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GOE 140 (MVA H.17) AIRFOIL (goe140-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 140 (MVA H.17) AIRFOIL (goe140-il)
Reynolds number: 100,000
Max Cl/Cd: 54.31 at α=9.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe140-il-100000.txt
Download as CSV file: xf-goe140-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 140 (MVA H.17) 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.2156   0.10213   0.09770  -0.0256   1.0000   0.0560
  -8.750  -0.2115   0.09906   0.09467  -0.0260   1.0000   0.0574
  -8.500  -0.3028   0.10740   0.10273  -0.0205   1.0000   0.0540
  -8.250  -0.2944   0.10390   0.09925  -0.0206   1.0000   0.0554
  -8.000  -0.2883   0.10095   0.09635  -0.0212   1.0000   0.0568
  -7.750  -0.2839   0.09826   0.09371  -0.0220   1.0000   0.0583
  -7.500  -0.2817   0.09584   0.09136  -0.0226   1.0000   0.0598
  -7.250  -0.2816   0.09377   0.08937  -0.0235   1.0000   0.0615
  -7.000  -0.2812   0.09261   0.08831  -0.0277   1.0000   0.0631
  -6.750  -0.2783   0.09237   0.08812  -0.0355   1.0000   0.0638
  -6.500  -0.2750   0.09031   0.08609  -0.0389   1.0000   0.0642
  -6.250  -0.2785   0.08490   0.08083  -0.0310   1.0000   0.0651
  -6.000  -0.2812   0.08221   0.07823  -0.0274   1.0000   0.0661
  -5.750  -0.2850   0.08023   0.07632  -0.0253   1.0000   0.0671
  -5.500  -0.2884   0.07844   0.07459  -0.0241   1.0000   0.0682
  -5.250  -0.2900   0.07665   0.07284  -0.0237   1.0000   0.0696
  -5.000  -0.1992   0.07322   0.06881  -0.0502   0.9886   0.0765
  -4.750  -0.1814   0.06585   0.06169  -0.0498   0.9831   0.0783
  -4.500  -0.1458   0.06154   0.05735  -0.0544   0.9736   0.0830
  -4.250  -0.0778   0.05720   0.05257  -0.0691   0.9634   0.0905
  -4.000  -0.0417   0.05237   0.04779  -0.0729   0.9564   0.0943
  -3.750   0.0176   0.04888   0.04389  -0.0829   0.9454   0.1048
  -3.500   0.0568   0.04493   0.03997  -0.0870   0.9364   0.1136
  -3.250   0.1051   0.04131   0.03613  -0.0931   0.9266   0.1238
  -3.000   0.1477   0.03842   0.03301  -0.0975   0.9128   0.1366
  -2.750   0.1853   0.03581   0.03023  -0.1003   0.8979   0.1518
  -2.500   0.2212   0.03379   0.02793  -0.1026   0.8816   0.1773
  -2.250   0.2471   0.03165   0.02572  -0.1029   0.8621   0.2079
  -1.250   0.3406   0.02496   0.01879  -0.0993   0.7793   0.3709
  -1.000   0.3740   0.02381   0.01724  -0.1000   0.7586   0.3727
  -0.750   0.4159   0.02283   0.01560  -0.1017   0.7361   0.3018
  -0.500   0.4641   0.02299   0.01440  -0.1008   0.7168   0.1480
  -0.250   0.4938   0.02251   0.01348  -0.0997   0.6961   0.1323
   0.000   0.5216   0.02127   0.01207  -0.0992   0.6759   0.1240
   0.250   0.5503   0.02089   0.01129  -0.0982   0.6572   0.1163
   0.500   0.5779   0.02025   0.01043  -0.0976   0.6397   0.1140
   0.750   0.6053   0.01980   0.00982  -0.0970   0.6216   0.1135
   1.000   0.6326   0.01947   0.00933  -0.0964   0.6049   0.1153
   1.250   0.6590   0.01910   0.00892  -0.0958   0.5893   0.1233
   1.500   0.6855   0.01891   0.00863  -0.0952   0.5748   0.1318
   1.750   0.7126   0.01867   0.00828  -0.0947   0.5616   0.1451
   2.250   0.7633   0.01682   0.00790  -0.0930   0.5372   1.0000
   2.500   0.7905   0.01721   0.00803  -0.0927   0.5252   1.0000
   2.750   0.8176   0.01762   0.00823  -0.0925   0.5144   1.0000
   3.000   0.8449   0.01803   0.00842  -0.0923   0.5047   1.0000
   3.250   0.8716   0.01848   0.00882  -0.0922   0.4944   1.0000
   3.500   0.8987   0.01896   0.00919  -0.0921   0.4861   1.0000
   3.750   0.9256   0.01944   0.00961  -0.0920   0.4775   1.0000
   4.000   0.9524   0.01999   0.01011  -0.0919   0.4699   1.0000
   4.250   0.9792   0.02049   0.01060  -0.0918   0.4624   1.0000
   4.500   1.0058   0.02108   0.01117  -0.0917   0.4556   1.0000
   4.750   1.0322   0.02164   0.01175  -0.0916   0.4486   1.0000
   5.000   1.0594   0.02224   0.01227  -0.0916   0.4434   1.0000
   5.250   1.0846   0.02296   0.01319  -0.0914   0.4371   1.0000
   5.500   1.1112   0.02358   0.01382  -0.0914   0.4321   1.0000
   5.750   1.1372   0.02430   0.01458  -0.0913   0.4272   1.0000
   6.000   1.1618   0.02504   0.01552  -0.0911   0.4211   1.0000
   6.250   1.1884   0.02557   0.01605  -0.0909   0.4159   1.0000
   6.500   1.2119   0.02617   0.01680  -0.0905   0.4080   1.0000
   6.750   1.2386   0.02618   0.01666  -0.0900   0.3984   1.0000
   7.000   1.2621   0.02616   0.01673  -0.0892   0.3864   1.0000
   7.250   1.2850   0.02623   0.01689  -0.0884   0.3747   1.0000
   7.500   1.3107   0.02651   0.01716  -0.0880   0.3679   1.0000
   7.750   1.3332   0.02673   0.01754  -0.0873   0.3583   1.0000
   8.000   1.3554   0.02663   0.01755  -0.0863   0.3458   1.0000
   8.250   1.3772   0.02651   0.01748  -0.0852   0.3332   1.0000
   8.500   1.4003   0.02655   0.01754  -0.0844   0.3236   1.0000
   8.750   1.4210   0.02672   0.01791  -0.0833   0.3130   1.0000
   9.000   1.4396   0.02670   0.01804  -0.0818   0.2984   1.0000
   9.250   1.4576   0.02684   0.01837  -0.0803   0.2837   1.0000
   9.500   1.4762   0.02718   0.01893  -0.0790   0.2707   1.0000
   9.750   1.4919   0.02753   0.01940  -0.0772   0.2516   1.0000
  10.000   1.5039   0.02819   0.02016  -0.0751   0.2151   1.0000
  10.250   1.4958   0.03053   0.02182  -0.0714   0.1253   1.0000
  10.500   1.4833   0.03347   0.02454  -0.0672   0.0943   1.0000
  10.750   1.4717   0.03623   0.02723  -0.0634   0.0653   1.0000
  11.000   1.4593   0.03935   0.03033  -0.0607   0.0544   1.0000
  11.250   1.4472   0.04286   0.03394  -0.0590   0.0493   1.0000
  11.500   1.4357   0.04676   0.03799  -0.0583   0.0466   1.0000
  11.750   1.4235   0.05118   0.04261  -0.0584   0.0448   1.0000
  12.000   1.4091   0.05631   0.04794  -0.0593   0.0437   1.0000
  12.250   1.3927   0.06210   0.05393  -0.0608   0.0430   1.0000
  12.500   1.3751   0.06834   0.06036  -0.0626   0.0426   1.0000
  12.750   1.3573   0.07474   0.06693  -0.0645   0.0422   1.0000
  13.000   1.3405   0.08101   0.07336  -0.0663   0.0419   1.0000
  13.250   1.3250   0.08704   0.07953  -0.0680   0.0415   1.0000
  13.500   1.3113   0.09278   0.08538  -0.0695   0.0410   1.0000
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