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GOE 275 (DAIMLER VI) AIRFOIL (goe275-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 275 (DAIMLER VI) AIRFOIL (goe275-il)
Reynolds number: 200,000
Max Cl/Cd: 73.3 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe275-il-200000-n5.txt
Download as CSV file: xf-goe275-il-200000-n5.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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3153   0.09597   0.09258  -0.0243   1.0000   0.0222
  -7.750  -0.3306   0.09491   0.09161  -0.0229   1.0000   0.0223
  -7.500  -0.3434   0.09361   0.09039  -0.0208   1.0000   0.0223
  -7.250  -0.3246   0.08896   0.08575  -0.0288   0.9956   0.0224
  -7.000  -0.3072   0.08485   0.08164  -0.0285   0.9928   0.0227
  -6.750  -0.2841   0.08071   0.07749  -0.0330   0.9878   0.0232
  -6.500  -0.2603   0.07655   0.07331  -0.0389   0.9814   0.0239
  -6.250  -0.2327   0.07214   0.06885  -0.0460   0.9759   0.0247
  -6.000  -0.2043   0.06761   0.06427  -0.0541   0.9675   0.0262
  -5.750  -0.1559   0.06115   0.05753  -0.0694   0.9583   0.0270
  -5.500  -0.1380   0.05718   0.05360  -0.0706   0.9536   0.0274
  -5.250  -0.1179   0.05413   0.05054  -0.0721   0.9470   0.0280
  -5.000  -0.0890   0.05064   0.04697  -0.0760   0.9410   0.0290
  -4.750  -0.0360   0.04621   0.04204  -0.0848   0.9351   0.0328
  -4.500  -0.0092   0.04174   0.03744  -0.0877   0.9278   0.0334
  -4.250   0.0214   0.03861   0.03430  -0.0908   0.9231   0.0343
  -4.000   0.0497   0.03609   0.03167  -0.0926   0.9137   0.0357
  -3.750   0.1005   0.03454   0.02937  -0.0965   0.9073   0.0409
  -3.500   0.1229   0.03023   0.02515  -0.0981   0.8973   0.0424
  -3.250   0.1551   0.02811   0.02293  -0.1001   0.8899   0.0443
  -3.000   0.1947   0.01055   0.00506  -0.0978   0.8567   0.0519
  -2.500   0.2460   0.00816   0.00234  -0.0985   0.8305   0.0644
  -2.000   0.3037   0.02096   0.01450  -0.1030   0.8299   0.0778
  -1.500   0.3647   0.01758   0.01025  -0.1013   0.7964   0.0418
  -1.250   0.3926   0.01703   0.00948  -0.1008   0.7730   0.0414
  -1.000   0.4199   0.01605   0.00832  -0.1004   0.7433   0.0400
  -0.750   0.4463   0.01534   0.00733  -0.0997   0.7061   0.0393
  -0.500   0.4713   0.01488   0.00656  -0.0987   0.6661   0.0390
  -0.250   0.4953   0.01455   0.00597  -0.0975   0.6310   0.0389
   0.000   0.5192   0.01430   0.00549  -0.0965   0.6002   0.0389
   0.250   0.5433   0.01415   0.00515  -0.0954   0.5725   0.0396
   0.500   0.5672   0.01417   0.00498  -0.0944   0.5447   0.0407
   0.750   0.5910   0.01404   0.00471  -0.0934   0.5179   0.0409
   1.000   0.6145   0.01389   0.00445  -0.0925   0.4911   0.0409
   1.250   0.6379   0.01381   0.00426  -0.0915   0.4663   0.0410
   1.500   0.6614   0.01370   0.00409  -0.0906   0.4433   0.0412
   1.750   0.6851   0.01363   0.00395  -0.0897   0.4248   0.0417
   2.000   0.7093   0.01364   0.00387  -0.0890   0.4098   0.0424
   2.250   0.7340   0.01368   0.00384  -0.0883   0.3979   0.0434
   2.500   0.7587   0.01377   0.00387  -0.0877   0.3882   0.0460
   2.750   0.7834   0.01391   0.00392  -0.0870   0.3779   0.0488
   3.000   0.8082   0.01405   0.00400  -0.0863   0.3674   0.0501
   3.250   0.8326   0.01424   0.00410  -0.0856   0.3573   0.0523
   3.500   0.8574   0.01439   0.00423  -0.0850   0.3481   0.0583
   3.750   0.8889   0.01298   0.00457  -0.0861   0.3395   1.0000
   4.000   0.9135   0.01323   0.00474  -0.0855   0.3313   1.0000
   4.250   0.9380   0.01349   0.00493  -0.0848   0.3242   1.0000
   4.500   0.9628   0.01372   0.00513  -0.0842   0.3170   1.0000
   4.750   0.9868   0.01401   0.00537  -0.0835   0.3109   1.0000
   5.000   1.0119   0.01422   0.00561  -0.0829   0.3044   1.0000
   5.250   1.0361   0.01448   0.00586  -0.0823   0.2978   1.0000
   5.500   1.0605   0.01473   0.00612  -0.0816   0.2910   1.0000
   5.750   1.0846   0.01499   0.00640  -0.0809   0.2826   1.0000
   6.000   1.1086   0.01523   0.00667  -0.0803   0.2727   1.0000
   6.250   1.1320   0.01551   0.00695  -0.0795   0.2613   1.0000
   6.500   1.1553   0.01579   0.00726  -0.0787   0.2504   1.0000
   6.750   1.1786   0.01608   0.00757  -0.0779   0.2378   1.0000
   7.000   1.2011   0.01642   0.00790  -0.0771   0.2234   1.0000
   7.250   1.2227   0.01681   0.00827  -0.0761   0.2069   1.0000
   7.500   1.2429   0.01732   0.00872  -0.0749   0.1901   1.0000
   7.750   1.2627   0.01787   0.00922  -0.0737   0.1778   1.0000
   8.000   1.2821   0.01845   0.00979  -0.0725   0.1675   1.0000
   8.250   1.3023   0.01896   0.01037  -0.0713   0.1587   1.0000
   8.500   1.3207   0.01959   0.01100  -0.0699   0.1502   1.0000
   8.750   1.3409   0.02007   0.01158  -0.0688   0.1402   1.0000
   9.000   1.3597   0.02064   0.01220  -0.0674   0.1292   1.0000
   9.250   1.3773   0.02126   0.01286  -0.0660   0.1164   1.0000
   9.500   1.3930   0.02199   0.01355  -0.0643   0.1044   1.0000
   9.750   1.4060   0.02282   0.01433  -0.0622   0.0959   1.0000
  10.000   1.4166   0.02372   0.01521  -0.0598   0.0897   1.0000
  10.250   1.4277   0.02458   0.01612  -0.0574   0.0851   1.0000
  10.500   1.4390   0.02542   0.01708  -0.0552   0.0814   1.0000
  10.750   1.4484   0.02639   0.01812  -0.0528   0.0784   1.0000
  11.000   1.4544   0.02756   0.01935  -0.0502   0.0754   1.0000
  11.250   1.4660   0.02842   0.02035  -0.0483   0.0730   1.0000
  11.500   1.4782   0.02925   0.02135  -0.0466   0.0692   1.0000
  11.750   1.4867   0.03034   0.02256  -0.0446   0.0653   1.0000
  12.000   1.4909   0.03177   0.02406  -0.0424   0.0623   1.0000
  12.250   1.5043   0.03260   0.02508  -0.0411   0.0580   1.0000
  12.500   1.5123   0.03385   0.02641  -0.0396   0.0508   1.0000
  12.750   1.5186   0.03531   0.02790  -0.0380   0.0398   1.0000
  13.000   1.5144   0.03772   0.03023  -0.0362   0.0263   1.0000
  13.250   1.5070   0.04058   0.03311  -0.0346   0.0218   1.0000
  13.500   1.5008   0.04357   0.03620  -0.0335   0.0199   1.0000
  13.750   1.4926   0.04700   0.03974  -0.0329   0.0185   1.0000
  14.000   1.4844   0.05072   0.04362  -0.0328   0.0175   1.0000
  14.250   1.4764   0.05469   0.04776  -0.0332   0.0168   1.0000
  14.500   1.4671   0.05909   0.05234  -0.0341   0.0162   1.0000
  14.750   1.4568   0.06387   0.05730  -0.0354   0.0158   1.0000
  15.000   1.4440   0.06929   0.06288  -0.0373   0.0153   1.0000
  15.250   1.4305   0.07504   0.06880  -0.0394   0.0150   1.0000
  15.500   1.4159   0.08121   0.07514  -0.0420   0.0148   1.0000
  15.750   1.4006   0.08769   0.08178  -0.0448   0.0145   1.0000
  16.000   1.3848   0.09445   0.08869  -0.0478   0.0143   1.0000
  16.250   1.3696   0.10123   0.09563  -0.0510   0.0142   1.0000
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