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HOBIESMO1.DAT (hobiesm-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: HOBIESMO1.DAT (hobiesm-il)
Reynolds number: 200,000
Max Cl/Cd: 78.96 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hobiesm-il-200000-n5.txt
Download as CSV file: xf-hobiesm-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3880   0.08697   0.08352  -0.0357   1.0000   0.0167
  -8.750  -0.3921   0.08301   0.07962  -0.0368   1.0000   0.0167
  -8.500  -0.3993   0.07905   0.07573  -0.0376   1.0000   0.0168
  -8.250  -0.4107   0.07545   0.07223  -0.0376   1.0000   0.0167
  -8.000  -0.4249   0.07179   0.06868  -0.0377   1.0000   0.0167
  -7.750  -0.4390   0.06736   0.06435  -0.0391   1.0000   0.0166
  -7.500  -0.4271   0.03128   0.02707  -0.0835   0.9810   0.0160
  -7.250  -0.3982   0.02681   0.02195  -0.0878   0.9739   0.0171
  -7.000  -0.3645   0.02434   0.01895  -0.0908   0.9696   0.0190
  -6.750  -0.3350   0.02234   0.01650  -0.0923   0.9625   0.0201
  -6.500  -0.3035   0.01966   0.01343  -0.0944   0.9577   0.0217
  -6.250  -0.2724   0.01844   0.01202  -0.0956   0.9514   0.0234
  -6.000  -0.2400   0.01756   0.01091  -0.0969   0.9453   0.0260
  -5.750  -0.2072   0.01649   0.00961  -0.0981   0.9395   0.0276
  -5.500  -0.1760   0.01564   0.00855  -0.0989   0.9322   0.0288
  -5.250  -0.1437   0.01463   0.00742  -0.1001   0.9259   0.0313
  -5.000  -0.1130   0.01402   0.00670  -0.1008   0.9180   0.0350
  -4.750  -0.0814   0.01345   0.00597  -0.1015   0.9109   0.0386
  -4.500  -0.0510   0.01285   0.00528  -0.1020   0.9028   0.0461
  -4.250  -0.0215   0.01237   0.00482  -0.1023   0.8945   0.0658
  -4.000   0.0087   0.01208   0.00451  -0.1028   0.8867   0.0881
  -3.750   0.0369   0.01188   0.00425  -0.1027   0.8775   0.1028
  -3.500   0.0656   0.01169   0.00403  -0.1029   0.8693   0.1208
  -3.250   0.0935   0.01153   0.00388  -0.1028   0.8602   0.1411
  -3.000   0.1210   0.01137   0.00368  -0.1027   0.8511   0.1558
  -2.750   0.1490   0.01119   0.00347  -0.1026   0.8428   0.1684
  -2.500   0.1760   0.01104   0.00327  -0.1023   0.8331   0.1817
  -2.250   0.2033   0.01089   0.00312  -0.1021   0.8239   0.1986
  -2.000   0.2307   0.01076   0.00298  -0.1019   0.8151   0.2196
  -1.750   0.2575   0.01064   0.00288  -0.1016   0.8051   0.2427
  -1.500   0.2845   0.01054   0.00279  -0.1013   0.7955   0.2666
  -1.250   0.3116   0.01044   0.00272  -0.1010   0.7860   0.2939
  -1.000   0.3383   0.01035   0.00267  -0.1007   0.7757   0.3235
  -0.750   0.3650   0.01027   0.00263  -0.1004   0.7653   0.3535
  -0.500   0.3917   0.01018   0.00259  -0.1000   0.7549   0.3855
  -0.250   0.4181   0.01008   0.00257  -0.0996   0.7443   0.4249
   0.000   0.4440   0.00993   0.00257  -0.0992   0.7329   0.4783
   0.250   0.4689   0.00968   0.00260  -0.0985   0.7213   0.5695
   0.750   0.5308   0.00889   0.00257  -0.0990   0.6973   1.0000
   1.000   0.5574   0.00899   0.00258  -0.0986   0.6847   1.0000
   1.250   0.5839   0.00910   0.00261  -0.0982   0.6716   1.0000
   1.500   0.6103   0.00923   0.00266  -0.0978   0.6583   1.0000
   1.750   0.6366   0.00936   0.00273  -0.0974   0.6446   1.0000
   2.000   0.6629   0.00950   0.00280  -0.0970   0.6307   1.0000
   2.250   0.6890   0.00965   0.00290  -0.0965   0.6166   1.0000
   2.500   0.7151   0.00981   0.00303  -0.0961   0.6025   1.0000
   2.750   0.7411   0.00998   0.00317  -0.0956   0.5882   1.0000
   3.000   0.7670   0.01017   0.00332  -0.0952   0.5740   1.0000
   3.250   0.7928   0.01036   0.00350  -0.0947   0.5597   1.0000
   3.500   0.8184   0.01057   0.00371  -0.0942   0.5454   1.0000
   3.750   0.8440   0.01078   0.00393  -0.0937   0.5310   1.0000
   4.000   0.8694   0.01101   0.00417  -0.0932   0.5157   1.0000
   4.250   0.8930   0.01131   0.00438  -0.0923   0.4875   1.0000
   4.500   0.9152   0.01169   0.00465  -0.0912   0.4495   1.0000
   4.750   0.9372   0.01211   0.00494  -0.0901   0.4095   1.0000
   5.000   0.9570   0.01272   0.00530  -0.0888   0.3511   1.0000
   5.250   0.9720   0.01382   0.00587  -0.0869   0.2532   1.0000
   5.500   0.9741   0.01650   0.00728  -0.0836   0.0529   1.0000
   5.750   0.9928   0.01749   0.00820  -0.0822   0.0314   1.0000
   6.000   1.0126   0.01831   0.00914  -0.0809   0.0249   1.0000
   6.250   1.0327   0.01908   0.01003  -0.0796   0.0210   1.0000
   6.500   1.0518   0.01990   0.01098  -0.0782   0.0188   1.0000
   6.750   1.0688   0.02087   0.01206  -0.0766   0.0172   1.0000
   7.000   1.0809   0.02224   0.01353  -0.0743   0.0159   1.0000
   7.250   1.0950   0.02338   0.01476  -0.0723   0.0147   1.0000
   7.500   1.1107   0.02435   0.01583  -0.0706   0.0135   1.0000
   7.750   1.1238   0.02559   0.01716  -0.0685   0.0127   1.0000
   8.000   1.1367   0.02691   0.01860  -0.0664   0.0121   1.0000
   8.250   1.1492   0.02829   0.02005  -0.0642   0.0115   1.0000
   8.500   1.1625   0.02976   0.02160  -0.0623   0.0111   1.0000
   8.750   1.1770   0.03139   0.02331  -0.0606   0.0107   1.0000
   9.000   1.1931   0.03338   0.02538  -0.0594   0.0103   1.0000
   9.250   1.2112   0.03599   0.02815  -0.0584   0.0096   1.0000
   9.500   1.2241   0.03744   0.02985  -0.0565   0.0091   1.0000
   9.750   1.2367   0.03942   0.03209  -0.0547   0.0086   1.0000
  10.000   1.2475   0.04192   0.03487  -0.0528   0.0083   1.0000
  10.250   1.2540   0.04459   0.03782  -0.0506   0.0082   1.0000
  10.500   1.2563   0.04737   0.04093  -0.0482   0.0081   1.0000
  10.750   1.2546   0.05035   0.04420  -0.0457   0.0080   1.0000
  11.000   1.2495   0.05351   0.04764  -0.0434   0.0079   1.0000
  11.250   1.2411   0.05696   0.05135  -0.0415   0.0078   1.0000
  11.500   1.2308   0.06062   0.05527  -0.0400   0.0078   1.0000
  11.750   1.2181   0.06467   0.05958  -0.0392   0.0078   1.0000
  12.000   1.2041   0.06910   0.06423  -0.0390   0.0078   1.0000
  12.250   1.1884   0.07403   0.06939  -0.0396   0.0079   1.0000
  12.500   1.1717   0.07939   0.07497  -0.0410   0.0079   1.0000
  12.750   1.1537   0.08538   0.08116  -0.0432   0.0079   1.0000
  13.000   1.1352   0.09191   0.08789  -0.0463   0.0080   1.0000
  13.250   1.1162   0.09910   0.09525  -0.0502   0.0080   1.0000
  13.500   1.0973   0.10694   0.10325  -0.0549   0.0081   1.0000
  13.750   1.0782   0.11565   0.11212  -0.0605   0.0082   1.0000
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