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GOE 275 (DAIMLER VI) AIRFOIL (goe275-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 275 (DAIMLER VI) AIRFOIL (goe275-il)
Reynolds number: 100,000
Max Cl/Cd: 53.1 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe275-il-100000.txt
Download as CSV file: xf-goe275-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 275 (DAIMLER VI) 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3420   0.10688   0.10195  -0.0276   1.0000   0.0498
  -8.250  -0.3518   0.10590   0.10108  -0.0279   1.0000   0.0500
  -8.000  -0.3568   0.10444   0.09971  -0.0306   1.0000   0.0501
  -7.750  -0.3288   0.09601   0.09123  -0.0241   1.0000   0.0523
  -7.500  -0.3284   0.09359   0.08887  -0.0226   1.0000   0.0540
  -7.250  -0.3332   0.09168   0.08704  -0.0212   1.0000   0.0555
  -7.000  -0.3367   0.08960   0.08504  -0.0209   1.0000   0.0572
  -6.750  -0.3398   0.08762   0.08314  -0.0216   1.0000   0.0588
  -6.500  -0.3413   0.08601   0.08157  -0.0251   1.0000   0.0603
  -6.250  -0.3346   0.08481   0.08026  -0.0330   1.0000   0.0611
  -6.000  -0.3344   0.08011   0.07568  -0.0299   1.0000   0.0619
  -5.750  -0.3340   0.07681   0.07247  -0.0254   1.0000   0.0632
  -5.500  -0.3303   0.07416   0.06986  -0.0238   1.0000   0.0650
  -5.250  -0.3236   0.07151   0.06722  -0.0240   1.0000   0.0675
  -5.000  -0.3106   0.06874   0.06440  -0.0268   1.0000   0.0713
  -4.750  -0.2856   0.06542   0.06082  -0.0343   1.0000   0.0749
  -4.500  -0.2846   0.06224   0.05779  -0.0306   1.0000   0.0770
  -4.250  -0.2746   0.05983   0.05539  -0.0300   1.0000   0.0814
  -4.000  -0.2458   0.05673   0.05201  -0.0357   1.0000   0.0895
  -3.750  -0.2390   0.05403   0.04942  -0.0337   1.0000   0.0928
  -3.500  -0.2095   0.05186   0.04690  -0.0380   1.0000   0.1040
  -3.250  -0.2015   0.04903   0.04424  -0.0363   1.0000   0.1076
  -3.000  -0.1627   0.04611   0.04114  -0.0413   0.9953   0.1221
  -2.750  -0.1093   0.04344   0.03817  -0.0488   0.9859   0.1506
  -2.500  -0.0677   0.04088   0.03552  -0.0535   0.9768   0.1814
  -0.750   0.2668   0.02516   0.01762  -0.0797   0.9107   0.1621
  -0.500   0.3217   0.02338   0.01534  -0.0827   0.9025   0.1310
  -0.250   0.3671   0.02206   0.01370  -0.0843   0.8904   0.1166
   0.000   0.4147   0.02043   0.01197  -0.0868   0.8795   0.1080
   0.250   0.4624   0.01945   0.01081  -0.0890   0.8672   0.1024
   0.500   0.5014   0.01825   0.00967  -0.0899   0.8496   0.1007
   0.750   0.5383   0.01732   0.00876  -0.0903   0.8282   0.1022
   1.000   0.5727   0.01644   0.00788  -0.0903   0.8023   0.1044
   1.250   0.6052   0.01583   0.00715  -0.0898   0.7699   0.1061
   1.500   0.6380   0.01544   0.00655  -0.0896   0.7328   0.1101
   1.750   0.6676   0.01534   0.00617  -0.0888   0.6916   0.1174
   2.000   0.6951   0.01462   0.00610  -0.0884   0.6542   0.4570
   2.250   0.7307   0.01398   0.00608  -0.0890   0.6171   1.0000
   2.500   0.7563   0.01446   0.00618  -0.0880   0.5905   1.0000
   2.750   0.7808   0.01492   0.00638  -0.0870   0.5669   1.0000
   3.000   0.8056   0.01536   0.00658  -0.0862   0.5471   1.0000
   3.250   0.8306   0.01580   0.00681  -0.0854   0.5300   1.0000
   3.500   0.8555   0.01623   0.00710  -0.0847   0.5151   1.0000
   3.750   0.8806   0.01668   0.00745  -0.0841   0.5021   1.0000
   4.000   0.9058   0.01714   0.00784  -0.0835   0.4903   1.0000
   4.250   0.9313   0.01761   0.00820  -0.0829   0.4791   1.0000
   4.500   0.9561   0.01805   0.00856  -0.0823   0.4671   1.0000
   4.750   0.9798   0.01848   0.00900  -0.0814   0.4542   1.0000
   5.000   1.0034   0.01890   0.00940  -0.0806   0.4410   1.0000
   5.250   1.0269   0.01934   0.00980  -0.0797   0.4280   1.0000
   5.500   1.0508   0.01981   0.01022  -0.0789   0.4158   1.0000
   5.750   1.0755   0.02032   0.01067  -0.0783   0.4043   1.0000
   6.000   1.0981   0.02081   0.01125  -0.0773   0.3920   1.0000
   6.250   1.1208   0.02134   0.01182  -0.0763   0.3793   1.0000
   6.500   1.1434   0.02188   0.01238  -0.0754   0.3664   1.0000
   6.750   1.1661   0.02244   0.01296  -0.0745   0.3535   1.0000
   7.000   1.1884   0.02298   0.01347  -0.0735   0.3401   1.0000
   7.250   1.2106   0.02351   0.01398  -0.0725   0.3268   1.0000
   7.500   1.2306   0.02403   0.01464  -0.0711   0.3133   1.0000
   7.750   1.2507   0.02459   0.01535  -0.0698   0.3001   1.0000
   8.000   1.2702   0.02511   0.01597  -0.0684   0.2865   1.0000
   8.250   1.2887   0.02553   0.01649  -0.0668   0.2720   1.0000
   8.500   1.3058   0.02588   0.01692  -0.0649   0.2560   1.0000
   8.750   1.3214   0.02623   0.01733  -0.0628   0.2388   1.0000
   9.000   1.3365   0.02678   0.01780  -0.0607   0.2216   1.0000
   9.250   1.3512   0.02772   0.01876  -0.0587   0.2046   1.0000
   9.500   1.3682   0.02891   0.01987  -0.0571   0.1915   1.0000
   9.750   1.3869   0.03020   0.02114  -0.0559   0.1808   1.0000
  10.000   1.4042   0.03167   0.02277  -0.0545   0.1719   1.0000
  10.250   1.4277   0.03330   0.02427  -0.0542   0.1644   1.0000
  10.500   1.4405   0.03463   0.02594  -0.0522   0.1574   1.0000
  10.750   1.4595   0.03600   0.02723  -0.0514   0.1494   1.0000
  11.000   1.4655   0.03697   0.02854  -0.0485   0.1419   1.0000
  11.250   1.4772   0.03801   0.02958  -0.0467   0.1343   1.0000
  11.500   1.4806   0.03894   0.03078  -0.0437   0.1277   1.0000
  11.750   1.4889   0.03997   0.03182  -0.0414   0.1214   1.0000
  12.000   1.4861   0.04110   0.03325  -0.0376   0.1159   1.0000
  12.250   1.4901   0.04211   0.03421  -0.0350   0.1097   1.0000
  12.500   1.4826   0.04373   0.03617  -0.0315   0.1042   1.0000
  12.750   1.4818   0.04532   0.03768  -0.0291   0.0973   1.0000
  13.000   1.4713   0.04767   0.04028  -0.0264   0.0908   1.0000
  13.250   1.4644   0.05068   0.04331  -0.0245   0.0832   1.0000
  13.500   1.4572   0.05370   0.04633  -0.0229   0.0757   1.0000
  13.750   1.4453   0.05782   0.05068  -0.0217   0.0707   1.0000
  14.000   1.4319   0.06178   0.05490  -0.0210   0.0671   1.0000
  14.250   1.4393   0.06512   0.05806  -0.0203   0.0616   1.0000
  14.500   1.4209   0.06967   0.06297  -0.0205   0.0605   1.0000
  14.750   1.4021   0.07482   0.06844  -0.0215   0.0593   1.0000
  15.000   1.3834   0.08048   0.07438  -0.0233   0.0583   1.0000
  15.250   1.3634   0.08671   0.08086  -0.0258   0.0575   1.0000
  15.500   1.3406   0.09382   0.08822  -0.0291   0.0572   1.0000
  15.750   1.3130   0.10229   0.09695  -0.0338   0.0576   1.0000
  16.000   1.2802   0.11248   0.10738  -0.0400   0.0587   1.0000
  16.250   1.2456   0.12392   0.11901  -0.0473   0.0600   1.0000
  16.500   1.2115   0.13616   0.13136  -0.0550   0.0612   1.0000
  16.750   1.0503   0.19784   0.19273  -0.0925   0.0882   1.0000
  17.000   1.0589   0.20213   0.19706  -0.0934   0.0871   1.0000
  17.250   1.0667   0.20717   0.20213  -0.0945   0.0865   1.0000
  17.500   0.8292   0.20953   0.20517  -0.0927   0.1222   1.0000
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