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HOBIE (hobie-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: HOBIE (hobie-il)
Reynolds number: 200,000
Max Cl/Cd: 78.79 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hobie-il-200000.txt
Download as CSV file: xf-hobie-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HOBIE                                           
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3835   0.10442   0.10068  -0.0304   1.0000   0.0507
  -9.250  -0.3893   0.10158   0.09790  -0.0339   1.0000   0.0513
  -9.000  -0.3932   0.09845   0.09484  -0.0362   1.0000   0.0515
  -8.750  -0.3975   0.09543   0.09187  -0.0378   1.0000   0.0516
  -8.500  -0.3838   0.09013   0.08656  -0.0340   1.0000   0.0532
  -8.250  -0.3762   0.08773   0.08419  -0.0327   1.0000   0.0543
  -8.000  -0.3740   0.08526   0.08176  -0.0321   1.0000   0.0555
  -7.750  -0.3763   0.08286   0.07942  -0.0316   1.0000   0.0566
  -7.500  -0.3835   0.08061   0.07723  -0.0306   1.0000   0.0577
  -7.250  -0.3891   0.07789   0.07458  -0.0309   1.0000   0.0592
  -7.000  -0.3955   0.07469   0.07144  -0.0330   1.0000   0.0611
  -6.750  -0.4020   0.06798   0.06469  -0.0460   1.0000   0.0634
  -6.500  -0.4036   0.06285   0.05940  -0.0497   1.0000   0.0636
  -6.250  -0.4095   0.05876   0.05548  -0.0464   1.0000   0.0649
  -6.000  -0.3977   0.05859   0.05538  -0.0429   0.9984   0.0666
  -5.750  -0.3595   0.05467   0.05135  -0.0499   0.9936   0.0736
  -5.500  -0.3194   0.04667   0.04307  -0.0616   0.9871   0.0810
  -5.250  -0.2782   0.04113   0.03718  -0.0702   0.9820   0.0939
  -5.000  -0.2439   0.03883   0.03475  -0.0738   0.9755   0.1080
  -4.750  -0.1979   0.02476   0.01897  -0.0820   0.9718   0.0710
  -4.500  -0.1617   0.02229   0.01598  -0.0841   0.9658   0.0731
  -4.250  -0.1230   0.02073   0.01396  -0.0863   0.9604   0.0758
  -4.000  -0.0822   0.01890   0.01173  -0.0890   0.9571   0.0784
  -3.750  -0.0488   0.01747   0.01021  -0.0903   0.9501   0.0817
  -3.500  -0.0089   0.01651   0.00914  -0.0926   0.9453   0.0850
  -3.250   0.0341   0.01557   0.00808  -0.0954   0.9422   0.0877
  -3.000   0.0670   0.01502   0.00741  -0.0961   0.9340   0.0904
  -2.750   0.1047   0.01412   0.00650  -0.0979   0.9289   0.0925
  -2.500   0.1377   0.01341   0.00583  -0.0987   0.9210   0.0954
  -2.250   0.1726   0.01287   0.00531  -0.0998   0.9136   0.0995
  -2.000   0.2034   0.01248   0.00490  -0.1000   0.9034   0.1038
  -1.750   0.2362   0.01200   0.00444  -0.1006   0.8948   0.1088
  -1.500   0.2653   0.01169   0.00413  -0.1004   0.8835   0.1167
  -1.250   0.2934   0.01132   0.00388  -0.1001   0.8717   0.1390
  -1.000   0.3208   0.01083   0.00377  -0.0998   0.8595   0.2563
  -0.750   0.3479   0.01050   0.00371  -0.0993   0.8467   0.3448
  -0.500   0.3745   0.01023   0.00361  -0.0987   0.8341   0.4103
  -0.250   0.3994   0.00986   0.00358  -0.0978   0.8215   0.5137
   0.000   0.4195   0.00921   0.00361  -0.0957   0.8087   0.7303
   0.250   0.4629   0.00879   0.00345  -0.0982   0.7962   1.0000
   0.500   0.4895   0.00888   0.00340  -0.0976   0.7826   1.0000
   0.750   0.5158   0.00897   0.00337  -0.0969   0.7684   1.0000
   1.000   0.5421   0.00908   0.00336  -0.0962   0.7538   1.0000
   1.250   0.5683   0.00919   0.00337  -0.0956   0.7390   1.0000
   1.500   0.5944   0.00931   0.00339  -0.0949   0.7236   1.0000
   1.750   0.6204   0.00943   0.00343  -0.0943   0.7076   1.0000
   2.000   0.6464   0.00956   0.00349  -0.0936   0.6917   1.0000
   2.250   0.6723   0.00970   0.00355  -0.0930   0.6754   1.0000
   2.500   0.6981   0.00984   0.00364  -0.0923   0.6584   1.0000
   2.750   0.7237   0.00999   0.00370  -0.0916   0.6398   1.0000
   3.000   0.7490   0.01014   0.00378  -0.0908   0.6203   1.0000
   3.250   0.7743   0.01031   0.00389  -0.0901   0.6003   1.0000
   3.500   0.7996   0.01051   0.00403  -0.0894   0.5815   1.0000
   3.750   0.8245   0.01073   0.00416  -0.0886   0.5625   1.0000
   4.000   0.8493   0.01096   0.00434  -0.0879   0.5415   1.0000
   4.250   0.8740   0.01121   0.00455  -0.0871   0.5219   1.0000
   4.500   0.8989   0.01147   0.00477  -0.0864   0.5044   1.0000
   4.750   0.9234   0.01175   0.00501  -0.0856   0.4856   1.0000
   5.000   0.9471   0.01202   0.00525  -0.0847   0.4611   1.0000
   5.250   0.9703   0.01235   0.00553  -0.0838   0.4362   1.0000
   5.500   0.9929   0.01274   0.00584  -0.0827   0.4094   1.0000
   5.750   1.0153   0.01310   0.00617  -0.0817   0.3741   1.0000
   6.000   1.0357   0.01360   0.00648  -0.0803   0.3196   1.0000
   6.250   1.0495   0.01478   0.00710  -0.0782   0.2273   1.0000
   6.500   1.0611   0.01642   0.00808  -0.0760   0.1155   1.0000
   6.750   1.0739   0.01798   0.00932  -0.0738   0.0807   1.0000
   7.000   1.0887   0.01928   0.01061  -0.0717   0.0701   1.0000
   7.250   1.1052   0.02033   0.01174  -0.0699   0.0633   1.0000
   7.500   1.1159   0.02196   0.01336  -0.0674   0.0578   1.0000
   7.750   1.1333   0.02296   0.01445  -0.0658   0.0539   1.0000
   8.000   1.1492   0.02421   0.01570  -0.0640   0.0503   1.0000
   8.250   1.1644   0.02652   0.01792  -0.0624   0.0466   1.0000
   8.500   1.1842   0.02734   0.01889  -0.0611   0.0441   1.0000
   8.750   1.2049   0.02870   0.02034  -0.0600   0.0419   1.0000
   9.000   1.2253   0.03013   0.02182  -0.0590   0.0398   1.0000
   9.250   1.2493   0.03252   0.02416  -0.0589   0.0375   1.0000
   9.500   1.2691   0.03443   0.02630  -0.0578   0.0358   1.0000
   9.750   1.2886   0.03628   0.02840  -0.0566   0.0347   1.0000
  10.000   1.3071   0.03853   0.03091  -0.0553   0.0338   1.0000
  10.250   1.3230   0.04096   0.03360  -0.0538   0.0330   1.0000
  10.500   1.3362   0.04312   0.03597  -0.0522   0.0320   1.0000
  10.750   1.3508   0.04495   0.03786  -0.0511   0.0307   1.0000
  11.000   1.3622   0.04763   0.04066  -0.0498   0.0298   1.0000
  11.250   1.3687   0.05143   0.04474  -0.0480   0.0295   1.0000
  11.500   1.3696   0.05504   0.04867  -0.0456   0.0294   1.0000
  11.750   1.3648   0.05805   0.05197  -0.0425   0.0296   1.0000
  12.000   1.3511   0.06066   0.05490  -0.0385   0.0299   1.0000
  12.250   1.3009   0.06559   0.06048  -0.0332   0.0315   1.0000
  12.500   1.2705   0.07101   0.06625  -0.0318   0.0325   1.0000
  12.750   1.2455   0.07648   0.07197  -0.0320   0.0333   1.0000
  13.000   1.2209   0.08238   0.07809  -0.0333   0.0339   1.0000
  13.250   1.1964   0.08879   0.08469  -0.0356   0.0344   1.0000
  13.500   1.1720   0.09586   0.09192  -0.0391   0.0349   1.0000
  13.750   1.1478   0.10360   0.09980  -0.0434   0.0353   1.0000
  14.000   0.8852   0.13378   0.13083  -0.0625   0.0488   1.0000
  14.250   0.9025   0.13294   0.12996  -0.0599   0.0477   1.0000
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