385   0.00550  -0.0814   0.7685   1.0000
   2.000   0.5597   0.01387   0.00551  -0.0814   0.7567   1.0000
   2.250   0.5876   0.01391   0.00557  -0.0813   0.7445   1.0000
   2.500   0.6145   0.01400   0.00566  -0.0811   0.7310   1.0000
   2.750   0.6415   0.01409   0.00577  -0.0808   0.7171   1.0000
   3.000   0.6685   0.01419   0.00590  -0.0806   0.7029   1.0000
   3.250   0.6955   0.01431   0.00608  -0.0803   0.6883   1.0000
   3.500   0.7223   0.01445   0.00625  -0.0800   0.6734   1.0000
   3.750   0.7486   0.01462   0.00647  -0.0797   0.6577   1.0000
   4.000   0.7748   0.01482   0.00676  -0.0793   0.6417   1.0000
   4.250   0.8008   0.01504   0.00707  -0.0789   0.6258   1.0000
   4.500   0.8268   0.01528   0.00741  -0.0785   0.6101   1.0000
   4.750   0.8526   0.01554   0.00780  -0.0780   0.5943   1.0000
   5.000   0.8776   0.01581   0.00820  -0.0774   0.5746   1.0000
   5.250   0.8946   0.01611   0.00831  -0.0748   0.5148   1.0000
   5.500   0.9064   0.01684   0.00854  -0.0717   0.4176   1.0000
   5.750   0.9121   0.01841   0.00923  -0.0681   0.2675   1.0000
   6.000   0.9058   0.02181   0.01108  -0.0636   0.0508   1.0000
   6.250   0.9208   0.02317   0.01244  -0.0616   0.0356   1.0000
   6.500   0.9362   0.02438   0.01380  -0.0596   0.0299   1.0000
   6.750   0.9503   0.02558   0.01521  -0.0577   0.0256   1.0000
   7.000   0.9588   0.02715   0.01692  -0.0549   0.0239   1.0000
   7.250   0.9692   0.02851   0.01847  -0.0522   0.0229   1.0000
   7.500   0.9791   0.02993   0.02004  -0.0496   0.0217   1.0000
   7.750   0.9901   0.03135   0.02159  -0.0471   0.0199   1.0000
   8.000   1.0043   0.03295   0.02328  -0.0452   0.0184   1.0000
   8.250   1.0246   0.03491   0.02533  -0.0441   0.0175   1.0000
   8.500   1.0514   0.03724   0.02781  -0.0439   0.0168   1.0000
   8.750   1.0777   0.03984   0.03061  -0.0436   0.0163   1.0000
   9.000   1.0980   0.04248   0.03348  -0.0427   0.0156   1.0000
   9.250   1.1129   0.04572   0.03696  -0.0416   0.0146   1.0000
   9.500   1.1225   0.05042   0.04204  -0.0400   0.0139   1.0000
   9.750   1.1251   0.05375   0.04572  -0.0373   0.0136   1.0000
  10.000   1.1248   0.05667   0.04907  -0.0343   0.0136   1.0000
  10.250   1.1198   0.05968   0.05238  -0.0311   0.0135   1.0000
  10.500   1.1118   0.06285   0.05584  -0.0280   0.0136   1.0000
  10.750   1.1015   0.06624   0.05950  -0.0253   0.0136   1.0000
  11.000   1.0891   0.06987   0.06338  -0.0231   0.0136   1.0000
  11.250   1.0749   0.07385   0.06759  -0.0215   0.0137   1.0000
  11.750   1.0461   0.08209   0.07632  -0.0204   0.0138   1.0000
  12.000   1.0314   0.08641   0.08083  -0.0208   0.0138   1.0000
  12.250   1.0163   0.09112   0.08574  -0.0221   0.0139   1.0000
  12.500   1.0011   0.09626   0.09105  -0.0241   0.0140   1.0000
  12.750   0.9859   0.10185   0.09682  -0.0268   0.0141   1.0000
  13.000   0.9707   0.10801   0.10313  -0.0304   0.0142   1.0000
  13.250   0.9555   0.11489   0.11016  -0.0348   0.0143   1.0000
  13.500   0.9403   0.12282   0.11823  -0.0402   0.0145   1.0000
  13.750   0.9245   0.13253   0.12806  -0.0470   0.0148   1.0000
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