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GOE 275 (DAIMLER VI) AIRFOIL (goe275-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 275 (DAIMLER VI) AIRFOIL (goe275-il)
Reynolds number: 1,000,000
Max Cl/Cd: 118.15 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe275-il-1000000.txt
Download as CSV file: xf-goe275-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3380   0.09835   0.09674  -0.0214   1.0000   0.0132
  -8.500  -0.3403   0.09565   0.09407  -0.0217   1.0000   0.0133
  -8.250  -0.3454   0.09325   0.09170  -0.0212   1.0000   0.0133
  -8.000  -0.3402   0.08946   0.08793  -0.0251   0.9986   0.0133
  -7.750  -0.3246   0.08504   0.08351  -0.0281   0.9967   0.0135
  -7.500  -0.3049   0.08193   0.08040  -0.0314   0.9947   0.0137
  -7.250  -0.2830   0.07799   0.07646  -0.0372   0.9908   0.0140
  -7.000  -0.2579   0.07399   0.07245  -0.0438   0.9872   0.0144
  -6.750  -0.2298   0.06953   0.06797  -0.0516   0.9846   0.0151
  -6.500  -0.1956   0.06306   0.06144  -0.0645   0.9763   0.0162
  -6.250  -0.1583   0.05634   0.05461  -0.0755   0.9726   0.0163
  -5.500  -0.0872   0.04632   0.04448  -0.0851   0.9508   0.0171
  -5.250  -0.0469   0.04264   0.04070  -0.0916   0.9457   0.0180
  -5.000   0.0054   0.03616   0.03385  -0.0996   0.9360   0.0197
  -4.750   0.0357   0.03112   0.02858  -0.1035   0.9257   0.0199
  -4.500   0.0638   0.02924   0.02661  -0.1054   0.9147   0.0202
  -4.250   0.0894   0.02759   0.02484  -0.1062   0.9029   0.0205
  -4.000   0.1137   0.02594   0.02305  -0.1064   0.8903   0.0211
  -3.750   0.1443   0.02406   0.02077  -0.1055   0.8784   0.0235
  -3.500   0.1683   0.02235   0.01879  -0.1048   0.8644   0.0236
  -3.250   0.1884   0.01902   0.01518  -0.1041   0.8499   0.0239
  -3.000   0.2112   0.01778   0.01383  -0.1036   0.8332   0.0242
  -2.750   0.2346   0.01682   0.01275  -0.1029   0.8141   0.0246
  -2.500   0.2580   0.01604   0.01181  -0.1021   0.7918   0.0253
  -2.250   0.2814   0.01528   0.01082  -0.1010   0.7617   0.0266
  -2.000   0.3067   0.01570   0.01080  -0.0993   0.7199   0.0282
  -1.750   0.3288   0.01523   0.00997  -0.0978   0.6736   0.0283
  -1.500   0.3497   0.01308   0.00756  -0.0968   0.6377   0.0291
  -1.250   0.3732   0.01256   0.00688  -0.0959   0.6063   0.0296
  -1.000   0.3977   0.01215   0.00632  -0.0952   0.5781   0.0303
  -0.750   0.4225   0.01187   0.00587  -0.0944   0.5496   0.0317
  -0.500   0.4481   0.01244   0.00618  -0.0935   0.5148   0.0338
  -0.250   0.4716   0.01128   0.00477  -0.0926   0.4775   0.0352
   0.000   0.4956   0.01100   0.00436  -0.0919   0.4388   0.0364
   0.250   0.5204   0.01090   0.00410  -0.0912   0.4078   0.0383
   0.500   0.5464   0.01148   0.00451  -0.0905   0.3846   0.0410
   0.750   0.5708   0.01048   0.00348  -0.0900   0.3678   0.0445
   1.000   0.5964   0.01040   0.00335  -0.0894   0.3540   0.0475
   1.250   0.6216   0.01013   0.00305  -0.0889   0.3435   0.0548
   1.500   0.6481   0.01013   0.00304  -0.0885   0.3364   0.0600
   1.750   0.6746   0.00987   0.00262  -0.0875   0.3306   0.0344
   2.000   0.7007   0.00980   0.00254  -0.0870   0.3247   0.0342
   2.250   0.7267   0.00964   0.00237  -0.0865   0.3194   0.0343
   2.500   0.7525   0.00957   0.00228  -0.0861   0.3140   0.0347
   2.750   0.7787   0.00954   0.00223  -0.0856   0.3092   0.0350
   3.000   0.8052   0.00950   0.00221  -0.0853   0.3045   0.0365
   3.250   0.8312   0.00955   0.00223  -0.0848   0.2980   0.0372
   3.500   0.8575   0.00959   0.00226  -0.0844   0.2930   0.0382
   3.750   0.8840   0.00963   0.00230  -0.0841   0.2879   0.0402
   4.000   0.9100   0.00972   0.00236  -0.0837   0.2818   0.0429
   4.250   0.9431   0.00817   0.00272  -0.0855   0.2759   1.0000
   4.500   0.9688   0.00831   0.00280  -0.0850   0.2681   1.0000
   4.750   0.9944   0.00845   0.00291  -0.0845   0.2601   1.0000
   5.000   1.0196   0.00863   0.00303  -0.0839   0.2478   1.0000
   5.250   1.0438   0.00889   0.00317  -0.0833   0.2249   1.0000
   5.500   1.0662   0.00931   0.00341  -0.0823   0.1931   1.0000
   5.750   1.0897   0.00965   0.00366  -0.0815   0.1781   1.0000
   6.000   1.1138   0.00991   0.00388  -0.0808   0.1699   1.0000
   6.250   1.1381   0.01016   0.00411  -0.0802   0.1629   1.0000
   6.500   1.1624   0.01041   0.00435  -0.0795   0.1562   1.0000
   6.750   1.1865   0.01068   0.00459  -0.0789   0.1483   1.0000
   7.000   1.2099   0.01100   0.00486  -0.0781   0.1361   1.0000
   7.250   1.2309   0.01155   0.00520  -0.0770   0.1019   1.0000
   7.500   1.2518   0.01210   0.00564  -0.0759   0.0861   1.0000
   7.750   1.2748   0.01243   0.00598  -0.0751   0.0827   1.0000
   8.000   1.2972   0.01282   0.00636  -0.0742   0.0793   1.0000
   8.250   1.3191   0.01324   0.00679  -0.0732   0.0751   1.0000
   8.500   1.3422   0.01353   0.00712  -0.0724   0.0731   1.0000
   8.750   1.3654   0.01379   0.00742  -0.0717   0.0718   1.0000
   9.000   1.3882   0.01408   0.00776  -0.0709   0.0698   1.0000
   9.250   1.4100   0.01444   0.00814  -0.0700   0.0674   1.0000
   9.500   1.4309   0.01486   0.00857  -0.0689   0.0642   1.0000
   9.750   1.4517   0.01526   0.00902  -0.0678   0.0616   1.0000
  10.000   1.4750   0.01545   0.00924  -0.0672   0.0596   1.0000
  10.250   1.4963   0.01577   0.00957  -0.0662   0.0558   1.0000
  10.500   1.5161   0.01620   0.00997  -0.0651   0.0505   1.0000
  10.750   1.5337   0.01677   0.01045  -0.0636   0.0390   1.0000
  11.000   1.5408   0.01805   0.01154  -0.0605   0.0194   1.0000
  11.250   1.5510   0.01889   0.01240  -0.0577   0.0158   1.0000
  11.500   1.5607   0.01967   0.01323  -0.0548   0.0141   1.0000
  11.750   1.5729   0.02029   0.01393  -0.0524   0.0134   1.0000
  12.000   1.5831   0.02104   0.01476  -0.0498   0.0127   1.0000
  12.250   1.5916   0.02190   0.01568  -0.0471   0.0120   1.0000
  12.500   1.5956   0.02304   0.01692  -0.0439   0.0112   1.0000
  12.750   1.6027   0.02402   0.01798  -0.0413   0.0108   1.0000
  13.000   1.6108   0.02495   0.01900  -0.0390   0.0105   1.0000
  13.250   1.6172   0.02604   0.02017  -0.0367   0.0101   1.0000
  13.500   1.6216   0.02732   0.02154  -0.0344   0.0097   1.0000
  13.750   1.6249   0.02874   0.02305  -0.0322   0.0094   1.0000
  14.000   1.6263   0.03040   0.02480  -0.0302   0.0092   1.0000
  14.250   1.6243   0.03244   0.02694  -0.0282   0.0090   1.0000
  14.500   1.6192   0.03493   0.02954  -0.0265   0.0087   1.0000
  14.750   1.6063   0.03841   0.03317  -0.0251   0.0084   1.0000
  15.000   1.5964   0.04198   0.03688  -0.0245   0.0083   1.0000
  15.250   1.5954   0.04482   0.03983  -0.0245   0.0082   1.0000
  15.500   1.5880   0.04871   0.04384  -0.0250   0.0082   1.0000
  15.750   1.5798   0.05297   0.04823  -0.0260   0.0081   1.0000
  16.000   1.5713   0.05749   0.05288  -0.0273   0.0080   1.0000
  16.250   1.5578   0.06299   0.05851  -0.0293   0.0079   1.0000
  16.500   1.5447   0.06861   0.06427  -0.0314   0.0078   1.0000
  16.750   1.5280   0.07502   0.07081  -0.0341   0.0078   1.0000
  17.000   1.5110   0.08165   0.07758  -0.0369   0.0078   1.0000
  17.250   1.4945   0.08832   0.08437  -0.0399   0.0077   1.0000
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