Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

HOBIE (hobie-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: HOBIE (hobie-il)
Reynolds number: 500,000
Max Cl/Cd: 100.54 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hobie-il-500000.txt
Download as CSV file: xf-hobie-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3825   0.08869   0.08637  -0.0313   1.0000   0.0298
  -8.500  -0.3822   0.08569   0.08341  -0.0320   1.0000   0.0307
  -8.250  -0.5811   0.02605   0.02263  -0.0719   0.9995   0.0216
  -8.000  -0.5512   0.02046   0.01622  -0.0765   0.9965   0.0230
  -7.750  -0.5132   0.02073   0.01656  -0.0787   0.9944   0.0239
  -7.500  -0.4775   0.02065   0.01643  -0.0805   0.9913   0.0252
  -7.250  -0.4428   0.01905   0.01447  -0.0827   0.9880   0.0271
  -7.000  -0.4068   0.01770   0.01292  -0.0852   0.9853   0.0288
  -6.750  -0.3672   0.01792   0.01316  -0.0876   0.9833   0.0302
  -6.500  -0.3347   0.01735   0.01244  -0.0887   0.9780   0.0323
  -6.250  -0.2993   0.01629   0.01114  -0.0906   0.9745   0.0348
  -6.000  -0.2616   0.01627   0.01115  -0.0928   0.9721   0.0364
  -5.750  -0.2234   0.01592   0.01074  -0.0950   0.9704   0.0388
  -5.500  -0.1917   0.01584   0.01050  -0.0956   0.9637   0.0412
  -5.250  -0.1580   0.01443   0.00899  -0.0973   0.9592   0.0441
  -5.000  -0.1240   0.01403   0.00856  -0.0986   0.9540   0.0464
  -4.750  -0.0929   0.01370   0.00814  -0.0991   0.9454   0.0492
  -4.500  -0.0609   0.01353   0.00787  -0.0997   0.9365   0.0511
  -4.250  -0.0308   0.01214   0.00633  -0.1003   0.9264   0.0538
  -4.000  -0.0029   0.01159   0.00575  -0.1002   0.9124   0.0561
  -3.750   0.0248   0.01116   0.00525  -0.1000   0.8981   0.0580
  -3.500   0.0521   0.01082   0.00483  -0.0997   0.8839   0.0601
  -3.250   0.0793   0.01050   0.00442  -0.0993   0.8697   0.0617
  -3.000   0.1063   0.01023   0.00406  -0.0989   0.8556   0.0627
  -2.750   0.1333   0.01010   0.00384  -0.0984   0.8415   0.0636
  -2.500   0.1592   0.00949   0.00315  -0.0979   0.8278   0.0655
  -2.250   0.1856   0.00917   0.00275  -0.0975   0.8144   0.0670
  -2.000   0.2122   0.00895   0.00247  -0.0970   0.8008   0.0687
  -1.750   0.2389   0.00879   0.00225  -0.0966   0.7878   0.0705
  -1.500   0.2658   0.00866   0.00206  -0.0962   0.7759   0.0728
  -1.250   0.2929   0.00856   0.00191  -0.0959   0.7641   0.0748
  -1.000   0.3199   0.00848   0.00177  -0.0955   0.7525   0.0764
  -0.750   0.3470   0.00842   0.00165  -0.0952   0.7410   0.0790
  -0.500   0.3740   0.00834   0.00154  -0.0948   0.7295   0.0851
  -0.250   0.4007   0.00807   0.00148  -0.0945   0.7179   0.1512
   0.000   0.4272   0.00786   0.00152  -0.0943   0.7063   0.2465
   0.250   0.4538   0.00771   0.00153  -0.0939   0.6943   0.2997
   0.500   0.4803   0.00761   0.00156  -0.0936   0.6816   0.3713
   0.750   0.5064   0.00747   0.00160  -0.0932   0.6678   0.4412
   1.000   0.5309   0.00710   0.00169  -0.0926   0.6531   0.6106
   1.250   0.5647   0.00631   0.00172  -0.0935   0.6349   1.0000
   1.500   0.5907   0.00644   0.00174  -0.0929   0.6119   1.0000
   1.750   0.6163   0.00660   0.00177  -0.0923   0.5866   1.0000
   2.000   0.6419   0.00679   0.00183  -0.0917   0.5633   1.0000
   2.250   0.6679   0.00697   0.00190  -0.0912   0.5431   1.0000
   2.500   0.6938   0.00715   0.00200  -0.0907   0.5235   1.0000
   2.750   0.7195   0.00736   0.00211  -0.0902   0.5034   1.0000
   3.000   0.7451   0.00758   0.00222  -0.0897   0.4803   1.0000
   3.250   0.7709   0.00778   0.00235  -0.0892   0.4611   1.0000
   3.500   0.7967   0.00800   0.00250  -0.0887   0.4446   1.0000
   3.750   0.8225   0.00821   0.00265  -0.0883   0.4299   1.0000
   4.000   0.8478   0.00846   0.00283  -0.0878   0.4129   1.0000
   4.250   0.8733   0.00870   0.00302  -0.0873   0.3939   1.0000
   4.500   0.8988   0.00894   0.00319  -0.0868   0.3683   1.0000
   4.750   0.9225   0.00934   0.00339  -0.0860   0.3221   1.0000
   5.250   0.9654   0.01066   0.00415  -0.0840   0.2170   1.0000
   5.500   0.9889   0.01112   0.00454  -0.0833   0.1981   1.0000
   5.750   1.0120   0.01162   0.00490  -0.0825   0.1611   1.0000
   6.000   1.0275   0.01296   0.00569  -0.0808   0.0694   1.0000
   6.250   1.0491   0.01363   0.00633  -0.0797   0.0584   1.0000
   6.500   1.0725   0.01406   0.00680  -0.0789   0.0528   1.0000
   6.750   1.0932   0.01478   0.00754  -0.0777   0.0460   1.0000
   7.000   1.1166   0.01517   0.00796  -0.0770   0.0416   1.0000
   7.250   1.1360   0.01597   0.00877  -0.0756   0.0366   1.0000
   7.500   1.1590   0.01637   0.00921  -0.0748   0.0340   1.0000
   7.750   1.1805   0.01690   0.00975  -0.0738   0.0313   1.0000
   8.000   1.1967   0.01791   0.01080  -0.0720   0.0287   1.0000
   8.250   1.2182   0.01838   0.01134  -0.0709   0.0270   1.0000
   8.500   1.2381   0.01896   0.01195  -0.0697   0.0253   1.0000
   8.750   1.2551   0.01975   0.01277  -0.0681   0.0239   1.0000
   9.000   1.2643   0.02121   0.01430  -0.0654   0.0225   1.0000
   9.250   1.2812   0.02193   0.01511  -0.0637   0.0218   1.0000
   9.500   1.2968   0.02271   0.01597  -0.0619   0.0208   1.0000
   9.750   1.3102   0.02346   0.01677  -0.0598   0.0199   1.0000
  10.000   1.3223   0.02424   0.01759  -0.0575   0.0191   1.0000
  10.250   1.3305   0.02536   0.01875  -0.0549   0.0184   1.0000
  10.500   1.3318   0.02757   0.02105  -0.0516   0.0176   1.0000
  10.750   1.3434   0.02855   0.02214  -0.0496   0.0173   1.0000
  11.000   1.3536   0.02976   0.02348  -0.0476   0.0169   1.0000
  11.250   1.3631   0.03111   0.02495  -0.0456   0.0164   1.0000
  11.500   1.3719   0.03257   0.02652  -0.0438   0.0159   1.0000
  11.750   1.3801   0.03409   0.02814  -0.0420   0.0155   1.0000
  12.000   1.3873   0.03559   0.02974  -0.0404   0.0151   1.0000
  12.250   1.3936   0.03711   0.03133  -0.0389   0.0147   1.0000
  12.500   1.3992   0.03878   0.03305  -0.0376   0.0143   1.0000
  12.750   1.4022   0.04141   0.03578  -0.0362   0.0139   1.0000
  13.000   1.4009   0.04487   0.03949  -0.0347   0.0135   1.0000
  13.250   1.4008   0.04725   0.04205  -0.0337   0.0133   1.0000
  13.500   1.3989   0.05010   0.04509  -0.0329   0.0132   1.0000
  13.750   1.3942   0.05351   0.04872  -0.0324   0.0130   1.0000
  14.000   1.3877   0.05722   0.05263  -0.0322   0.0129   1.0000
  14.250   1.3785   0.06142   0.05704  -0.0325   0.0127   1.0000
  14.500   1.3671   0.06612   0.06196  -0.0333   0.0126   1.0000
  14.750   1.3531   0.07140   0.06746  -0.0347   0.0126   1.0000
  15.000   1.3369   0.07736   0.07363  -0.0368   0.0125   1.0000
  15.250   1.3185   0.08406   0.08054  -0.0396   0.0125   1.0000
  15.500   1.2981   0.09159   0.08829  -0.0433   0.0125   1.0000
  15.750   1.2759   0.09999   0.09690  -0.0479   0.0126   1.0000
  16.000   1.2515   0.10939   0.10651  -0.0535   0.0126   1.0000
  16.250   1.2262   0.11964   0.11694  -0.0599   0.0127   1.0000
  16.500   1.1987   0.13124   0.12873  -0.0674   0.0129   1.0000
  16.750   1.1681   0.14462   0.14227  -0.0762   0.0131   1.0000
  17.000   1.1286   0.16208   0.15987  -0.0875   0.0135   1.0000
<< Back to HOBIE (hobie-il)

Polar data table (+)

Polar graphs


<< Back to HOBIE (hobie-il)