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

HOBIESMO1.DAT (hobiesm-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: HOBIESMO1.DAT (hobiesm-il)
Reynolds number: 100,000
Max Cl/Cd: 60.36 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hobiesm-il-100000-n5.txt
Download as CSV file: xf-hobiesm-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HOBIESMO1.DAT                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3810   0.08890   0.08408  -0.0370   1.0000   0.0308
  -8.500  -0.3851   0.08514   0.08042  -0.0379   1.0000   0.0307
  -8.250  -0.3984   0.08038   0.07579  -0.0392   1.0000   0.0299
  -8.000  -0.4087   0.07636   0.07189  -0.0400   1.0000   0.0294
  -7.500  -0.4221   0.06718   0.06287  -0.0444   1.0000   0.0290
  -7.250  -0.4289   0.06187   0.05760  -0.0473   1.0000   0.0290
  -7.000  -0.4340   0.05456   0.05024  -0.0522   1.0000   0.0288
  -6.750  -0.4234   0.04324   0.03841  -0.0636   0.9971   0.0287
  -6.500  -0.3913   0.03416   0.02833  -0.0735   0.9901   0.0294
  -6.250  -0.3591   0.03149   0.02543  -0.0771   0.9845   0.0322
  -6.000  -0.3263   0.02850   0.02188  -0.0802   0.9786   0.0352
  -5.750  -0.2925   0.02539   0.01807  -0.0828   0.9730   0.0371
  -5.500  -0.2574   0.02323   0.01537  -0.0849   0.9682   0.0393
  -5.250  -0.2259   0.02183   0.01380  -0.0863   0.9614   0.0436
  -5.000  -0.1898   0.02058   0.01231  -0.0883   0.9567   0.0477
  -4.750  -0.1577   0.01944   0.01088  -0.0892   0.9498   0.0518
  -4.500  -0.1221   0.01846   0.00986  -0.0910   0.9444   0.0599
  -4.250  -0.0875   0.01768   0.00893  -0.0925   0.9385   0.0769
  -4.000  -0.0533   0.01724   0.00846  -0.0939   0.9318   0.1043
  -3.750  -0.0182   0.01697   0.00812  -0.0955   0.9259   0.1313
  -3.500   0.0138   0.01674   0.00787  -0.0965   0.9182   0.1541
  -3.250   0.0481   0.01639   0.00740  -0.0977   0.9120   0.1720
  -3.000   0.0793   0.01606   0.00701  -0.0983   0.9039   0.1875
  -2.750   0.1118   0.01571   0.00664  -0.0992   0.8967   0.2033
  -2.500   0.1430   0.01541   0.00633  -0.0998   0.8887   0.2221
  -2.250   0.1733   0.01515   0.00606  -0.1001   0.8803   0.2440
  -2.000   0.2053   0.01488   0.00581  -0.1008   0.8728   0.2705
  -1.750   0.2337   0.01469   0.00566  -0.1008   0.8631   0.3008
  -1.500   0.2635   0.01447   0.00548  -0.1010   0.8546   0.3339
  -1.250   0.2925   0.01428   0.00534  -0.1010   0.8454   0.3714
  -1.000   0.3203   0.01410   0.00524  -0.1008   0.8353   0.4137
  -0.750   0.3489   0.01385   0.00513  -0.1007   0.8260   0.4681
  -0.500   0.3761   0.01351   0.00506  -0.1003   0.8165   0.5519
  -0.250   0.3977   0.01285   0.00505  -0.0984   0.8058   0.7451
   0.000   0.4386   0.01253   0.00486  -0.1006   0.7958   1.0000
   0.250   0.4667   0.01259   0.00478  -0.1003   0.7854   1.0000
   0.500   0.4940   0.01267   0.00475  -0.1000   0.7742   1.0000
   0.750   0.5206   0.01277   0.00477  -0.0996   0.7622   1.0000
   1.000   0.5473   0.01288   0.00479  -0.0991   0.7502   1.0000
   1.250   0.5740   0.01298   0.00482  -0.0987   0.7381   1.0000
   1.500   0.6007   0.01309   0.00487  -0.0983   0.7259   1.0000
   1.750   0.6274   0.01320   0.00495  -0.0978   0.7135   1.0000
   2.000   0.6539   0.01333   0.00504  -0.0973   0.7009   1.0000
   2.250   0.6804   0.01346   0.00514  -0.0968   0.6880   1.0000
   2.500   0.7067   0.01360   0.00528  -0.0963   0.6746   1.0000
   2.750   0.7328   0.01376   0.00543  -0.0958   0.6610   1.0000
   3.000   0.7588   0.01393   0.00560  -0.0952   0.6472   1.0000
   3.250   0.7847   0.01412   0.00580  -0.0946   0.6329   1.0000
   3.500   0.8104   0.01432   0.00606  -0.0941   0.6184   1.0000
   3.750   0.8359   0.01454   0.00632  -0.0934   0.6036   1.0000
   4.000   0.8613   0.01478   0.00660  -0.0928   0.5887   1.0000
   4.250   0.8866   0.01503   0.00692  -0.0922   0.5735   1.0000
   4.500   0.9117   0.01531   0.00730  -0.0915   0.5582   1.0000
   4.750   0.9363   0.01559   0.00766  -0.0907   0.5407   1.0000
   5.000   0.9573   0.01586   0.00784  -0.0890   0.5037   1.0000
   5.250   0.9761   0.01625   0.00807  -0.0871   0.4539   1.0000
   5.500   0.9947   0.01678   0.00845  -0.0853   0.3998   1.0000
   5.750   1.0075   0.01783   0.00897  -0.0828   0.3010   1.0000
   6.250   1.0158   0.02276   0.01206  -0.0768   0.0431   1.0000
   6.500   1.0318   0.02400   0.01343  -0.0749   0.0361   1.0000
   6.750   1.0460   0.02536   0.01496  -0.0729   0.0327   1.0000
   7.000   1.0608   0.02652   0.01632  -0.0710   0.0294   1.0000
   7.250   1.0733   0.02782   0.01774  -0.0689   0.0262   1.0000
   7.500   1.0813   0.02944   0.01947  -0.0663   0.0245   1.0000
   7.750   1.0861   0.03153   0.02162  -0.0634   0.0234   1.0000
   8.000   1.0994   0.03304   0.02320  -0.0613   0.0227   1.0000
   8.250   1.1163   0.03473   0.02505  -0.0597   0.0219   1.0000
   8.500   1.1352   0.03640   0.02686  -0.0585   0.0204   1.0000
   8.750   1.1538   0.03814   0.02873  -0.0574   0.0188   1.0000
   9.000   1.1737   0.04022   0.03096  -0.0565   0.0177   1.0000
   9.250   1.1948   0.04271   0.03362  -0.0558   0.0171   1.0000
   9.500   1.2133   0.04543   0.03654  -0.0549   0.0167   1.0000
   9.750   1.2283   0.04845   0.03981  -0.0538   0.0163   1.0000
  10.000   1.2389   0.05167   0.04331  -0.0522   0.0161   1.0000
  10.250   1.2437   0.05490   0.04683  -0.0501   0.0160   1.0000
  10.500   1.2433   0.05808   0.05031  -0.0477   0.0159   1.0000
  10.750   1.2385   0.06155   0.05405  -0.0452   0.0158   1.0000
  11.000   1.2300   0.06519   0.05797  -0.0429   0.0156   1.0000
  11.500   1.2027   0.07273   0.06606  -0.0396   0.0154   1.0000
  11.750   1.1874   0.07644   0.07003  -0.0389   0.0154   1.0000
  12.000   1.1717   0.08063   0.07447  -0.0390   0.0153   1.0000
  12.250   1.1559   0.08545   0.07951  -0.0399   0.0153   1.0000
  12.500   1.1393   0.09064   0.08490  -0.0415   0.0153   1.0000
  12.750   1.1221   0.09635   0.09081  -0.0439   0.0153   1.0000
  13.000   1.1057   0.10255   0.09718  -0.0468   0.0154   1.0000
  13.500   0.8943   0.12003   0.11578  -0.0552   0.0179   1.0000
  13.750   0.8646   0.13016   0.12605  -0.0622   0.0184   1.0000
<< Back to HOBIESMO1.DAT (hobiesm-il)

Polar data table (+)

Polar graphs


<< Back to HOBIESMO1.DAT (hobiesm-il)